InteractiveEducationalToolforSim

ulation

and

Visualization

ofFluid

Flows

Sow

mitra

Singh

Dyn

aflow,Inc.

An

impro

ved

understa

nding

ofth

efu

ndamenta

lco

nce

pts

inFluid

Mech

anicslaysth

efoundation

forpursuingeithercu

ttingedgeaca

demic

rese

arch

orta

cklingindustry

relate

dpro

blems.

ThebasicprinciplesofFluid

Mech

anics,

dueto

their

math

ematica

lco

mplexities,

are

often

tough

togra

spforbeginners.Thepre

sentwork

introduce

san

innovativeeduca

-tionalso

ftware

thathelpsalearn

erbypro

vidinginte

ractively

aphysica

lpictu

re(v

isualiza

-tion,anim

ation,andillustra

tion)ofanunderlyingflow

phenomenonandth

eco

rresp

onding

math

ematica

lform

ulation

itse

rvesasalink

betw

een

themath

ematics

and

thephysics

of

Fluid

Mech

anics.

The

software

toolhas

an

inte

ractive

GUI(G

raphicalUse

rIn

terface

)th

atfacilita

tesstudents

examination

ofth

ee!ectsofch

anging

variousflow

para

mete

rsin

agiven

flow

set-up.TheGUIalsoallowsth

elearn

erto

saveth

ere

sultsand

anim

ationsin

filesth

atca

nbeexaminedlate

r.This

inte

ractiveto

olis

expectedto

serv

easavirtu

alfluids

labora

tory

formillionsofengineeringstudents

acr

oss

variousdisciplinesand

isexpected

totremendously

pro

mote

activese

lf-learn

ing.

Inth

epre

sentwork

theto

olis

applied

tostudyafew

case

ssu

chasth

eflow

aro

und

sin-

gle/multiple

cylinders,hydro

foils,

Rankinebodies,..

etc.Theto

ol’sca

pabilitiesin

captu

r-inginviscid

flow

aro

und

hydro

foilsand

inca

ptu

ringflow

pattern

sgenera

ted

byinte

racting

singularitiesis

alsosh

owca

sed.

1of1

AmericanInstituteofAeronauticsandAstronautics

Resp

onse

ofabubble

cloud

toacoustic

pressure

variations

Ti!anyFourm

eau,Sow

mitra

Singh

Dyn

aflow,Inc

Itis

well

known

thatca

vitation

occ

urring

on

apro

pellerca

nca

use

significa

ntero

sion

damage

toth

epro

pellerovertime.T

he

high

pre

ssure

socc

urring

ina

cavitation

field

are

dueto

theco

llapse

ofindividualbubblesand

bubble

clouds.

There

fore

,understa

ndingth

ebehaviorofbubble

cloudsand

the

pre

ssure

sth

ey

create

iscr

ucialto

understa

nding

and

controlling

thephenomenon

ofca

vitation

ero

sion.Furtherm

ore

,labora

tory

investigations

ofca

vitation

ero

sion

are

usu

ally

perform

ed

atsm

allerscalesin

length

and

timeand

itis

notalw

aysclearasto

how

thecloud

resp

onse

and

theco

rresp

onding

cavitating

pre

ssure

field

scale

with

length

and

time.

Inth

epre

sentstudy,

there

sponse

ofa

bubble

cloud

toan

impose

daco

ustic

field

isstudied

inord

erto

understa

nd

the

scaling

laws.

The

study

wasco

nducted

atDYNAFLOW

using

theco

dePHANTOM

CLOUD,which

solvesforth

edynamicsandmotionofallth

ebubblesbyacc

ountingforth

epre

sence

ofth

eoth

erbubbles.

This

reveals

both

individualbubble

dynamicsand

overa

llbubble

cloud

dynamics.

The

firstpart

ofth

estudy

focu

sed

on

bubble

cloud

resp

onse

toasinuso

idalaco

ustic

pre

ssure

variation.

Forsm

all

magnitudesofth

eapplied

pre

ssure

oscillations,

the

highest

bubble

cloud

amplitu

de

oscillationswere

ach

ieved

when

the

frequency

ofth

eim

pose

daco

ustic

field

wasclose

toth

ebubble

cloudfrequency

.There

sultsobta

inedsh

owedgoodagre

ement

with

analytic

resu

ltsavailable

inth

elite

ratu

re,which

are

usu

ally

linearize

d.

For

larg

emagnitudesofth

eapplied

aco

ustic

pre

ssure

oscillations,

however,

itwasobse

rved

thatth

eamplitu

de

ofth

ecloud

oscillationsincr

ease

dwith

decr

easing

frequenciesofth

eim

pose

daco

ustic

field.In

these

cond

part

ofth

estudy,

there

sponse

ofbubble

cloudsofdi!

ere

nt

initialvoid

fractions

near

arigid

wall,to

astro

ng

step

pre

ssure

was

investigate

d.

Itwasfound

thata

decr

ease

inth

eso

und

speed

ofth

emedium

(with

incr

easing

cloud

void

fraction)decr

ease

sth

epeak

and

incr

ease

sth

eperiod

ofth

epre

ssure

wave

reach

ing

the

wall.

Itwasalso

found

thatincr

easing

the

numberofbubblesin

the

cloud,orre

ducing

the

size

ofth

ebubblesin

the

cloud

resu

lted

inhigherpeaksand

smallerperiodsofth

epre

ssure

waveappearing

on

thebottom

plate

.Someofth

ere

sultsobta

ined

were

verified

against

numerica

lre

sultsavailable

inth

elite

ratu

re.

1of1

AmericanInstituteofAeronauticsandAstronautics

MESSENGER

Pro

pulsion

System

Cru

iseand

MOI

Perform

ance

Marc

Wilson,CarlEngelbrecht,Michael

Trela

JohnsHopkinsUniversity

Applied

PhysicsLaboratory

The

MErc

ury

Surface

,Space

ENvironment,

GEoch

emistry,

and

Ranging

(MESSEN-

GER)mission

wasdesigned

tounlock

the

secr

ets

ofourso

larsy

stemsinnerm

ost

planet,

revealing

clues

toth

eplanets

enigmatic

geologicalhisto

ry,unusu

ally

high

density,and

radar-re

flective

mate

rials

atth

epoles,

among

many

oth

erdeca

des-old

unansw

ere

dques-

tions.

MESSENGER

began

itsjourn

ey

on

3August

2004,when

itwaslaunch

ed

from

the

CapeCanavera

lAir

Forc

eSta

tion

inFlorida,and

thesp

ace

craft

wassu

ccessfu

lly

inse

rted

into

itsdestination

orb

itaboutM

erc

ury

on

18

March

2011.

On

itsway

toM

erc

ury

,th

eM

ESSENGER

space

craft

complete

d12

trajectory

-correction

maneuvers,five

deep-space

maneuvers,and

onecr

iticalM

erc

ury

orb

it-inse

rtion

maneuver.

This

paperdescribesth

eopera

tion

and

perform

ance

ofth

epro

pulsion

system

duringth

eM

ESSENGER

space

crafts

inte

rplaneta

rycr

uisephase

and

thro

ugh

itsinse

rtion

into

orb

itaboutM

erc

ury

.

1of1

AmericanInstituteofAeronauticsandAstronautics

Developmentofan

AdaptiveLeadingEdgeDro

op

Mech

anism

toReduceTake-O

!and

Landing

Casu

altieson

LightSport

Aircra

ft

MarioChris,JohnReidy,

Je!

Witz

Xavier

HighSchool

Sta

lling

isoneofth

elarg

est

dangers

whileflying

an

aircr

aft.Sta

lling

occ

urs

when

the

separa

tion

ofairflow

going

overand

underth

ewing

beco

mesto

osignifica

ntand

resu

lts

inth

eloss

oflift

and

controloverth

eaircr

aft.

Aircr

aft

Owners

and

Pilots

Association

reports

that

stalling

acc

ounts

for

13.7The

goalofth

ispro

ject

isto

design

an

adaptive

leadingedgecu

!forlightsp

ort

aircr

aft

whichwilldecr

ease

dra

gbyutilizingafu

ele"cient

wingcu

!angle

atallco

nditions,

whileincr

easingstallangle

byadaptingwingcu

!angle

for

this

purp

ose

when

high

anglesofattack

are

appro

ach

ed.Thedesign

willbecr

eate

dusing

compute

raided

design

(CAD)

software

and

willth

en

be

analyze

dusing

computa

tional

fluid

dynamics(C

FD)so

ftware

.Sta

tics

equationswillbe

use

dto

calculate

the

required

actuato

rforc

esforth

emech

anism

ofth

eadaptive

wing

cu!.

Ultim

ate

ly,th

epurp

ose

of

this

design

isto

notonly

incr

ease

fuele"ciency

butalso

incr

ease

safety

by

reducing

the

risk

ofstalling

inflight.

Analysisofdra

gre

sultsfrom

CFD

studiesofth

evariousleading

edge

dro

op

configura

tionsatth

edi!

ere

ntclim

b,cr

uise,and

descentco

nditionsofflight

indicate

sth

atinco

rpora

tion

ofth

edesigned

mech

anism

on

all

lightsp

ort

aircr

aft

willsa

ve

appro

xim

ate

ly170

thousa

nd

gallonsoffu

el,

corresp

onding

tosa

vingsofover1.04

million

dollars,peryear.

This

correlate

sto

reductionsin

over3million

poundsofCO2emissions,

which

isaboutth

eamountabso

rbed

by

64th

ousa

nd

trees,

peryear.

1of1

AmericanInstituteofAeronauticsandAstronautics

InterfaceRedesign

forGeoCam

Pro

ject

TyTrapps

CapitolCollege

TyTrapps,

CapitolCollegeNASA

AmesAcademyRese

arch

Associate

-Undergraduate

Inte

rn

Mento

r:

Dr.

Terry

Fong

Code:

TIBranch:

Inte

lligent

Robotics

Group,In

telligent

SystemsDivision

Clean,consistentdesign

isone

ofth

ekey

attribute

sofany

well

thoughtoutso

ftware

inte

rface.Even

moreso

forapplicationsuse

dby

rescueworkers,

theuse

rmust

beable

to

quickly

navigate

thesite

.TheGeoCam

Project,

which

isaweb-b

ase

dmappinglocato

rfor

rescuecrews,

hasasimple

enoughte

mplate

,yetth

edesignis

somewhatoutofdate

andnot

asintu

itiveasit

could

beforbasiccompute

ruse

rs.

Theta

skwassimple:M

akeit

easierfor

resp

ondersto

collaborate

during

acrisis

by

sharing

geosp

atialdata

.In

addition,anoth

er

goalwasto

utilizeth

eAndroid

DevelopmentEnvironmentto

create

mobileapplicationsfor

thedisasterreliefcommunity.

Rese

arch

wasconducte

dasto

how

tointe

grate

EmberJS

into

thecurrentJQueryframework.Onceproto

typesweredrawn

out,

developmentbegan

on

changing

the

currentinte

rface,using

Google

MapsAPI,

KM

LM

ap

Layers,

JQuery

and

Ember.Thenew

design

willbetteraid

NASA

emergency

perso

nneland

state

orcity

rescueunitsin

quickly

accessingmap

locationsin

theeventofan

emergencyand

empower

citizensto

actively

participate

inrescuee!orts

on

their

mobiledevices.

1of1

AmericanInstituteofAeronauticsandAstronautics

NumericalSim

ulation

ofBubble

Flow

Interactions

ArvindJayap

rakash

Dyn

aflow

Inc.

Stu

dyofca

vitationince

ptionte

ach

esusth

atliquidsra

rely

existunderapure

monopha-

sicform

andth

atbubble

nucleiare

omnipre

sent.

Whileformanyapplica

tionsth

ese

bubble

nucleihavenoim

pact

and

can

beignore

din

CFD

simulations,

there

are

flow

fieldswhere

thepre

sence

anddynamicsofth

ese

bubblespro

foundly

a!ect

thephysics

athand.W

hena

micro

scopic

bubble

nucleusenco

unte

rsalarg

enegativepre

ssure

gra

dientin

theliquid

flow,

itexpands.

Depending

on

the

dynamic

balance

betw

een

the

pre

ssure

sgenera

ted

by

the

inertia

ofth

eliquid,th

ebubble

gasco

nte

nt,

andth

esu

rface

tension,th

ebubble

maygro

wexplosively,exce

edingitsequilibrium

volume,and

then

collapse

violently,

genera

tinghigh

aco

ustic

and

dynamic

pre

ssure

s.These

could

resu

ltin

hydro

dynamic

noise,mate

rials

ero

-sion,anddegra

dationofperform

ance

.W

henco

ntrolled,th

eyca

nalsobeexploitedfordra

gre

duction,ch

emicalre

action

enhance

ments,disinfection,pro

pulsion

impro

vements,mate

-rials

cleaning,cu

tting,and

noise

reduction.

Where

bubblesa!ect

the

flow

significa

ntly,

treatingth

em

asdiscr

ete

entitiesand

track

ingth

eir

motion

and

deform

ation

may

pro

vide

importantinsightto

the

design

engineer.

One

example

where

adiscr

ete

bubble

model

isvery

use

fulis

thedete

rmination

ofca

vitation

ince

ption

on

advance

dequipmentdesign,

such

astu

rbomach

inery

.In

aCFD

flow

field,aco

mmonly

use

dcr

iterion

isth

atca

vitation

occ

urs

where

verth

eliquid

pre

ssure

dro

psbelow

the

vapourpre

ssure

.This

assumption

failsif

the

liquid

isnotsu

persatu

rate

dwith

nucleiand

isparticularly

pro

blematic

fora

designth

ataim

sto

avoid

cavitationco

mplete

ly.Usingre

sultsofpre

viousexte

nsivestudies

on

non-spherica

lbubble

dynamicsand

their

inte

ractionswith

vorticalflow

stru

cture

sand

oth

erbubbles,

asimplified

Surface

Avera

ged

Pre

ssure

(SAP)sp

herica

lbubble

dynamics

modeland

aLagra

ngian

bubble

track

ing

scheme

hasemerg

ed.

Inth

eSAP

scheme,th

epre

ssure

and

velocity

ofth

esu

rrounding

flow

field

are

avera

ged

on

the

bubble

surface

,and

then

use

dforca

lculationsofth

ebubble

motion

and

volumedynamics.

This

pro

duce

sa

remark

ably

acc

ura

tesimulation

ofth

ebubble

dynamics,

which

acc

ounts

for

the

non-

uniform

ityofth

eliquid

flow

filed

inwhich

thebubble

isevolving.This

wasdeveloped

and

implemente

dasa

Use

rDefined

Function

(UDF)in

Fluentand

enablesco

mputa

tionsin

reaso

nable

CPU

timesofa

realnucleifield

distribution.Pre

sente

dhere

isth

edeveloped

appro

ach

and

someexamplesofapplica

tionsto

engineeringapplica

tions.

1of1

AmericanInstituteofAeronauticsandAstronautics

Optimizingth

eDesign

ofan

InertialElectrostatic

ConfinementSystem

JoshuaSloane

University

ofMarylandCollegePark

An

inertialelectrostaticconfinementsy

stem

compose

dofmultiple

dodecahedralgrids,

aswell

aselectron

core

neutralization,is

considered

asa

meansofim

proving

e!ciency.

The

first

step

ofth

erese

arch

was

todete

rmine

the

electrostatic

properties

ofa

single

dodecahedralgrid

withuniform

pote

ntial.

This

includedcalculatingth

echargedistribution

on

thegrid,and

thepote

ntialdueto

thecharged

grid.

Using

theparaxialray

equation,

themotionofbeamsofproto

nandboronionsdueto

amulti-grid

configurationis

modeled.

From

this,th

efu

sionpowergenerate

dbyaparticularconfigurationis

dete

rmined.Finally,a

gradientroutineandsimulate

dannealingroutineareuse

dto

findth

eoptimalconfiguration

thatmaxim

izesth

efu

sion

outp

utofth

esy

stem.

Thefu

sion

powergenerate

dfrom

theoptimized

configurationsis

unexpecte

dly

low,on

theorderof10-8

Watts.

This

ispossibly

dueto

amiscalculation

orbugin

thesimulation,

and

willbeconsidered

inmoredepth

asIcontinuemy

rese

arch.Futu

rerese

arch

willalso

includeusingth

eCOM

SOL

Multiphysicsso

ftwareto

analyzese

veralmechanismsbywhich

theelectronscan

beconfined,su

ch

aselectrostaticallyaswell

aswith

permanentmagnets.

1of1

AmericanInstituteofAeronauticsandAstronautics

Tra

jecto

ryCalculationsand

theJupiterSystem

MarioChris

Xavier

HighSchool

Essentialto

the

planning

ofany

space

mission

isth

eprocess

ofcalculating

required

velocitiesandtrip

times,

andresu

ltantmass

ratios,

ofth

edesiredtrajecto

rybetw

eenEarth

and

the

inte

nded

destination.

These

necessary

calculationswere

conducte

dto

design

a

frameworkforasp

acemission

toanyofth

ese

veralplanets

and

moonsin

theSolarSystem

thatmay

be

capable

ofsu

staining

life.

Jupiterand

itsmoons,

Europa,Ganymede,and

Callisto

,are

among

the

most

plausible

environments

for

life.

However,when

planning

apilote

dmission

toJupiter,th

eharmfu

lradiation

field

wasa

major

concern

thatwas

addressed,asit

isim

porta

ntto

take

note

ofany

risksto

the

crew’s

health.

Inaddition,

scenarioswereconsidered

such

thatoneofth

emoons,

preferably

safe

tohumans,

may

be

use

dasabase

tocontrolinvestigationofth

eoth

ertw

omoons.

TheenvironmentofJupiter

and

itsmoonswerealsostudied

foradiscussion

ofpossible

utilization

forlife

supportand

in-situ

propellant.

Taken

asa

whole,th

ese

examinationsofpossibilitiesoffu

turepilote

d

missionsto

Jupiterand

itsicymoons,

alongwith

calculationsforcorresp

ondingtrajecto

ry

requirements,may

provebeneficialin

these

arch

forextrate

rrestriallife.

1of1

AmericanInstituteofAeronauticsandAstronautics

STEM

Educa

tion

atth

eNationalAeroSpace

Tra

ining

And

Resea

rch

(NASTAR)Cen

ter,

AM

odel

for

Corp

ora

teSustainability

Gregory

Kennedy

NASTAR

Center

Loca

ted

inSouth

ampto

n,PA,th

eNationalAero

Space

Tra

ining

And

Rese

arch

(NAS-

TAR)Cente

ris

aco

mmerc

ialfacility

thatco

nductssp

ace

flighttraining,advance

dpilot

training,re

search,and

K-12

inform

aleduca

tionalpro

gra

ms.

The

NASTAR

Cente

ris

awholly

owned

subsidiary

ofETC,a

manufacture

rofaero

medicaltraining

and

rese

arch

equipment.

TheNASTAR

Cente

ris

anA!liate

Memberofth

eNASA

Pennsy

lvania

Space

Gra

ntConso

rtium

and

wasth

efirstfacility

tore

ceive

safety

appro

valfrom

the

FAA

for

commerc

ialsp

ace

flighttraining.

In2009,th

edecision

was

made

tota

ke

apro

active

position

on

STEM

educa

tion

toinsp

ire

students

topursue

care

ers

inscience

and

engineering.

Components

ofth

isef-

fort

includeschoolfield

trips,

asu

mmerday

camp

and

teach

erpro

fessionaldevelopment

pro

gra

msth

atta

keadvanta

geofNASTAR

equipmentand

curricula

topro

videhands-on

experience

sforstudents

and

teach

ers.Since

January

2010,more

than

1,100students

have

visited

NASTAR;274students

haveattended

NASTAR

Camp;and

150te

ach

ers

havepar-

ticipate

din

pro

fessionaldevelopmentpro

gra

ms.

In2012,th

eNASTAR

Cente

rpro

vided

STEM

conte

ntforanoth

er100

students

thro

ugh

NASTAR

Camp

EX

o"-site

pro

gra

ms.

Teach

erpro

gra

msinclude

opportunitiesto

fly

a3-G

suborb

italsp

ace

flightsimulation

inth

eNASTAR

Cente

rce

ntrifuge

and

experience

the

GasLawsin

the

NASTAR

altitude

chamber.

NASTAR

Camp

participants

flyNASTAR

aircr

aft

simulato

rsand

participate

innon-m

otion

suborb

italsp

ace

flightsimulationsin

thece

ntrifugesp

ace

trainingco

ckpit.

In2012,NASTAR

CampEX,asu

mmerca

mpin

aboxpro

duct

debute

d.TheNASTAR

CampEX

kit

includesallsu

pplies,

classro

om

mate

rials,lessonplans,

powerpointslides,

and

videonece

ssary

foraweek-longpro

gra

m.In

itspilotyear,

4NASTAR

CampEX

pro

gra

ms

were

pre

sente

d,which

serv

ed

113

students

inand

aro

und

Philadelphia.Forte

ach

ers,tw

onew

pro

gra

ms,

500

Years

ofFlight,

and

Rock

et

Science

,were

introduce

d.

The

Flight

Physiology

pro

gra

mforte

ach

ers

wasre

vised

using

NASA

SummerofIn

novation

conte

nt,

which

gaveit

more

ofasp

ace

medicineflavor.

NASTAR

STEM

pro

gra

mmingis

pre

sente

dasan

example

ofaprivate

-sectorinitiative

tocr

eate

asu

stainable

educa

tion

initiativeth

atre

inforc

esclassro

om

instru

ction.

1of1

AmericanInstituteofAeronauticsandAstronautics

Geometry-b

ased

ObservabilityM

etric

forAuto

nomous

Navigation

ColinEaton,BoNaasz

NASA

-Goddard

Space

FlightCen

ter

Goddard

sNatu

ralFeatu

reIm

ageReco

gnition

(GNFIR

)so

ftware

supportsauto

nomous

navigationin

pro

xim

ityopera

tionsbyutilizinganedge-b

ase

dmodelofata

rgetvehicle

and

fitting

this

modelto

camera

imagery

togenera

tea

relativepose

estim

ate

.Theacc

ura

cyand

reliability

ofth

epose

estim

ate

sare

highly

dependenton

the

chose

nmodelfeatu

res,

which

histo

rica

llyhavebeen

chose

nmanuallyand

refined

usingtrial-and-error.

Acc

ord

ing

tolinearestim

ation

theory

,th

einverseofth

epro

jection

matrix

(use

din

theleast-square

soptimization)

and

the

standard

deviation

ofth

eestim

ation

error

are

correlate

d.

This

relationsh

ipca

nbeexploited

toobta

inametric

ofth

estate

obse

rvability

simply

from

the

modelgeometry

and

targ

ettrajectory

,withoutre

quiring

imagery

tobe

pro

cessed.

The

new

metric

facilita

tesra

pid

modeland

trajectory

design,and

pro

videsan

impro

ved

real-

timepose

quality

metric.

Asimplified

3-d

egre

e-of-freedom

(3DOF)study

demonstra

ting

thebasicobse

rvability

principlesis

explore

din

deta

il.In

itialre

sultsfrom

applying

these

principlesto

full

6DOF

hard

ware

-in-the-loop

test

data

are

pre

sente

d.

1of1

AmericanInstituteofAeronauticsandAstronautics

Perceived

Realism

AssessmentofSynth

esized

Aircra

ft

EngineFan

Noise

SelenOkcu

NationalInstitute

ofAerospace

Sim

ulation

ofaircr

aft

flyoverevents

can

facilita

tepsy

choaco

ustic

studiesexploring

the

e!ectsofnoisegenera

ted

by

futu

reaircr

aft

designs.

Theperc

eived

realism

ofasimulate

dflyovereventmaybeim

pacted

byth

eperc

eived

realism

ofth

esy

nth

esize

dfan

noiseofth

eaircr

aft

engine.

Short-term

fluctuationsin

tonalamplitu

de

and

frequency

are

important

cuesco

ntributing

toth

atperc

eption

ofre

alism

,butare

notacc

ounte

dforby

pre

dictions

base

don

long-term

avera

ges.

Anew

synth

esis

meth

od

has

been

developed

at

NASA

Langley

Rese

arch

Cente

rto

genera

tere

alistic

aircr

aft

engine

fan

noise

using

pre

dicte

dso

urc

enoisedirectivitiesin

combination

with

short-term

fluctuations.

Inth

enew

meth

od,

fluctuationsin

amplitu

deand

frequency

are

included

base

dupon

analysisofstaticengine

test

data

.Thro

ugh

psy

choaco

ustic

testing,th

isstudy

assessed

perc

eived

e!ectiveness

of

thenew

synth

esismeth

od

ingenera

ting

realistic

fan

noiseso

urc

e.Realism

wasindirectly

assessed

by

judging

the

similarity

ofsy

nth

esize

dso

unds(w

ith

and

withoutfluctuations)

with

reco

rdingsoffan

noise.

Resu

ltsofANOVA

analyse

sindicate

dth

atsu

bjectsju

dged

synth

esize

dfannoisewithfluctuationsasbeingmore

similarto

reco

rdingsth

ansy

nth

esize

dfan

noisewithoutfluctuations.

1of1

AmericanInstituteofAeronauticsandAstronautics

UsingSolarCellsand

SolarTherm

alCollection

to

Captu

reSolarEnerg

y

LaurenWagner

MarriottsRidge

HighSchool

The

purpose

ofth

isexperim

entwasto

dete

rmine

ifa

solarelectric

orso

larth

ermal

panelwould

collectth

emost

solarenergy.

Itwashypoth

esized

thatif

solarenergy

was

collecte

dby

aso

larth

ermaland

aso

larelectric

panelwith

equalsu

rfaceareas,

then

the

solarelectric

panelwould

collectth

emost

energy

because

itwasprofessionally

made

to

collectso

larenergy.In

this

experim

ent,

oneso

larelectric

andoneso

larth

ermalpanelwere

filled

with

equalamounts

ofwate

rand

placed

nextto

each

oth

eroutside.They

werese

t

toth

esa

meangle

which

would

allow

them

tocollectth

eoptimum

amountofso

larenergy.

Throughoutth

eday,th

ete

mperatu

reofth

ewate

rin

both

deviceswasrecorded.From

this

information

itwascalculate

dwhich

devicecollecte

dth

emost

energy.

Theso

larth

ermal

panelconsistentlycollecte

dmoreenergyth

anth

eso

larelectric

panel.

Theaverageamount

ofenergy

gained

from

the

solar

thermalpanelafter

five

trials

was

1,168,032.2

Joules.

Theaverageamountofenergy

gained

from

theso

larelectric

panelwas477,736.4

Joules.

Asy

stematic

errorth

atpossibly

a!ecte

dth

edata

wasth

atboth

panels

were

setto

the

optimum

angle

forenergy

collection

during

summer,and

this

wasmainta

ined

even

into

thefall

soasnotto

introduceanew

variable.Thedata

refu

ted

thehypoth

esis.

Theso

lar

thermalpanelcollecte

dmoreenergyth

anth

eso

larelectric

panel.

Thedata

suggestedth

at

solarth

ermalpanels

would

bemoree!ectiveth

an

solarelectric

panels

tosu

pply

powerto

homes.

1of1

AmericanInstituteofAeronauticsandAstronautics

An

Experimentto

Assess

theM

icro

meteoro

idand

Orb

italDebrisEnvironment

JosephHussey,AlbertSad

ilek

United

StatesNavalAcadem

y

An

Experimentto

Assess

theM

icro

mete

oro

idand

Orb

italDebrisEnvironment

Jose

ph

Hussey(1

),Alb

ert

Sadilek(1

),Robert

Bru

ninga(1

),Chris

Anderson(1

),Hau

Ngo(1

),Fra

nk

Giovane(2

),Robert

Corsaro

(2),

J.C.Liou(3

),Gene

Sta

nsb

ery

(3),

Mark

Burchell(4

),(1

)United

Sta

tesNavalAca

demy,

AnnapolisM

D,21412,USA

(2)NavalRe-

search

Labora

tory

Aco

usticsDivision

(3)NASA

Johnso

nSpace

Cente

rOrb

italDebris

O!ce

(4)University

ofKent

Cente

rofAstro

physics

&Planeta

ryScience

Orb

italdebrisis

an

issu

eofgre

atco

nce

rnforcu

rrentsp

ace

opera

tions.

Space

debris

can

collideand

ruin

space

craft

and

isasa

fety

conce

rnforhuman

space

flight.

Whiledebris

gre

ate

rth

an

ten

centimete

rsis

track

ed

by

the

Department

ofDefense

(DoD),

smaller

micro

-debrisis

notcu

rrently

being

track

ed.Desp

iteitssm

all

size

,micro

-debristraveling

atupward

sofse

ven

kilomete

rsperhourca

nstilldamagesp

ace

craft.

TheDebrisResistive/Aco

ustic

Grid

Orb

italNavy

Senso

r(D

RAGONS)willpro

videa

capability

tomonitororb

italdebrisassm

all

as50

m.

Itwillmeasu

reth

evelocity,mass,

size

,position

inorb

it,im

pact

loca

tion,and

impact

angle

with

thepurp

ose

ofupdatingth

ecu

rrentorb

italdebrismodel(O

RDEM

).Pro

vidingsu

chdata

isth

efirststep

toward

shelp-

ingth

esp

ace

community

betterdefineitsobjectivesformeth

odsto

mitigate

oreliminate

risk

from

micro

-debrisin

orb

it.

DRAGONSis

essentiallyaninstru

mentco

mpose

dofth

reesu

bsy

stems:

anaco

ustic

grid

subsy

stem

(ACS),

resistivegridsu

bsy

stem

(RGS),

andco

mmandanddata

stora

ge(C

DSS).

TheACS

willdete

ctdebrisbyca

ptu

ringth

eaco

ustic

wavesth

atth

eparticle

create

supon

impact

withth

einstru

ment.

TheRGSwillhelp

validate

these

impactsbyta

kingadvanta

ge

ofOhm’s

Law.Using

aco

nstantcu

rrentand

stringsofpara

llelre

sistors

only

75

mwide,

DRAGONS

willmeasu

reth

evoltagevariation

cause

dby

aparticle

impactsbre

aking

one

ormultiple

resistors.Thedata

from

theACS

and

RGS

willbestore

din

theCDSS

until

late

rtransferto

thehost

space

craft

and

downlink

toan

Earth

gro

und

station.

Thedesign

forth

eDRAGONS

flightpro

toty

pehasbeen

complete

d,and

itis

currently

beingbuiltatth

eUnited

Sta

tesNavalAca

demy(U

SNA)mach

inesh

op.Upon

completion

offabrica

tion,it

willbeputth

rough

vibra

tion,aco

ustic,and

therm

alte

ststo

ensu

reth

at

itis

pre

pare

dfor

the

launch

and

space

environments.

Hyperv

elocity

particleswillalso

be

fire

datth

einstru

mentatUSNA

and

atth

eUniversity

ofKentin

ord

erto

calibra

teit

toco

llect

impact

data

from

orb

italdebris.

Afterte

sting,any

changeswillbemadeto

theinitialmodel.

DRAGONS

iscu

rrently

scheduled

tolaunch

toth

eIn

tern

ationalSpace

Sta

tion

(ISS)in

March

of2014.

1of1

AmericanInstituteofAeronauticsandAstronautics

Aero

dynamicsAirfoil

Configura

tion

MannySantana,Jennifer

Vasquez

VaughnCollegeofAeronautics

&Technology

Thesu

rfaceconfiguration

on

agolf

ball

isuniquein

itsdrag

reduction.In

theprese

nt

work,th

eapplication

ofth

isconfiguration

willbeincorporate

dto

apropose

daerodynamic

wingto

investigate

theabilityto

promote

lift

and

reducedrag;investigatingif

therecould

possibly

beadelayin

stallangle

ofanaircraft

wing.This

workwillreconfigureth

einitially

smooth

surfaceatth

eairplanewing

and

apply

adim

pled

surfaceasth

atofth

egolf

ball

while

rese

arching

the

e!ect

on

the

propose

dairfoils

flight

characte

ristics.

An

aircrafts

wingis

considered

tobeth

eheartofan

aircraft;a!ectingcruisesp

eed,ta

keo!

and

landing

dista

nces,

handling

qualitiessu

ch

asstall

speed

and

overall

aerodynamicsofth

eaircraft

duringflight;

this

wingconsistingofan

airfoil

shapeasse

en

initscross-section,producing

aerodynamic

forcesoflift,drag

and

moment.

Asth

eleading

edgeis

rounded

o!

and

the

trailingedgeis

sharp,th

esu

rfaceis

alw

ayssm

ooth

.On

theoth

erhand,th

esciencebehind

itsreduction

indrag

ingolf

ball

comesfrom

thedelay

inse

paration

ofitsboundary

layer

ofair

overitssu

rface;creating

alow

narrowerwaketh

an

thatofa

smooth

surfaced

ball.

Importa

ntasp

ects

ofan

airfoil

design

consist

ofairfoil

geometry,airfoil

selection,sp

eed

range,winggeometry,asp

ectratio,wingsw

eep,ta

perratio,tw

ist,

wingincidence,dihedral,

wingtips,

and

numberofwings.

With

an

exte

nsivenumberofvariablesto

consider,it

has

been

decided

toconcentrate

this

propose

ddesign

and

rese

arch,on

only

theaerodynamic

forcesassociate

dwithflight.

Whilefocusingth

eobjectiveofth

eoutcomeonth

eresu

rfaced

structu

re,an

actu

alaircraft

NACA

airfoil

willbe

use

d.

As

AeronauticalEngineering

students,a

good

aerodynamic

airfoil

willbe

carefu

lly

selecte

dand

incorporate

din

the

design

by

creating

a3-D

modelusing

SolidW

orks.

ItsCFD

Solidworksflow

simulation

packagewillbeutilizedto

gath

errealistic

flightdata

forourpropose

dconfigurationandan

AOA

willbeincorporate

dto

close

lyreflectrealistic

flight.

With

utilizingaCAD

program,

we

willbe

able

toreposition

and

resh

ape

ourpropose

ddesign

togetth

ebest

resu

ltsof

theincorporate

ddesign

on

thesu

rfaceatdi!

erentairsp

eeds,

asair

becomescompressible

and

incompressible

inrelation

toM

ach

number.This

intu

rn

willa!ectth

estall

angle

of

thewingin

conclusion

ofapositivemeansbya!ectingth

eair

within

itsboundarylayeras

thatofgolf

ball.

1of1

AmericanInstituteofAeronauticsandAstronautics

LiftForcePerform

anceofaCarSpoileratCurvatu

res

Dom

inic

Elrington

,Joh

nAndon

VaughnCollegeofAeronautics

andTechnology

Aero

dynamicsis

essentially

importantforan

aircr

aft

and

iscr

ucialforan

auto

mobile.

Aero

dynamic

stru

cture

use

din

the

auto

motive

industry

thatis

on

the

rearofan

auto

-mobileis

called

an

auto

motivewing

butis

popularly

known

asasp

oiler.

Theauto

motive

wingis

similar,

inte

rmsofstru

cture

,to

an

aircr

aft

wingasboth

pro

duce

lift

toitsstru

c-tu

re.

However

inauto

mobiles,

the

auto

motive

wing

pro

duce

snegative

lift

toact

as

adownforc

eto

help

keep

an

auto

mobilestability

when

opera

ting

athigh

speedsparticular

incu

rved

roadsand

turn

s.W

hen

auto

mobilesare

opera

ting

athigh

speedsand

go

into

sharp

turn

s,often

timesth

ey

enco

unte

rover-steering

and

may

lose

control.

With

thatin

mind

installing

the

wing

stru

cture

with

an

airfoil

thatpro

duce

sth

eneeded

negative

lift

and

also

doesn

tpro

duce

larg

edra

gis

crucialto

attain

high

aero

dynamic

chara

cteristics

forourapplica

tion.Thepre

sentwork

involvesru

nning

afluid

analysison

an

auto

motive

wingth

atwasdevelopedfrom

theNACA

63210airfoil.It

willbemounte

donth

eback

ofa

thre

edim

ensionalco

mpute

rsp

ortsca

rmodel.

This

modelwillbeuse

dto

pro

videre

alistic

airflow

chara

cteristicsto

thewingstru

cture

inth

eCFD

simulation.It

willalsoinvestigate

and

chara

cterize

showing

thee!ectsofth

edi!

ere

nttu

rnra

diusand

carsp

eed

on

thelift

genera

ted.Thro

ugh

this

analysisan

obse

rvation

willbemadeofth

eairflow

resp

onse

with

thesp

oilerand

solid

body

(car)

inte

rmsofperform

ance

chara

cteristicsdete

rmining

dif-

fere

ntangle

ofattack

with

di!

ere

nttu

rnsand

speed.Theobse

rved

willbemanipulate

dto

study

thee!ectsit

hason

aso

lid

body

(car).Thro

ugh

this

adevelopmentofasp

oilerca

nbemadeth

atwillpro

duce

thedesire

ddownforc

eto

pre

serv

eth

evehicle

stabilityin

turn

s.

1of1

AmericanInstituteofAeronauticsandAstronautics

Chara

cterization

ofEnerg

yDeposition

forDra

g

Reduction

MonaGolbabaeiAsl

Rutgers,

theState

University

ofNew

Jersey

Theobjectiveofth

ispre

senta

tionis

todescribedra

gmitigationin

supersonic

flightusing

energ

ydeposition

tech

nique.Overth

epast

severa

ldeca

des,

publicdemand

forsu

personic

transp

ortationhasre

ceivedsignifica

ntattention.There

searchin

this

are

ahasalw

aysbeen

challenged

by

e!ciency

,perform

ance

,and

environmenta

lissu

es.

High

dra

gis

oneofth

emajorpro

blemswhich

considera

bly

impact

the

e!ciency

insu

chflights.

Awave

dra

gis

genera

teddueto

existe

nce

ofsh

ock

wavesin

thesu

personic

flight.

Hence

,it

isvery

impor-

tantto

develop

an

e!cientmeth

od

tore

solveth

eadversee"ect

from

high

dra

g.

Energ

ydeposition

hasre

centlybeen

known

asaro

bust

meth

od

fordi"

ere

ntflow

controlpurp

ose

s.The

actuation

time

ofth

iste

chnique

isvirtu

ally

instanta

neousand

compara

ble

with

the

very

small

timescalesinvolved

inhigh

speed

flow.Energ

ydeposition

isach

ieved

thro

ugh

avariety

ofmeth

ods:

RF,electrica

l,micro

waveand/orlase

rdisch

arg

e.

Aplasm

are

gion

plasm

oid

isgenera

ted

upon

disch

arg

ein

the

flowfield

which

inte

racts

with

the

existing

shock

system

and

alters

flow

para

mete

rsre

sultingin

changesin

dra

gbehavior.

Depending

on

the

disch

arg

ety

pe

variousplasm

aco

nfigura

tionsca

nbe

create

d.

Experimenta

land

computa

tionalstudieshavebeen

perform

ed

toinvestigate

thee"ect

from

di"

ere

ntplasm

aco

nfigura

tions.

Saso

hetal.

perform

ed

experiments

tostudy

the

inte

raction

offocu

sed

lase

rpulsewith

shock

wave.Kandala

and

Candleruse

da

therm

o-chemicalmodelforair

tostudy

loca

llase

rdisch

arg

ein

supersonic

flow.

Sch

ulein

etal.

studied

the

e"ect

ofa

lase

rdisch

arg

ein

supersonic

flow

using

aperfect

gasmodel.

Lash

kov

etal.

perform

ed

experiments

toexamine

the

resu

ltofmicro

wave

disch

arg

eahead

ofsu

personic

AD

bod-

ies.

Knightetal.

haveperform

ed

computa

tionsfora

realgasmodelto

study

micro

wave

disch

arg

einte

raction

with

shock

wave.

Bro

vkin

etal.

(2006)im

plemente

dexperiments

tostudy

the

inte

raction

ofco

mbined

micro

wave

and

lase

rdisch

arg

ewith

flowfield.

This

rese

arch

focu

seson

computa

tionalch

ara

cteriza

tion

ofdra

gmodifica

tion

dueto

form

ation

ofan

instanta

neousplasm

asp

ike

genera

ted

by

combined

lase

rand

micro

wave

disch

arg

eahead

ofa

bluntcy

linderatM

ach

3.

Aperfect

gasmodeland

axisymmetric

flowfield

isassumed.Theperfect

gasassumption

helpssimulate

theplasm

asp

ikewith

ahigh

temper-

atu

refilament.

Ase

tofdim

ensionless

para

mete

rsis

defined

toinsp

ect

both

thefilament

length

and

tempera

ture

e"ect

on

dra

gcu

rve.Thehigh

tempera

ture

filamentis

introduce

dinstanta

neously

ahead

ofth

ecy

linder

inpre

sence

ofth

eexisting

bow

shock

.The

flow

conto

urs

pre

sentth

eform

ation

ofa

toro

idalvortex

behind

the

shock

upon

initiation

of

filamentinte

raction

with

the

bluntcy

linder.

The

circ

ulation

region

expandsasit

moves

o"

theaxis

and

reduce

sth

efronta

lpre

ssure

.There

sultsindicate

amaxim

um

momenta

rydra

gre

duction

of90

1of1

AmericanInstituteofAeronauticsandAstronautics

Reusable

ArchitectureforM

anned

MarsM

ission

RyanSchmidt,HongraeKim

,EricTran

United

StatesNavalAcadem

y

Eversince

theacc

omplish

mentofth

eApollo

lunarlandings,

thenextstep

forNASAs

mannedsp

ace

pro

gra

mhasbeenamissionto

Mars.Thoughth

eUnitedSta

tesgovern

ment

hasse

ta

goaldate

fora

manned

mission

launch

inth

e2030s,

eco

nomic

unce

rtainty

and

persiste

ntbudgetcu

tsmaketh

efinancialback

ingforsu

chamission

unce

rtain.There

fore

,co

ste!ectiveness,ormaxim

izingscientificre

turn

on

investment,

isofprimary

importance

inany

pote

ntialmission

design.

The

objective

ofth

isre

search

pro

ject

isto

investigate

the

benefits

ofa

multi-part

reusa

ble

mission

architecture

thatca

nsu

pport

multiple

manned

missionsto

Mars.

The

inte

ntbehind

this

e!ort

isto

ach

ieve

gre

ate

rscientific

retu

rnwith

many

missions,

each

individualonebeing

lowerin

cost

dueto

thelarg

erinitialinvestmenton

reusa

ble

infras-

tructure

.W

hile

the

tota

lco

stofth

ispro

gra

mmay

be

higher

than

one

base

daro

und

single-u

semission

architecture

,th

emuch

gre

ate

rre

turn

ofscientificknowledgewould

jus-

tify

thegre

ate

rexpense

.Thegro

undse

gmentwould

consist

ofEarthgro

undinfrastru

cture

and

C3infrastru

cture

.Thelaunch

segmentwould

beNASAsSpace

Launch

System

(SLS).

Thesp

ace

segmentwould

consist

offourre

usa

ble

parts:

apro

pulsion

module

fortransfer

tomars,aM

ars

landingmodule,aM

ars

surface

habitatmodule,andanEarth-M

ars

cycler

space

station.Each

part

would

beco

nstru

cted

and

stationed

initsappro

priate

place

prior

toth

efirstmanned

mission

launch

and

would

remain

there

afterth

ere

turn

ofth

efirst

crew

foruse

by

futu

remissions.

The

pre

senta

tion

willco

ver

the

conce

ptu

aldesign

ofth

eentire

mission

architecture

,from

thefirstlaunch

ofth

esu

pport

infrastru

cture

toth

ere

turn

ofth

efirstcr

ew

toEarth.

The

majority

ofre

search

tobe

done

willfocu

son

tech

nicalfeasibility

and

cost/benefit

analysis.

1of1

AmericanInstituteofAeronauticsandAstronautics

FlightTestingSenso

rsforRPAs

MarisaLockhart

JohnPaultheGreatCatholicHighSchool

Remote

lyPilote

dAircr

afts(R

PAs)

are

unmanned

airborn

emach

inesth

atare

use

dby

theUS

govern

mentand

military

tota

kepictu

res,

surv

ey

land,and

communicate

inform

a-

tion,re

cord

data

,and

oth

eruse

fulpurp

ose

s.Beca

use

ofth

eir

unique

abilities,

they

are

inhigh

demand

insu

rveillance

,co

mmunications,

and

weaponsdelivery

.However,

these

missionsca

nbeco

me

compro

mised

by

unexpected

weath

er.

With

every

mission

costing

millionsofdollars,every

lost

RPA

isvery

devastating

toth

epeople

who

opera

te,fly

and

invest

much

toth

eexpedition.Realtimeknowledgeofatm

osp

hericte

mpera

ture

and

rela-

tivehumidityca

nbeuse

dto

betterpre

pare

theco

ntrollerandpilots

ofth

eRPAsandenable

them

toavoid

dangero

usweath

erco

nditionssu

chasicing,tu

rbulence

,winds,

aco

usticsand

thundersto

rmactivity.

This

isbeca

use

knowing

thete

mpera

ture

and

relativehumidity

of

theatm

osp

here

can

pre

dictth

epre

sence

ofcloudsand

moistu

re.

Ase

nso

rwasdesigned

and

manufacture

dto

work

on

aRPA

and

measu

rete

mpera

ture

and

relative

humidity.

Ascientifica

lly

base

dflightte

stpro

gra

mhad

tobe

designed

toevaluate

these

nso

rforitsacc

ura

cyin

measu

ringre

lativehumidityandte

mpera

ture

.Since

no

RPA

wasavailable

forte

sting,a

suitable

altern

ativeaircr

aft

had

tobefound

toca

rry

outth

eairborn

ete

sts.

Asu

itable

civilian

lightairplane,Cessna340,wasmadeavailable

forth

ete

sting.This

airplanewasse

lected

base

don

itsnorm

alopera

tingweight,

speed,and

altitude,which

all

rese

mbledth

estandard

RPAs.

Themanufacture

dse

nso

rwasattach

edto

thefrontwindow

ofth

eaircr

aft

andflownin

ase

riesofflightmaneuvers

inHouston,Texasin

June2012.The

senso

rco

llected

there

adingsofte

mpera

ture

,re

lativehumidity,

and

GPS

and

transm

itte

dth

em

toan

on-b

oard

lapto

pco

mpute

r.Thedata

wasth

en

plotted

realtimeto

allow

the

test

crew

toevaluate

the

atm

osp

heric

conditionswhile

they

flew.

The

transm

itte

ddata

wasco

mpare

dto

NationalW

eath

erServ

iceweath

erballoon

data

from

thesa

meloca

tion

and

time.

These

nso

rwase!ectivein

readingte

mpera

ture

and

pre

ssure

on

thegro

und

and

inth

eair.

The

plotted

data

showed

thatth

ete

mpera

ture

sduring

flightch

anged

asexpected.

However,

thedata

acc

ura

cywassu

spicious.

There

adingsforte

mpera

ture

and

relativehu-

miditydid

notalw

aysmatchth

ere

adingsfrom

theNationalW

eath

erServ

iceoraircr

aft.It

isbelieved

thatth

emeta

lca

singofth

ese

nso

rco

llected

heatfrom

sunlightorinte

rnalelec-

tronicsand

sentco

nductiveheatth

rough

themeta

lsto

these

nso

rsslightly

compro

mising

these

nso

rse!ectiveness.

The

flightte

stssh

owed

thatth

ese

nso

rswere

overa

llsu

ccessfu

l,butre

quire

design

of

anew

and

di!

ere

ntca

sing

toeliminate

the

heatco

nta

mination

from

sunlightand

oth

er

sourc

es.

Furtherdesign

work

and

flightte

stswillth

en

benece

ssary

toach

ieveth

egoalof

usingase

nso

rto

measu

rete

mpera

ture

and

relativehumidity

from

aRPA.

Marisa

A.Lock

hart

Junior,

John

Paulth

eGre

atHigh

Sch

ool

1of1

AmericanInstituteofAeronauticsandAstronautics

Steady-S

tate

Compressible

Flow

ComputationalFluid

DynamicsAnalysisofTra

ilingEdgeHigh-L

iftDevices

Agastya

Parikh

Howard

HighSchool

The

purp

ose

ofth

isexperiment

was

toim

pro

ve

the

design

oftrailing-edge

high

lift

deviceson

theAirbusA330-300in

ord

erto

explore

feasible

waysto

impro

vefu

ele!ciency

on

midsize

aircr

aft.Experimenta

tion

wasco

nducted

thro

ugh

use

ofco

mputa

tionalsteady-

state

meth

odsin

ANSYSCFX,andpost-p

roce

ssinganalysiswasco

nductedin

AvizoW

ind.

Thedesignste

stedwere

thestandard

A330-300sy

stem,afu

ll-spansy

stem

derivedfrom

the

A330sy

stem,and

amodifica

tion

ofth

efu

ll-span

system.Themodels

create

dwere

tested

inta

keo"

and

landing

configura

tionsbase

don

Airbus-pro

vided

data

.The

data

obta

ined

wasanalyze

din

term

soflift,dra

g,and

L/D

ratio,and

wasth

en

post-p

roce

ssed

forvisual

analysis.

Thehypoth

esisstate

dth

atth

emodified

fullsp

an

system

would

perform

thebest

inboth

configura

tions.

Itwasnotsu

pportedbyth

edata

.Thestandard

wingperform

edth

ebest

inboth

takeo"

and

landingco

nditions,

pro

ducingL/D

ratiosof7.81998and

7.50963,

resp

ectively.

The

modified

fullsp

an

followed,genera

ting

7.23719

and

7.36081

asitsL/D

ratios.

The

fullsp

an

flap

perform

ed

worst,

with

L/D

ratiosof7.23627

and

7.31575.

The

standard

wingpro

duce

dth

ebest

perform

ance

byo"se

ttingitsdra

gpro

duction

su!ciently

with

lift

pro

duction.Themodified

fullsp

an

waslimited

severe

lyby

reduce

dwingare

a,as

itslack

oflift

pro

duction

wasth

eca

use

oflow

L/D

ratio.Thefu

llsp

an

flap

waslimited

by

dra

g,asitshigh

lift

pro

duction

led

tohigh

dra

gpro

duction.Theco

nclusion

thatca

nbe

dra

wnfrom

thedata

isth

atth

estandard

flapse

ctionre

pre

sents

thebest

designformidsize

aircr

aft.There

sultsofth

isexperimentwould

best

beapplied

inord

erto

impro

veth

efu

el

e!ciency

ofaircr

aft

duringta

keo"

and

landing.

1of1

AmericanInstituteofAeronauticsandAstronautics

Establish

ingCapabilitiesforParticle

Image

Velocim

etryofPlasm

aActu

ato

rFlow

Pattern

s

NicholasZarbo

University

ofMaryland

Plasm

aactuato

rsare

thin

sheets

ofwireth

an

can

induce

low

wind

speedsormainta

inattach

ed

flow

on

high

angle

ofattack

airfoils.

Plasm

asare

well

understo

od

on

amacr

o-

scopic

scale,butth

eflow

pro

pertiesinsideth

em

are

notwell

understo

od.Thegoalofth

ispro

ject

isto

establish

an

e!ective

Particle

Image

Velocimetry

(PIV

)se

tup

todete

rmine

velocity

vectors

thro

ughoutaplasm

aactuato

r.This

pre

senta

tion

deta

ilsth

einitialdesign

considera

tionsand

pre

liminary

stepsto

ward

scr

eatingate

stbed

forth

eexperiment.

Fur-

therdeta

ilis

pro

vided

on

the

challengesand

some

solutionsofth

edesign

pro

cess.

The

futu

restepsofth

epro

ject

are

described

and

pote

ntialexperiments

are

discu

ssed

aswell.

1of1

AmericanInstituteofAeronauticsandAstronautics

MLIE!ectiveness

Stu

dy

RegisVenti,JuanRodriguez

UMBC

Thee!ectiveemissivity

(*)ofmulti-layerinsu

lation

(MLI)

isdependenton

theoptica

l,th

erm

al,

and

physica

lpro

pertiesofth

eindividuallayers,which

comprise

MLI.

Therm

al

modeling

pra

ctice

ofsp

ace

born

eobjects

with

MLI

typically

use

sa

default

value

of*

base

don

pre

viousre

search,herita

ge,and

legacy

.A

math

solver

typically

constru

ctsa

radiation

coupling

using

this

*value

and

doesnotacc

ountforco

nductive

heattransfer.

This

pro

ject

focu

seson

thee!ect

of*

fordi!

ere

ntM

LIco

nfigura

tions.

Therm

alvacu

um

testing

ofa

therm

ally

isolate

dsh

eetmeta

lbox,re

pre

senta

tive

ofa

common

electro

nics

box

on

asp

ace

craft,wasco

mplete

dto

exemplify

the

a!ectsofM

LIco

nfigura

tion

on

its

e!ectiveness.TwoM

LIco

nfigura

tionswere

tested:1)form

fitted

and

2)te

nte

d.Thebox

utilize

dth

esa

meM

LIforeach

configura

tion

and

wasexpose

dto

thesa

meenvironmentof

-150C

(10C)and

5x

10-5

torr.Therm

alDesk

top

5.5

correlate

dte

stdata

toso

lveforth

e*.

Pro

viding

1W

ofpowerto

the

box,th

ere

sultsyield

an

*of0.036

forth

eform

fitted

case

and

an

*of0.021forth

ete

nte

dca

se.There

sultsindicate

thatate

nte

dco

nfigura

tion

ofM

LImay

pro

videbetterinsu

lation

than

form

fitting.Oth

erte

sted

powerse

ttingssh

ow

thatth

ere

isate

mpera

ture

dependence

of*,with

higherte

mpera

ture

syieldingalower*.

1of1

AmericanInstituteofAeronauticsandAstronautics

MM

SPro

pellantTankTherm

alCapacitanceM

odel

Stephen

McK

im,AmandaSteckel

NASA

TheM

agneto

sphericM

ultiSca

le(M

MS)M

ission

seeksto

understa

nd

how

theSunsand

Earthsmagneticfieldsinte

ract

thro

ugh

an

energ

eticphenomenon

called

magneticre

con-

nection.Tohelp

acc

omplish

this,aform

ation

of4sp

ace

craft,each

with

amonopro

pellant,

blow

down

pro

pulsion

system,willbeuse

dto

raiseth

eapogeeofeach

space

craft,enabling

scientiststo

study

magneticphenomena

atboth

thebow

shock

and

magneto

-tail

regions

aro

und

Earth.Acc

ura

teknowledgeofth

epro

pellantload

ineach

space

craft

iscr

iticalto

execu

teth

ismaneuver,

perform

station

keepingduringth

etw

o-yearmission,and

plan

for

end-of-life

disposa

l.This

pre

senta

tiondiscu

ssesath

erm

alca

pacita

nce

modelofth

eM

MSpro

pulsionsy

stem

pro

pellantta

nksth

atwascr

eate

dto

estim

ate

thepro

pellantload

on

thesp

ace

craft

near

end-of-life,a

phase

inth

emission

where

high-acc

ura

cyknowledge

ofth

ere

maining

pro

-pellantis

importantto

dete

rmineth

eend

ofscience

opera

tions.

Theth

erm

alca

pacita

nce

meth

od

isuniquein

thatth

eacc

ura

cyofth

epro

pellantestim

ate

incr

ease

sasth

eamount

ofpro

pellantin

theta

nk

decr

ease

s.This

contrastswith

thetraditionalpro

pellantgauging

meth

odsofbook

keeping

and

pre

ssure

-volume-tempera

ture

,which

are

more

acc

ura

teat

thebeginning-of-life

and

less

acc

ura

teatend-of-life.

The

therm

alca

pacita

nce

modelwascr

eate

dby

developing

adeta

iled,transientth

er-

malmodelofth

eM

MS

pro

pellantta

nk

using

the

ANSYS

finite

elementso

ftware

pack

-age.Boundary

conditionswere

obta

ined

from

theM

MS

therm

alte

amssp

ace

craft

therm

al

model.

Opera

tion

ofth

erm

ostatica

lly

controlled

heate

rs,th

eappro

xim

ate

shape

ofth

epro

pellantco

nta

ined

within

thediaphra

gm

tank,busvoltage,and

actualinte

gra

ted

heate

rre

sistance

swere

each

added

toth

eANSYS

model.

This

pro

pellant

gauging

tech

nique

was

initially

validate

dagainst

the

MM

Sth

erm

al

teamsindependentth

erm

alanalysisofth

eM

MS

pro

pulsion

system

and

tanks.

Pro

pellant

loadsof10,15,and

20

kilogra

mswere

simulate

din

the

modelto

pro

duce

tempera

ture

versustimecu

rvesbase

dupon

tempera

ture

data

.Thepre

senta

tion

willalsodiscu

ssfu

ture

work

tovalidate

themodelusingsp

ace

craft

therm

alvacu

um

test

data

,aswell

ase!ectsof

thesy

stemsinitialte

mpera

ture

and

time-vary

ingboundary

conditions.

1of1

AmericanInstituteofAeronauticsandAstronautics

Real-Tim

eEstim

ationofAircra

ftFrequencyResp

onses

JaredGrauer,EugeneMorelli

NASA

Langley

ResearchCen

ter

Frequency

resp

onse

sdescrib

eth

erelativemagnitudeand

phase

angle

steady-sta

tere-

sponse

ofadynamic

system

subjectto

harmonic

excitation.Frequencyresp

onse

sestim

ation

via

Welch’s

Meth

od

isoften

use

dforidentifying

aircraft

dynamic

models

from

measu

red

flight

data

for

severalreaso

ns.

For

instance,estim

ating

frequency

resp

onse

sis

anon-

parametric

technique

thatrequiresno

previousknowledge

ofth

efu

ndamenta

ldynamics,

e.g.from

aCFD

analysisorawind-tunnelte

st.Furth

ermore,linearmodels

resu

lt,which

facilitate

abroad

toolsetofstandard

stability

analysisand

controlsy

nth

esiste

chniques.

However,th

ere

are

severaldrawbacksto

this

approach.

Frequency

sweepsare

typically

use

dto

exciteth

eaircraft,andlongdata

recordsof90to

120se

condsperinputareneeded

forgoodresu

lts.

Thewindowingproceduresrequireth

eanalyst

tomakeengineeringju

dge-

ments

thatim

pactth

eresu

lts,

such

aswindow

length

,sh

ape,and

overlap.Finally,th

ere

isnodirectquantification

ofuncerta

inty

toqualify

theresu

lts.

This

work

prese

nts

anew

meth

od

forestim

ating

frequency

resp

onse

sand

their

uncer-

taintiesin

realtime.Previously

developed

orth

ogonalphase

-optimized

multi-sineexcita-

tionsareemployed

toexciteall

theaircraft

inputs

simultaneously,th

erebysh

orte

ningte

st

durations.

AFouriertransform

isuse

dto

thenconvertmeasu

rements

atth

eexcitationfre-

quenciesinto

thefrequencydomain,whereth

emagnitude,phase

angle,and

uncerta

inty

of

thefrequency

resp

onse

sareextracte

d.A

recursiveformulation

ofth

isprocess

and

adata

forgetting

algorithm

give

the

meth

od

areal-time

and

adaptive

capability.

This

meth

od

providesan

accurate

and

computa

tionally-e!cientmeth

od

ofestim

atingpote

ntially

time-

varyingfrequencyresp

onse

sand

their

uncerta

intiesusingrelatively

briefamounts

ofdata

.

This

meth

od

can

be

use

dto

identify

pote

ntially

time-varying

dynamicsmodels,sh

orte

n

wind

tunnelte

stdurations,

and

supply

first

orderstability

marginsforadaptivenonlinear

controlalgorithms.

1of1

AmericanInstituteofAeronauticsandAstronautics

Design

and

Manufactu

reofth

eCock

pit

and

Tra

nsm

ission

foraHuman

Powered

Helicopter

CodyKarcher

University

ofMaryland

This

prese

nta

tionwilldeta

ilth

eprocess

ofdesigningandmanufactu

ringth

ecockpit

and

transm

issionofth

eworld

recordse

ttingGameraII

humanpoweredhelicopte

r.Since2008,

Team

Gamera

atth

eUniversity

ofM

aryland

hasbeen

dedicate

dto

building

ahuman-

powered

helicopte

rcapable

ofattaining

theAmerican

Helicopte

rSociety

sSikorsk

yPrize.

To

claim

the

prize,th

ete

am

must

design

and

build

ahuman

powered

helicopte

rth

at

demonstrate

sasu

stained

duration

inhoverof60se

conds,

atso

mepointduringth

atflight

reachesanaltitudeof3mete

rs,

andstayswithin

a10mete

rby10mete

rboxforth

eentirety

ofth

eflight.

Currently,th

ete

am

hasbuilta

vehicle,Gamera

II,which

hasachieved

65

secondsofduration

inhoverand

inase

parate

flightreached

over9feetin

altitude.Atth

e

coreofth

isfeatofengineeringis

thecockpit

and

transm

ission.Thecockpit

ofGameraII

wasdesigned

toplaceth

epilotin

arecumbentposition

and

allow

him

orherto

pedalwith

both

handsand

feet.

Sinceth

epilotoutp

uts

energyin

acycle,th

ecockpit

wasdesigned

to

berigid

undercyclicloadingconditions,

whilestillbeinglightw

eight.

This

goalwasmetby

designingth

ecockpit

asan

assembly

oftw

o-d

imensionaland

three-d

imensionalcomposite

trusses.

Each

ofth

ese

truss

memberswasmanufactu

red

by

acontinuousfilamentwinding

process,allowingtrusseswithdozensofelements

tobeconstructe

din

atimely

fash

ion.The

transm

ission

ofGamera

IIwasdesigned

asa

two

stagesy

stem.

Thefirst

stageconsisted

ofth

epilotpedaling

inth

ecockpit.

Unlike

prior

human

powered

aircraft,th

epilotof

Gamera

IIuse

dboth

hand

cranksand

footpedals

topowerth

evehicle.

Aflywheelwas

also

included

into

this

phase

ofth

etransm

ission

ina

furth

ere!ortto

smooth

the

time

varying

poweroutp

utofth

epilot.

Inth

ese

cond

stage,a

pulley

atth

epilots

feetth

en

droveawinch

system

thatreels

instring

from

largerpulleyslocate

don

theroto

rblades.

Inboth

stages,

itwascritically

importa

ntto

cutweightwhilestillmainta

iningth

equality

ofth

eperformance

ofeach

component.

This

provided

many

unique

challenges,

which

included

thedevelopmentofa

chain

tensioning

system,th

emanufactu

ring

oflightw

eight

roto

rpulleys,

and

theoptimization

ofth

eflywheeldesign.

1of1

AmericanInstituteofAeronauticsandAstronautics

Lincoln

Labora

tory

RadarIn

troduction

ForStu

dent

Engineers

RaoulOuedraogo

MIT

Lincoln

Laboratory

TheM

ITLinco

lnLabora

tory

RadarIn

troduction

forStu

dentEngineers

(LLRIS

E)pro

-gra

mis

anew

two-w

eek,re

sidential,

pro

ject-b

ase

d,enrich

mentpro

gra

mwhich

wasco

n-

ducted

for

the

firsttime

during

July

2012

for

outsta

nding

students

from

New

England

who

are

ente

ring

their

senioryearofhigh

school.

Thegoalofth

epro

gra

mis

topro

mote

students

inte

rest

inscience

,te

chnology,

engineeringand

math

.Participatingstudents

gain

anin-d

epth

experience

inra

dararchitecture

,signalpro

cess-

ing,and

ora

lpre

senta

tion

thro

ugh

ase

riesofinte

ractivelecture

s.Stu

dents

are

challenged

tobuildalow-cost,2.4

GHz,

frequency

-modulate

dco

ntinuouswave(F

MCW

)Dopplerand

rangera

dar,

andto

demonstra

teitsfu

nctionality

usingcr

eativepro

blem-solvingstra

tegies.

This

hands-onpro

gra

mallowsstudents

towork

inastate

-of-th

e-art

labora

tory

withhighly

talente

dscientistsand

engineers.

Duringth

etw

o-w

eek

course,students

are

house

din

an

MIT

campusre

sidence

hall

and

pro

vided

with

transp

ortation

toLinco

lnLabora

tory

for

their

lecture

sand

radar

pro

to-

typing.

Instru

ction

ispro

vided

atM

ITLinco

lnLabora

tory

inLexingto

n,M

assach

use

tts,

by

Labora

tory

tech

nicalsta!

and

underg

raduate

and

gra

duate

students

from

MIT

.The

pro

gra

m,including

room

and

board

and

expense

sforth

epro

toty

pera

dars,is

freeto

all

participating

students.

Beca

use

ofth

esu

ccess

ofth

eLLRIS

Epro

gra

m,th

eLabora

tory

plansto

expand

thepoolofapplica

nts

tohigh

schoolstudents

acr

oss

thenation.Deta

ils

ofth

ese

lection

pro

cess

ofth

eparticipants,th

evariousco

urses,

the

architecture

ofth

eFM

CW

radar,

and

thefu

ture

ofth

epro

gra

mwillbepre

sente

d.

1of1

AmericanInstituteofAeronauticsandAstronautics

SuperconductingReso

nantlyCoupled

Wireless

Power

Tra

nsfer

Matthew

Marcus,Tim

Russell,RaymondSedwick

University

ofMaryland,CollegePark

Reso

nantinductivepowertransferhassh

ownpro

miseasameth

odofsu

pplyingelectrica

lpowerwirelessly

oversh

ort

dista

nce

s.Such

systemshavemanyapplica

tionsin

space

flight,

such

as

powering

lunar

rovers

from

are

mote

power

plant,

allowing

for

more

versatile

travel.

Reducing

losses,

such

as

those

due

toohmic

(resistive)

losses,

inth

einductive

coilsofth

ese

systemsca

nallow

forsignifica

ntlyhigherpowertransfer,

andgre

ate

rra

ngeof

powertransfer.

Pre

viouswork

use

daco

ilco

nstru

ctedwithsu

perc

onductingwirefabrica

ted

with

abismuth

stro

ntium

calcium

copperoxideco

re(1

G)in

theinductivepowertransfer

system.However,

this

typeofco

ilsh

owed

little

impro

vementoveraco

nventionalre

sistive

coil.

We

believe

this

isdue

toth

esk

ine!ect,which

cause

selectricity

totravelonly

along

theoute

rlayerofth

ewire,traveling

entire

lyth

rough

there

sistiveoute

rlayer,

and

bypassing

thesu

perc

onducting

core

.To

test

this

theory

,weare

developing

asy

stem

that

willutilize

aco

ilco

nstru

cted

ofa

new

type

ofsu

perc

onducting

wire

(2G),

inwhich

the

superc

onductinglayeris

close

toth

eoute

redgeofth

ewire.W

henco

mplete

,re

sultswillbe

compare

dwith

perform

ance

inform

ation

from

a1G

high

tempera

ture

superc

onductorco

iland

anon-superc

onducting

coil.This

talk

willpro

videan

overv

iew

ofre

sonantinductive

powersy

stemsand

there

late

dsp

ace

applica

tionsofth

iste

chnology,

and

theim

portance

ofre

ducing

lossesin

thesy

stemsinductiveco

ilin

ord

erto

impro

veperform

ance

.Then

itwilldiscu

ssth

edi!

ere

nce

betw

een

1G

and

2G

wire,highlighting

theanticipate

dbenefits

ofth

e2G

wire,and

describean

experimenta

lse

tup

thatwillbedeveloped

toco

mpare

the

perform

ance

ofa

system

using

aco

ilco

nstru

cted

from

1G

wire

toa

system

with

aco

ilusing2G

wire.

1of1

AmericanInstituteofAeronauticsandAstronautics

Investigation

on

WingFuselageofUnmanned

Mini-Air

Vehicle

usingSTAR-C

CM

+

Bharath

Madduri,Dr.ThundilKaruppaRaj

University

AtBu!alo

Micro

Air

Vehicles(M

AVs)

are

catchingmore

and

more

attention

forth

eir

applica

tions

incivilian

and

military

fields.

Unmanned

air

vehiclesin

the

same

class

are

exte

nsively

use

dforsu

rveillance

purp

ose

s.Demand

forhigh

altitude,low

cost,lightweightUM

AVsis

continuously

incr

easingfrom

variousse

ctors.Thelow

speed

and

thesm

all

asp

ect

ratio

of

wingsofth

ese

vehiclesgenera

teaparticularflow

regim

eth

atis

stillnotwell

understo

od.

Since

theth

eorieson

theaero

dynamicsoflow

Reynoldsnumberflowsare

yetto

beunder-

stood

and

wind

tunnelexperiments

cost

long

periodsand

gre

atexpense

s,th

enumerica

lsimulation

base

don

computa

tionalfluid

dynamics(C

FD)is

agood

appro

ach

toadopt.

This

investigation

focu

seson

theinte

rfere

nce

e!ectsth

atocc

uron

basicth

reety

pesof

Wing-F

use

lagegeometriesth

atare

considere

dsu

itable

foradesign

ofan

airplaneinte

nded

toopera

teatlow

subso

nic

speedsathigh

altitude.Thefollowingpaperwould

conce

ntrate

on

flow

chara

cteristicsacr

oss

di!

ere

ntwing-fuse

lagegeometriesofM

AV

thatwould

assist

indeveloping

aUM

AV

suitable

tomaneuverathigh

altitudes.

The

main

conce

ntration

would

bedealt

upon

on

Inte

rfere

nce

Dra

gacr

oss

thewing-fuse

lageinte

gra

tion’s

subjected

todi!

ere

ntpara

mete

rs.

Wing-F

use

lage

sizing

playsa

majorro

lein

designing

and

ispre

sente

din

deta

il.

Air-

foil

and

wing

analysisare

work

ed

inXFLR5

(Airfoil

Work

Bench

)th

atpro

duce

alm

ost

exact

resu

ltsforlow

Reynoldsnumberflightco

nditions.

CFD

(Sta

rCCM

+)simulations

usingvariousco

mputa

tionalmodels

are

inte

nsively

doneon

these

geometriesand

thebest

configura

tion

thatpro

duce

shigh

lift

among-stth

eentriesis

identified.

1of1

AmericanInstituteofAeronauticsandAstronautics

TheIm

plementation

ofVortexGenera

tors

forGro

und

Vehicles

Jose

Mondragon

University

ofMaryland,CollegePark

This

pre

senta

tion

willdescribeth

eim

plementa

tion

ofvortexgenera

tors

(VGs)

inord

er

tore

duce

pre

ssure

dra

gon

gro

und

vehicles.

So

far,

vortex

genera

tors

have

been

widely

use

don

aircr

aftsto

inhibit

flow

separa

tion

and

incr

ease

themaxim

um

lift

coe!cient.

On

the

oth

er

hand,when

VGs

are

implemente

dfor

cars,th

ey

willpro

vide

are

duction

on

pre

ssure

dra

g.

This

experimentis

conducted

inord

er

toco

ver

certain

factors

thatwillallow

us

todete

rmine

the

e"ectiveness

ofvortex

genera

tors.

These

factors

include

the

heightofth

eboundary

layer,

theangle

ofattack

with

there

spect

toth

eupco

mingflow

and

thenumber

ofVGsneeded

.Theheightofth

eboundary

layerwillpro

videinform

ation

on

how

farth

eVGswillbe

place

dfrom

the

frontofth

eca

r.In

addition

toth

at,

itwillenable

usto

dete

rmine

the

criticalloca

tion

where

the

VGsare

no

longere"ective

inord

erto

reduce

dra

g.Thech

angingangle

ofattack

isanoth

erim

portantexperimenta

lfactorth

atallowsus

tose

eth

edevelopmentofth

evortex

inth

einco

ming

flow.This

pro

videsqualita

tiveand

quantita

tiveinform

ation

on

how

thesize

ofth

ewakebehind

thevehicle

isa"ected.

The

numberofVGsneeded

isanoth

erco

nstra

inth

atneedsto

be

explore

d.

These

elements

ofth

eexperimentwilldete

rminehow

e"ectiveth

eVGsare

inaform

ation

and

how

those

form

ationssh

ould

be

arranged.

The

pre

liminary

resu

ltsfrom

this

experimentare

being

dete

rmined

thro

ugh

SolidW

ork

sFlow

Sim

ulation,in

ord

erto

eliminate

theleast

e"ective

configura

tions.

Afterw

ard

s,windtu

nnelte

stingwillbeco

nductedin

ord

erto

obta

invalida-

tionfrom

theflow

simulationdata

.In

additionto

that,

flow

visualiza

tionwillbeco

nducted

inord

erto

obse

rveth

evortex

form

ation

and

thesize

ofth

ewake.

With

theim

plementa

tion

ofth

evortexgenera

tors,it

isexpected

tore

duce

theamount

ofdra

gforc

eactingon

gro

und

vehicles.

1of1

AmericanInstituteofAeronauticsandAstronautics

Chara

cterization

ofBistable

TapeasaGravity

Gra

dientBoom

Jin

Kan

g,Joh

nKelly,Austin

Kelly,Ethan

Albrecht,ZacharyGri!tt

United

StatesNavalAcadem

y

One

ofth

emany

pro

blemsassociate

dwith

launch

ing

sate

llitesinto

orb

itis

orienting

these

nso

rsco

rrectly

with

theEarth.Past

pro

jectshavetried

tore

medy

this

pro

blem

by

installing

agra

vity

gra

dientboom

into

the

body

ofth

esa

tellite.

The

conce

ptbehind

agra

vity

gra

dientboom

isth

atonce

thesa

telliteexitsth

eEarthsatm

osp

here

,a

weighte

dboom

would

deploy

and

the

di!

ere

nce

sbetw

een

the

gra

vitationalstre

ngth

acting

on

the

mass

ofeach

side

ofth

eboom

would

orientth

esa

tellite

inre

lation

toth

ece

nte

rofth

eEarth.

Oth

er

universities,

such

asDre

xelUniversity,

use

da

tape

measu

reasa

gra

vity

gra

dientboom.

The

tape

measu

reboom,th

ough

e!ective

inorienting

the

sate

llite,had

many

faultsin

itsdesign.

The

deploymentofth

eta

pe

measu

reca

use

da

gre

atdealof

vibra

tion

and

shock

which

can

adversely

a!ect

the

sate

llite

components

and

opera

tion.

Additionally

theforc

eca

use

dby

thedeploymentofth

eboom

haspote

ntialto

damageth

ebody

ofth

esa

tellite.

Weinte

nd

tote

stabista

ble

tapepro

vided

tousby

Air

Forc

eRese

arch

Lab

(AFRL)as

amore

e!ectivegra

vity

gra

dientboom.Thebista

ble

tapein

contrast

toth

eavera

geta

pe

measu

reis

both

stable

inth

erigid

deployedstageandth

estowedstage.Ourstudyinte

nds

toch

ara

cterize

thedeploymentofth

ebista

ble

tapebymeasu

ringth

eforc

e,vibra

tions,

and

acc

elera

tion

ofth

eta

pesdeploymentand

toestablish

asy

stem

todampen

these

e!ects

on

thesa

tellite.In

ord

erto

dampen

theforc

eand

vibra

tion

cause

dby

thebista

ble

tapes

deployment,

weinte

nd

toattach

an

80gcy

linderfilled

with

asp

ecificliquid.This

demon-

stra

tion

willsh

ow

thedeploymentofth

ebista

ble

gra

vity

gra

dientboom

and

ourmeth

od

ofdampeningth

eforc

edueto

itsdeployment.

1of1

AmericanInstituteofAeronauticsandAstronautics

Mappingfrom

theUnmanned

Vehicle

GabrielLadd

AdvancedConcepts

Consulting

Mapping

from

any

aircraft

ischallenging

tostartwith.M

apping

from

aUAS

bring

a

uniquese

tofproblems.

Tocreate

agood

unmanned

mappingsy

stem

you

haveto

consider

manytradeo!s.

Thechiefconstraintafterweightandpoweris

data

application.This

make

theta

skofageosp

atialengineerin

aremote

sensingcompanyis

tobridgeth

egap

betw

een

application

and

hardware.

Itis

the

translation

betw

een

needsofpeople

who

may

know

noth

ing

ofaircraft

and

engineerswho

need

deta

iled

specificationsfora

very

constrained

world.This

talk

willcoverso

meofth

eessentials

thingsto

think

aboutwhen

designing

a

UAS

mappingsy

stem.

1of1

AmericanInstituteofAeronauticsandAstronautics

FreeFlightTestingTech

niqueforAvianScale

Flapping

WingUn-m

anned

Air

Vehicle

Aim

yW

issa

,Jared

Grauer

,NelsonGuerreiro,Yashwan

thTummala,

Cornelia

Altenbuchner,Dr.

Jam

esHubbardJr.

,Dr.

MaryFrecker

University

ofMaryland

Unmanned

AerialVehicles(U

AVs)

are

pro

lifera

tingin

both

thecivil

and

military

mar-

kets.

Flapping

wing

UAVsororn

ithopte

rshaveth

epote

ntialto

combineth

eagility

and

maneuvera

bilityofro

tary

wingaircr

aft

withexce

llentperform

ance

inlow

Reynoldsnumber

flightre

gim

es.

These

traitspro

miseoptimized

perform

ance

overmultiple

mission

scenar-

ios.

The

objective

ofth

ispre

senta

tion

isto

pre

senta

novelfree

flightte

sting

tech

nique

foravian

scale

flappingwingun-m

anned

air

vehicles.

Theflightte

stto

ok

place

atW

right

Patterson

Air

Forc

eBase

inth

eAir

Forc

eRese

arch

Labora

tory

MAV

indoorflightfacility.

This

facility

conta

insth

elarg

est

Vicon

motion

track

ing

facility

inth

eU.S.A

and

maybe

theworld.53Reflectivetrack

ingmark

ers

were

place

don

theorn

ithopte

r’swings,

tail

and

fuse

lage.

The

orn

ithopte

rwashung

from

ate

ther

and

wasflown

diagonally

acr

oss

the

room.

The

x,y

and

zpositionsofth

ese

53

mark

ers

were

track

ed

and

post

pro

cessed

togive

deta

iled

time

histo

ryforth

eorn

ithopte

r’skinematics

and

dynamics.

Variouswings

configura

tionswere

tested

during

theafore

mentioned

flightte

steach

formultiple

flights.

Resu

ltspre

sente

dsh

owsth

atfreeflightwasindeed

ach

ieved

forall

thete

sted

wing

con-

figura

tions.

Alsoth

ete

stdata

show

thatacc

ura

temark

ertrack

ing

wasach

ieved

and

that

consistentand

repeata

ble

kinematics

were

obta

ined,th

usabro

ad

spectru

mofhigh

fidelity

flightdata

isnow

readilyavailable

forfu

ture

modeling.This

flightte

stse

tsnew

pre

cedent,

asit

washeld

inth

elarg

est

indoorflightfacility

inth

eU.S.A

.M

ore

over,

theorn

ithopte

rth

atflew

during

this

test

wasth

elarg

est

flapping

wing

vehicle

tobe

everte

sted

inth

isfacility

and

itca

rried

themost

numberoftrack

ingmark

ers.

1of1

AmericanInstituteofAeronauticsandAstronautics

ACommonExplora

tionArchitectu

reforth

eDetection

ofLifein

theSolarSystem

MarioChris,ColinHow

ard,Michael

Starr,VictorTrofimov,James

James

Xavier

HighSchool,AvonHighSchool,GreaterHartford

Academ

yofMath

andScien

ce

Inconsidering

the

search

for

extrate

rrestriallife

asone

ofth

eprim

ary

objectivesof

conducting

inte

rplaneta

ry

spaceexploration,many

planets

and

corresp

onding

moonscan

be

cate

gorized

asfeasible

environments

forlife.

Inparticular,M

ars,

and

the

icy

moons

ofJupiter

and

Satu

rn,are

worth

examining.

The

moonsofmost

inte

rest

toth

escien-

tificcommunity

and

specifically

addressed

inourrese

arch

areEuropa,Titan,Enceladus,

Ganymede,andCallisto

.W

hendesigninganoverarchingframeworkforane!cientpilote

d

spaceexploration

program

tostudyth

eaforementioned

regionsofinte

rest,it

isim

porta

nt

tota

ke

into

accountsp

acecraft

components

and

maneuversaswell

asmission

scenarios

once

adestination

ischose

n.

Some

asp

ects

ofth

emission

trajecto

ry

thatare

evaluate

d

include

the

usa

ge

ofa

trailing

toroidalballute

toslow

the

spacecraft

and

decrease

con-

vectiveheatingaswell

asaerocaptu

remaneuvers.

Hohmann

transfersand

therecognition

ofcorridor

width

when

landing

are

also

explored

asuniform

frameworksfor

trajecto

ry

calculations.

Inte

rmsofpropulsion,abim

odalnuclearth

ermalrocketis

propose

dasth

e

most

practicable

solution.Thepurpose

ofth

ebim

odalrocketis

tomaxim

izee!ciency

by

utilizing

thenuclearth

ermalpowerplantasa

sourceofboth

high

thrust

and

low

thrust

propulsion

via

atraditionalnuclear

rocketand

aXenon

Ion

thruster

resp

ectively.

The

nuclearreacto

ris

tobe

constructe

dso

thatth

epoweroutp

utcan

be

modified

betw

een

thetw

oformsofpropulsion,aswell

asto

providepowerforth

emiscellaneousneedsofth

e

crew

and

spacecraft.Additionalfu

elis

tobegath

ered

atth

edestination

site

via

theuse

ofin-situ

propellantcreate

dfrom

the

reso

urcesavailable.

Inorderto

ensu

re

the

pilots’

safety,riskfacto

rswillbeaddressedbymeansofachievingartificialgravitywhennecessary

and

radiation

prote

ction.

According

toth

einte

nsity

ofth

eradiation

area,variousmod-

ulesto

bringth

eastronauts

toth

edestinationandbacke"ectively

areconsidered.M

ission

scenariosarealsoexaminedwithcombinationsoffeatu

ressu

chashabitat-hopping,icepen-

etrating

cryobots,and

surface

sample

collection.

Itis

explored

how

coordinate

drobotic

exploration

can

most

e"ectively

precedepilote

dmissionsand

establish

abase

ofinforma-

tion.Thesu

rfacecollection

reflects

ase

arch

forlife

and

reso

urceson

thedestination

and

a

common

instrumenta

tion

and

collection

framework

isexplored.Forpilote

dmissions,

the

conceptofhabitat-hopping

considersth

eestablish

mentofvarioushabitats

on

thesu

rface

ofth

edestination

which

would

serve

astransitionalpoints

fora

traveling

mission

team.

The

variousmeth

odsexplored

share

the

common

purpose

ofincreasing

the

e!ciency

of

the

mission

and

allow

for

amaxim

um

exploration

area.

An

asp

ectofth

emission

also

discussed

isth

euse

ofth

eflightcraft

on

unmanned

missionsasa

reconnaissa

nceorbiter,

vastly

increasingth

einformationgath

eringlifetimebeyondth

atofso

lely

thesu

rfaceexplo-

ration

and

reducing

mass

waste.This

iscomplemente

dby

variousoth

erinstrumenta

tion

tobeleft

on

ornearth

esu

rfaceafterth

ecompletion

ofth

eprim

ary

objectiveswhich

will

transm

itvariousinformation

toearth

via

thecommunication

infrastructu

recreate

dbyth

e

initialmission.Overall,by

employingth

ese

innovative,yetviable

design

attribute

sin

lieu

ofth

econventionalmeth

odscurrently

employed

by

unmanned

spacecraft,th

eth

orough

design

and

exploration

structu

recreate

dwillallow

thescientificobjectivesoffu

turesp

ace

exploration

missionsto

bebeoptimally

achieved

and

thepossibility

ofextrate

rrestriallife

tobemorefu

lly

tested.

Theauth

orswould

liketo

acknowledgeth

esu

pportofProfessorBriceCassenti

and

the

University

ofConnecticutforth

eir

help

inth

epreparation

ofth

ispaper.

1of1

AmericanInstituteofAeronauticsandAstronautics

ACommonExplora

tionArchitectu

reforth

eDetection

ofLifein

theSolarSystem:Tra

jecto

ryCalculations

and

theJupiterSystem

MarioChris

Xavier

HighSchool

Essentialto

the

planning

ofany

space

mission

isth

eprocess

ofcalculating

required

velocitiesandtrip

times,

andresu

ltantmass

ratios,

ofth

edesiredtrajecto

rybetw

eenEarth

and

the

inte

nded

destination.

These

necessary

calculationswere

conducte

dto

design

a

frameworkforasp

acemission

toanyofth

ese

veralplanets

and

moonsin

theSolarSystem

thatmay

be

capable

ofsu

staining

life.

Jupiterand

itsmoons,

Europa,Ganymede,and

Callisto

,are

among

the

most

plausible

environments

for

life.

However,when

planning

apilote

dmission

toJupiter,th

eharmfu

lradiation

field

wasa

major

concern

thatwas

addressed,asit

isim

porta

ntto

take

note

ofany

risksto

the

crew’s

health.

Inaddition,

scenarioswereconsidered

such

thatoneofth

emoons,

preferably

safe

tohumans,

may

be

use

dasabase

tocontrolinvestigationofth

eoth

ertw

omoons.

TheenvironmentofJupiter

and

itsmoonswerealsostudied

foradiscussion

ofpossible

utilization

forlife

supportand

in-situ

propellant.

Taken

asa

whole,th

ese

examinationsofpossibilitiesoffu

turepilote

d

missionsto

Jupiterand

itsicymoons,

alongwith

calculationsforcorresp

ondingtrajecto

ry

requirements,may

provebeneficialin

these

arch

forextrate

rrestriallife.

1of1

AmericanInstituteofAeronauticsandAstronautics

ACommonExplora

tionArchitectu

reforth

eDetection

ofLifein

theSolarSystem:M

ission

toth

eJovian

Icy

Moons,

Euro

paand

Enceladus

Michael,ColinStarr,How

ard

AvonHighSchool,GreaterHartford

Academ

yofMath

andScien

ce

Acr

ucialasp

ect

ofanymissionis

theexplora

tionofth

edestinationplanetormoon.On

thesu

rface

ofth

eJovian

IcyM

oons,

theprimary

objectiveis

todete

rmineth

eexiste

nce

of

an

underg

round

oce

an,itsexte

nt,

and

itspote

ntialforth

edevelopmentofpast,pre

sent,

orfu

ture

exta

ntextrate

rrestriallife.

On

Euro

pa,scientificanalysishasdete

rmined

that

there

islikely

tobean

enorm

ousliquid

seaunderro

ughly

10milesofice.W

hilepre

vious

investigation

ofEnce

ladushasbeen

less

conclusive,and

the

moon

ismuch

smallerth

an

itsco

usin,th

epre

sense

oficegeyse

rslikewiseindicate

sacr

yolayerto

somedegre

eactive.

On

both

Euro

paand

Ence

ladus,

icemelting

cryobots

should

beuse

dto

melt

thro

ugh

the

froze

ncr

ust

andre

ach

thewate

rundern

eath

.Powerforth

ese

devicessh

ould

comefrom

on

board

nuclearre

actors

and

thepro

duction

ofin-situ

pro

pellant(themost

feasible

option

ishydro

gen

and

oxygen

from

ice).

The

explora

tion,both

unmanned

and

manned,oficy

moonswillbea

long

term

endeavor,

and

willinvolvemultiple

obse

rvationalto

ols

from

ase

lection

ofth

seavailable.M

issionsto

both

Euro

paand

Ence

laduswillleavemultiple

base

modulesandre

connaissa

nce

orb

iters

thatwillco

ntinuepro

vidinginform

ationanddata

over

alongperiod

oftime.This

willse

rveto

best

pre

pare

forapossible

manned

mission

inth

efu

ture

.Ofall

thebodiesin

theso

larsy

stem,th

eicy

moonsofJupiterpro

videth

ehighest

pro

babilityoflife,butare

stillte

nsofyears

away,

and

thussh

ould

beth

oro

ughly

explore

dsa

fely

priorto

any

manned

mission.

*NOTE:This

isth

eth

ird

offourpre

senta

tionsby

HS

students

mento

red

by

Pro

fessor

Brice

Cassenti

ofth

eUniversity

ofConnecticut.

1of1

AmericanInstituteofAeronauticsandAstronautics

GPGPU

implementation

and

bench

mark

ingofth

e

unsteadyvortexlatticemeth

od

Christopher

Chabalko,BalakumarBalachandran

University

ofMaryland

Theunsteady

vorte

xlatticemeth

od

iswidely

known

foraccuracy

undercerta

incondi-

tionsand

robustness

inmodeling

theaerodynamicsofdi!

erentbodiesincluding

flapping

systemsin

unsteady

flows.

Thecomputa

tionalsu

broutinesin

this

formulation

can

beex-

pressed

aslinearalgebra

base

droutines.

Whilelinearalgebra

may

bea

convenientform

ofnota

tion,th

ememoryrequirements

aredetrim

enta

lto

computa

tionalperformance.Ex-

pressingth

eroutinesasnested

forloopsmitigate

sunnecessarymemoryaccess

whilemain-

tainingfidelity

inth

ecalculations.

Twodi!

erentim

plementa

tionsofasu

broutineuse

din

thevorte

xlatticecalculationsareconsidered.Oneis

aM

atlabim

plementa

tionwhichta

kes

advanta

geofvecto

roperations,

and

theoth

eris

an

implementa

tion

nVidiasCUDA

frame-

work.Thetw

oim

plementa

tionsarevalidate

dandcomparedin

benchmarkingapplications.

Asanexample

applicationconsiderth

einfluenceofanundulatinggroundonanairfoilata

fixed

angle

ofattackin

an

unsteadysy

stem.Thelargesp

an

bodyreprese

ntingth

eground

requiresa

high

levelofcomputa

tion,and

asignificantincrease

incomputa

tionalsp

eed

is

expecte

din

theCUDA

implementa

tion.

1of1

AmericanInstituteofAeronauticsandAstronautics

ACommonExplora

tionArchitectu

reforth

eDetection

ofLifein

theSolarSystem

Segment4:Piloted

Explora

tion

toTitan

and

Mars

Victor,James

Trofimov,Wang

GreaterHartford

Academ

yofMath

andScien

ce

The

identification

ofplanets

and

moonswithin

ourso

larsy

stem

asconta

ining

life

or

beingcapable

ofsu

pportinghuman

life

hasbecomeparticularly

importantaswebegin

toask

keyquestionsaboutth

ecapabilityoflife.In

particular,

Mars

and

Titan

o!erinte

rest-

ing

case

studiesofpossible

life-conta

ining

environments.Thedesigning

ofan

overa

rching

framework

forapilote

dmission

toth

ese

planets,among

oth

ers,could

facilitate

spaceex-

plora

tionofth

ere

gion.It

isim

portantto

takeinto

accountdi!

ere

ncesin

these

twoplanets

and

the

arising

di!

ere

ncesin

design

faced

by

each

,and

recognize

similaritiesth

atcould

resu

ltin

asp

ects

being

developed

thatcould

beuse

dto

travelto

both

destinations.

Such

asp

ects

ofth

emission

include

aero

captu

re,bim

odalnuclear

therm

alro

cketpro

pulsion,

multiple

habitation

modules,

in-situ

pro

pellantpro

duction,and

long-rangebuggies.

Some

asp

ects

ofth

emission

willhaveto

beta

ilore

dto

each

destination.Among

these

are

des-

tination

selection,investigation

and

access,and

post-retu

rndata

collection.In

Titan,th

epossible

investigation

are

aswillhave

tobe

keptopen,asth

ere

are

partsofTitan

whose

surfaceis

notwell-d

ocumente

d,work

thatwillbedoneon

themission.Points

ofinte

rest

includeth

enorthern

hemisphere

,which

conta

insmany

hydro

-carb

on

lakes,

someofwhich

seem

tohavech

anged

sizesoverth

eyears.In

addition,th

eso

uth

ern

hemisphere

ofTitan

sportsaperm

anenthurricane,which

would

beofprimemete

oro

logicalinte

rest.Further-

more

,se

ismologicaland

geologicalinvestigationssh

ould

beta

ken

on

Sinlap

Cra

ter,

oneof

thefourconfirm

edim

pactcra

ters

ofTitan.This

considera

ble

bre

adth

ofinvestigationsite

scallsforth

epro

duction

ofnumero

ushabitats

and

cre

wtransp

ortation

vehiclesto

shuttle

thecre

wfrom

destination

todestination.Anoth

erfeatu

reofTitan

underinvestigation

isitsmete

oro

logicalactivity.Forth

ispurp

ose

,aswell

asto

documentth

esu

rfaceofTitan

and

changesth

ere

of,

itwould

bebeneficialto

mainta

inpro

besin

orb

itaro

und

Titan

and

on

lander

site

safter

mission

completion.

Mars

exhibitsth

ebest

explora

tory

targ

etfor

pilote

dsp

aceexplora

tionin

thenearfu

ture

.Theprimary

objectiveforapilote

dM

ars

mis-

sion

isto

search

forsignsoflife

on

theplanetutilizinghuman

analytical-capabilities.

The

rationale

forse

nding

humansinto

space,asoppose

dto

robots,is

simply

because

humans

can

accomplish

more

than

any

robotcan.

Robots

have

been

continuously

exploring

and

monitoringth

eplanetforth

elast

few

decades,

soth

enextlogicalstep

isforhumansto

be

sentto

Mars.Themission

toM

ars

isdesigned

inaway

thatastro

nauts

willhaveenough

time

toe!ectively

explore

avast

range

ofth

eplanet.

Itis

expensive

tose

nd

astro

nauts

into

spaceand

bringth

em

back

,th

usit

isvitalto

utilizeasmuch

outofonetrip

toM

ars

aspossible.An

explora

tion

ofM

ars

willincludeastudy

ofth

egeologicaland

atm

osp

heric

conditionsofdi!

ere

ntre

gions,

and

most

importantly,heavy

sample

collecting

forfu

rther

analysisupon

there

turn

toEarth.

Thekey

toth

esu

ccess

ofa

Mars

mission

involving

along-term

stay

and

vast

explora

tion

are

ais

theuse

ofnumero

ushabitatmodules.

*NOTE:This

isth

elast

offourpre

senta

tionsby

HS

students

mento

red

by

Pro

fessor

BriceCassenti

ofth

eUniversity

ofConnecticut.

1of1

AmericanInstituteofAeronauticsandAstronautics

Low-E

arth

Orb

itReliabilityand

Maintainability

Para

digmsand

Their

Application

toDeep-S

pace

Explora

tion

Mariel

Rico,Melissa

Flores

TheGeorgeWashingtonUniversity

AsNASA

developsmore

inte

rest

inDeep-S

pace

(DS)explora

tion,th

ere

are

avariety

of

Reliability,

Mainta

inability,

and

Supportability(R

MS)co

nce

rnsth

atneed

tobeaddre

ssed

tolowerth

erisk

sofloss

ofcr

ew

orloss

ofmission.Low-E

arthOrb

it(L

EO)RM

Spara

digms

are

no

longer

valid

beca

use

ofth

enatu

reofDS

missions.

Environmenta

lfactors

that

need

tobe

acc

ounte

dforinclude

elongate

dtime

periodsin

space

and

gre

ate

rdista

nce

sfrom

the

Earth.

Aco

mpre

hensive

rese

arch

e!ort

hasbeen

putforw

ard

toidentify

RM

Spra

cticesfrom

past

space

flightpro

gra

ms,

and

then

re-evaluate

and

apply

them

into

DS

explora

tion

craft

design

and

pro

cesses.

Thedesign

considera

tionsinvestigate

dincludeth

ero

leofmanagementin

thedesign

pro

cess,overa

llhard

ware

considera

tions,

and

thee!ect

ofhumanfactors

onaDScr

aft.Primary

conclusionsmadeincludedesigningRM

Ssu

pport

along

side

the

space

craft

design

toim

pro

ve

e"ciency

,re

ducing

specialize

dco

mponents

and

tools

tocr

eate

redundancy

,and

designing

hard

ware

toenable

planned

mainte

nance

over

unplanned

mainte

nance

.This

inform

ation

willhelp

space

craft

designers

prioritize

subsy

stemsfordesign

and

mainte

nance

,which

decr

ease

sth

elikelihood

offailure

s.

1of1

AmericanInstituteofAeronauticsandAstronautics

Linco

lnIn

itiativeforThermalLinks(L

ITL)

RonEfromson,AllisonMoore

MIT

Lincoln

Laboratory

Meta

lfoil

stra

psare

currently

use

dto

pro

videstru

ctura

lly

deco

upled

heatco

nduction

path

sin

aero

space

payloads.

The

mass

ofco

pper

or

aluminum

foil

stra

ps

required

tomeetincr

easingheatdissipation

demandshasdesign

engineers

lookingforim

pro

ved

ther-

malmanagementso

lutions.

New,advance

d,lightw

eightmate

rials

can

pro

videmech

anical

flexibility

and

higher

heat

transfer

perform

ance

.M

anufacture

rsofKapto

nand

copper

enca

psu

late

dannealed

pyro

lyticgra

phite(A

PG)stra

pshavepro

mised

conductivity

thre

etimesth

atofco

pperwithaquarterofth

edensity.Heatpip

eswithflexible

bellowsse

ctions

pro

misesimilarbenefits.Thegoalofth

ispaperis

toch

ara

cterize

theth

erm

alre

sistance

and

mech

anicalsti!

ness

ofth

ese

advance

dso

lutions,

compare

them

tomanufacture

rsclaim

s,and

tote

chnologiescu

rrentlyuse

din

designs.

Itwasfound

thatth

eco

nfigura

tionsofAPG

stra

pand

flexible

heatpip

ete

sted

perform

ed

betterth

erm

ally

butare

up

toan

ord

erof

magnitudesti!

erth

an

copperfoil

heatstra

ps.

Ifdesignsca

nto

lera

teso

mesti!

ness,it

isre

commended

thatAPG

stra

psand

flexible

heatpip

esbeco

nsidere

d.

1of1

AmericanInstituteofAeronauticsandAstronautics

Reconstru

ctingth

eF4-U

CorsairsEngineM

ountusing

Modern

Tech

nology

Helen

Zhao,ZhangLiu,Ben

Staniewicz,

ThomasMeehan,MingZhao

AmityRegionalHighSchool

TheChance-V

oughtF4U

Corsa

ir,th

eo!cialstate

aircraft

ofConnecticut,

iscurrently

beingrestoredbyConnecticutCorsa

ir,avolunte

erorganizationdedicate

dto

educatinghigh

schoolstudents

inmath

,science,engineering,andte

chnology.Theobjectiveofth

isproject

isto

use

modern

mate

rialformsto

design

and

restore

the

Corsa

irsengine

mount.

The

website

CT

iHubwasuse

dto

communicate

withSikorsk

yengineersactingasmento

rsonth

e

project.

Toconstructath

reedim

ensionalmodel,aso

ftwareprogram

calledSolidW

orkswas

implemente

d.First,th

erequirements

thatneededto

beadheredto

beforeconstructingth

e

mount,

includingFAA

requirements

and

specificationslaid

outin

thechallengestate

ment,

such

aste

mperatu

rerequirements

and

ultim

ate

load

specificationswererese

arched.After

thatweanalyzed

theoriginalschematicsofth

eenginemountand

theactu

almounts

itse

lf

tomeasu

re,whichwasinputto

SolidW

orks.

Afterrese

archingdi"

erentdesigningmeth

ods,

an

alternativedesign

wasproduced

toim

proveth

eload

distribution

ofth

estructu

re.

In

addition,th

emate

rialwasupdate

dfrom

steel4130

tosteel4340,which

isstrongerand

moreresistantto

fatigue.

1of1

AmericanInstituteofAeronauticsandAstronautics

Accelera

tingth

eair

transp

ortation

systems

transform

ation:asy

stemsengineering,sy

stems

thinkingand

complexitysciencebased

rational

framework

tounifyhereto

fore

disso

ciated

linesof

inquiry

Liviu

Nedelescu

CrownConsulting

Ifth

enextgenera

tion

air

transp

ortation

system

(NextG

en)had

tobech

ara

cterize

din

only

twoword

s,th

elikely

candidate

swould

besy

stemsandco

mplexity.

Whilesy

stemsare

genera

lly

overt

and

explicit,

complexity

isan

implicitpro

perty

ofadvance

dsy

stems.

To

date

systemsare

unquestionably

betterundersto

odth

anco

mplexity,

forwhichaco

mmonly

agre

ed

definition

stilllack

s.Even

so,th

ere

isa

gro

wing

body

ofknowledgeaim

ed

atun-

dersta

ndingand

managingboth

.This

paperpro

pose

sanovelpara

digm

atth

einte

rsection

ofsy

stemsandco

mplexityforacc

elera

tingth

edevelopmentofadvance

dairsp

ace

conce

pts.

Thro

ugh

the

lensofth

epro

pose

dSystemic-O

pera

tional-Phenomenological(S

OP)frame-

work

,end

state

system

traitsare

identified

from

initialco

nce

ptdefinition

phase

s,which

pro

videsinsightinto

thesy

stem

complexity.

TheSOP

meth

odologyaim

sto

reco

ncile

thre

eofth

edisciplinesnece

ssary

and

likely

su!cientforundersta

nding

systemsth

atare

com-

plex:sy

stemsengineering,sy

stemsth

inkingand

complexityscience

.Ofth

eth

ree,sy

stems

engineeringhashad

thebest

reco

rdandhighest

acc

epta

nce

withth

eair

tra!cco

mmunity.

SOP

assertsth

eopera

tionalperspectivehasto

beexpanded

toca

ptu

resy

stemic

traitsand

complexity.

SOP

isdefined

inte

rmsofth

reedisciplinesth

us:

Thesy

stemic

perspective

refers

tosy

stemic

implica

tionsofopera

tionalmech

anismsasgleaned

thro

ugh

theapplica

-tion

ofsy

stemsth

inking;

The

traditionalopera

tionalperspective

remainsth

edominant

conce

ptdefinition

space

with

systems

engineering

as

the

pre

vailing

meth

odology;

The

phenomenologicalperspective,usingco

mplexity

science

,aim

sto

unco

verundesira

ble

con-

tentin

thegeneticmake-u

pofopera

tionalmech

anisms.

Theback

gro

und

section

pro

vides

theore

tica

lco

nsidera

tionsasnece

ssary

conte

xt.

The

subse

quentse

ctionspro

vide

aSOP

definition

developed

from

applica

tion

tose

vera

lNextG

en

conce

pts

and

one

opera

tional

conce

ptcu

rrently

inuse

.SOP

isth

en

use

dasath

eore

tica

lappro

ach

tounify

appare

ntly

orthogonalface

tsofth

eNextG

en

challenge:

rese

arch,modeling

and

simulation,sa

fety,

metrics.

Finally

aco

nstru

ctforair

tra!conto

logy

ispro

pose

d.

1of1

AmericanInstituteofAeronauticsandAstronautics

ExperimentalCalculation

ofAero

dynamic

Forceson

a

FlappingRigid

Wing

David

Coleman

University

ofMaryland,CollegePark,MD

Since

thedevelopmentofth

efirstairplane,fixed-w

ingsandro

tary

-wingshavebeenuse

don

mostly

all

conventionalaircr

aft

togenera

teth

ere

quired

lift.However,

this

isnotth

emech

anism

thatbiologicalorg

anismssu

chasbirdsand

inse

cts,

use

tofly;instead,th

ey

utilize

repeate

dflapping

ofa

pair

oflight-weight,

flexible

wingsto

genera

teth

ere

quired

lift

and

pro

pulsiveforc

es.

The

question

we

are

trying

toansw

er

inth

isre

search

iswhat

advanta

ges

does

the

flapping

wing

ofan

inse

ctor

bird

have

over

the

fixed

or

rota

ting

wings

ofman-m

ade

airplanesand

helico

pte

rs?

Answ

eringth

isquestion

involvesre

plica

tingth

eflappingwings

ofbirdsand

inse

cts,

and

experimenta

llymeasu

ringth

eaero

dynamic

forc

esoflift

and

dra

gth

atare

genera

ted

asth

ewingflapsforw

ard

and

back

thro

ugh

theair.

To

imitate

this

flapping

wing

conce

pt,

aplanar,

rigid

carb

on

fiberwing

ofsize

3x

6x

1/16wasco

nstru

cted

and

mounte

donto

aholderwhich

allowsfreero

tation

alongth

elong

axis

ofth

ewing.Thewingca

nflip

insu

chawayasto

striketh

eair

stre

am

at+40angle

of

attack

travellingeitherforw

ard

orback

ward

.Thewingholderis

mounte

dto

aminiatu

re6

degre

e-of-freedom

balance

atth

ewingro

otca

pable

ofmeasu

ringall

thre

eaxialforc

esand

moments.

Mech

anically,

thewingmust

beflappedforw

ard

andback

ward

tosimulate

thebiological

flightpro

cedure

,andth

isis

donebymeansofanelectrica

lmoto

randdrivech

ain

mech

anism

consistingofamain

gearandtw

olinkages.

Thefinallinkagenotonly

movesback

andforth

inre

sponse

toth

ere

volving

gearwheel,

butholdsasu

pport

stru

cture

towhich

theforc

ebalance

,wingholderand

wingare

mounte

d.Thusth

ero

tatingmotion

ofth

edrivemoto

ris

converted

toaflapping

motion,co

mpelling

thewing

toflip

betw

een

opposing

anglesof

attack

.During

aflapping

test

pro

cedure

,data

from

theforc

ebalance

and

shaft

enco

ders

pro

-vidingforc

es,

moments,pitch

angle

and

flap

position

isre

cord

ed

byLABVIE

W.Thedata

isth

en

analyze

din

MATLAB

and

all

forc

esand

flap

positionsare

plotted

versustime.

However,

theforc

esmeasu

red

by

theforc

ebalance

conta

inboth

aero

dynamic

and

inertial

forc

eco

mponents.In

ord

erto

obta

inpure

lyaero

dynamic

forc

es,

thete

stis

repeate

dwith

theassembly

inavacu

um

chamber,

inwhich

case

only

inertialloadsare

pre

sent,

and

these

inertialforc

esca

nbesu

btracted

from

theto

tal,

leavingju

staero

dynamic

lift

and

dra

g.

Atth

isstagein

theexperiment,

thetimehisto

ryoflift

anddra

gofarigid

flappingwing

hasbeendete

rminedforgivenanglesofattack

,andvariesacc

ord

ingto

thegenera

lexpected

behavior.

Dra

galw

ayspoints

inth

edirection

opposite

oftravel,

and

thusis

negativefor

one

half

ofth

ecy

cle

and

positive

forth

eoth

erhalf.

Lift,

however,

ispositive

forboth

anglesofattack

,and

goesto

zero

asth

ewing

flipsfrom

one

position

toth

eoth

er,

thus

oscillatingfrom

positiveto

negativetw

iceeach

wingflap.This

isasignifica

ntmilestonein

ultim

ate

lyco

mparing

aero

dynamicsofaflexible,flapping

wing

and

those

ofarigid,fixed

wing.

1of1

AmericanInstituteofAeronauticsandAstronautics

ComputationalAnalysisofth

ee!ects

ofPoro

sity

Gra

phitePro

perties

Edwin

Gaddis,RamanaPidaparti

Virginia

CommonwealthUniversity

Gra

phite

due

toits

extraord

inary

mate

rialpro

perties

has

been

use

das

astru

ctura

lmate

rialaswell

asa

key

componentofnuclearre

actors.Athigh

tempera

ture

s,gra

phite

underg

oesincr

ease

dporo

sity

dueto

oxidation

thatch

angesth

emicro

stru

cture

ofth

ema-

terial.

Itis

importantto

acc

ura

tely

chara

cterize

themate

rialpro

pertiesofgra

phiteunder

high

tempera

ture

conditions,

initspristine

condition

and

atvariousinte

rvals

during

its

serv

icelife,and

todevelop

failure

pre

diction

models.Oneofth

emost

widely

use

dch

ar-

acteriza

tion

tools

forgra

phiteis

x-ray

tomogra

phy,

which

pro

duce

sim

agesofth

einte

rnal

stru

cture

ofth

emate

rial.

These

imagesca

nth

en

be

use

dto

reco

nstru

ctCAD

models,

which

intu

rnca

nbe

analyze

dusing

finite-element

meth

ods

(FEM

).This

pre

senta

tion

discu

sseste

chniquesforco

nstru

cting

CAD

models

ofto

mogra

phic

images,

and

forusing

FEM

topre

dictth

ee!ectsofincr

ease

dporo

sity

on

mech

anicaland

therm

alpro

pertiesof

gra

phite.

Resu

ltsobta

ined

from

the

computa

tionalanalysissh

ow

thatYoungsmodulus

decr

ease

swith

incr

easing

poro

sity

and

this

relation

isverified

both

experiments

from

the

lite

ratu

reaswell

asanalytica

lso

lutions.

1of1

AmericanInstituteofAeronauticsandAstronautics

WillPROFAC

and

PHARO

Tra

nsform

Space

Economicsand

Mission

Design?

BlairCapriotti,Derek

Montalvan,NatashaPeake

WorcesterPolytechnic

Institute

Space

travelbeyondearthorb

it,dueto

thecu

rrentnece

ssityforliftingfarmore

fuelmass

than

payload,is

exponentially

expensive.

Orb

iting

fueldepots

are

aviable

solution,but

refillingth

em

would

requireeitherbringingre

sourc

esup

from

Earthssu

rface

oracq

uiring

them

insp

ace

.If

theneed

forliftingre

sourc

esfrom

Earth

could

bere

duce

doreliminate

dwithoutth

ere

quiringamassiveextraction

and

delivery

infrastru

cture

on

themoon

oran

astero

id,th

ere

sult

would

bea

bre

akth

rough.It

would

transform

theeco

nomicsofsp

ace

activity

and

have

massive

implica

tionsforboth

space

craft

and

mission

design.

Atleast

two

tech

nicalpro

posa

lsexistin

the

currentlite

ratu

reth

atfocu

son

the

gath

ering

ofgas

reso

urc

esin

low

earthorb

it(L

EO).

Thefirst,

byatleast

50years,is

PROFAC,invente

dby

Ste

rgeDemetriades(p

ublish

ed

in1959),

butth

isideaso

mehow

dro

pped

outofsightfora

genera

tion.It

wasn

tuntilan

independentre

invention

ofagasgath

eringsy

stem

known

as

PHARO

(byate

am

ledbyAlanW

ilhite)wasente

redinto

aRASCAL

conte

standaward

ed

seco

nd

place

thatth

isideawasre

introduce

d.Both

PROFAC

(in

itsmost

stra

ightforw

ard

andim

mediate

applica

tionin

LEO)andPHARO

requireth

eco

llectionofatm

osp

hericgase

sin

ord

erto

overc

omedra

gto

mainta

inorb

itand

fuelhigh

impulseand

chemicalro

ckets.

Demetriades(J

BIS

,1959)describesPROFAC

asfollows,

”It

isa

deviceth

atorb

itsatan

altitudeofro

ughly

110km,co

llectsatm

osp

hericgase

s,store

sth

eoxygen

tore

fueldevices

for

high-thru

stsp

ace

missions,

thuseliminating

the

need

tolift

oxidizer

toorb

it,while

using

thenitro

gen

inan

Electro

magneticth

ruster(p

owere

dby

solarce

lls,

nuclearpower

oroth

ermeans)

tooverc

omedra

gand

mainta

inorb

itand/oruse

forpro

pulsion

insp

ace

where

highersp

ecificim

pulseis

required.”

Heenvisaged

ord

erofmagnitudere

ductionsof

takeo!

weightand

oth

erlarg

eadvanta

gesforsp

ace

travel.

Wewillco

nte

nd

thatth

efield

isfinally

ready

forth

iste

chnology.

PROFAC/PHARO

isnow

inth

eopen

lite

ratu

reand

Wilhiteclaim

sth

athewaspro

mpte

dto

lookinto

theco

nce

ptbyNASAsChiefTech

nologist.

While

the

majority

position

inth

efield

isstillth

atin-situ

reso

urc

eutiliza

tion

inLEO

isim

possible,clearly

that

view

isbre

aking

down

or

at

least

being

questioned

inso

me

importantplace

s.Significa

ntpro

gre

sshasbeen

madein

developing

theco

mponents

that

would

make

up

such

agas-gath

ering

system

inth

elast

few

deca

des,

which

could

lead

toitsre

aliza

tion

fasterth

an

expected.

Demetriadeshim

self

estim

ate

dit

at10-20

years

from

thestart

ofawell-funded

tech

nologydevelopmentpro

gra

m,aboutmid

care

erforour

genera

tion.

Additionally,

we

would

like

togetaero

space

pro

fessionals

ofourgenera

tion

thinking

aboutth

iste

chnicalca

pability

and

designing

acc

ord

ingly.

Thus,

we

pro

pose

astudentco

nte

stassuming

the

existe

nce

ofa

PROFAC-like

device.

Conte

stants

would

be

ask

ed

toplan

amission

thatis

only

possible

oreco

nomically

feasible

given

PROFAC

as

infrastru

cture

.This

would

highlightth

eadvanta

gesofth

esy

stem

and

limitationsth

efield

face

swithoutit.

By

exploring

whatco

uld

be

ach

ieved

insp

ace

afterth

isbre

akth

rough,

theca

sefordevelopingit

ismade.

1of1

AmericanInstituteofAeronauticsandAstronautics

Pro

posalforan

EducationallyIn

tera

ctiveLunarBase

Exhibit

Justin

White,

DillonLankenau,JulianSullivan

WorcesterPolytechnic

Institute

Since

1970

NASAssh

are

ofth

efedera

lbudgethassh

runk

by

75

perc

ent,

thre

ate

ning

thefu

ture

ofth

eU.S.sp

ace

pro

gra

m.How

can

were

vivein

young

mindsth

eexcite

ment

and

sense

ofdisco

very

thatacc

ompanied

ourfirstvisit

toth

emoon

in1969?

What

ifwe

retu

rnto

the

moon

via

adynamic

educa

tionalexhibit

base

don

acirc

a2069

lunarbase

thatis

tech

nologically

and

eco

nomically

feasible

today,

aspre

sente

dby

Cra

tersville

and

Moon

Capital?

Whatif

this

exhibit

were

inpara

llelwith

asp

iralcu

rricu-

lum

pro

gra

m,which

buildson

itse

lfevery

yearfor6years

with

students

ingra

des5-10in

theW

orc

esterPublicSch

ools

(WPS)sy

stem?

Whatif

italso

pro

videshands-on

learn

ing,

review

forM

CAS

conce

pts

(MA

state

exam),

auniqueyearlyca

pstoneexperience

,and

an

immersiveenvironmentsimilarto

actually

living

and

work

ing

on

themoon?

This

exhibit

could

insp

ire

students,pare

nts,educa

tors,artists,enth

usiasts,

and

pro

fessionals

towork

toward

saco

mmon

goal:

anew

space

ageofdisco

very

.A

single

exhibit

ofelements

found

on

the

moon

could

explain

state

sofmatter,

the

Periodic

Table,andco

mpounds.

Apre

sente

r,forexample,mightintroduce

iron,aluminum,

tita

nium,silico

n,and

oth

ertrace

elements

pre

sentin

thelunarre

golith

.These

elements

may

be

separa

ted

from

the

regolith

using

their

resp

ective

melting

points.

Nitro

gen

and

Carb

on

Dioxide

are

rare

on

the

moon,and

willlikely

be

imported.

This

pre

sents

an

opportunity

todemonstra

tehow

nitro

gen

initsliquid

state

can

lower

the

tempera

ture

ofobjectsenough

tobe

shattere

dwith

lightforc

e.

Plants

harn

ess

energ

yby

consu

ming

card

ondioxide,whichin

aso

lidstate

beco

mesdry

iceandwillsu

blimate

(sta

tech

angefrom

solid

togas)

(07.P

S.09)1

.Thepre

sente

rca

ndoexampleswith

multiple

elements

from

the

periodic

table

(07.P

S.04).

Furtherm

ore

,th

eFahre

nheit,Celsiusand

Kelvin

scaleswillall

beuse

dth

roughoutth

eexhibit

(07.P

S.08).

Anoth

erexhibit

mightfeatu

rero

botics,where

visitors

identify,re

pair,and

implement

robots

forvariouspurp

ose

s(0

5.IS.01).

Visitors

would

beask

edto

imaginewhatfu

nctionit

willperform

(07.T

S.05,07.T

S.07),

and

then

customizearo

botforminingopera

tions,

con-

stru

ction,and

transp

ortation.In

terchangeable

partsmightincludeca

mera

s,te

rrain

com-

patible

wheels,co

mmunication

systems,

and

roboticarm

sand

tools

(08.T

S.01,07.T

S.03).

Visitors

could

test

their

robots,forexample,bymeltingmoon

dust

into

glass

usinglase

rs,

orbre

aking

thro

ugh

lunarcr

ust

with

adrill.

There

willalso

be

controlco

nso

lesallow-

ing

visitors

tointe

ract

with

the

robots

manipulating

the

camera

sorro

tating

the

robot

(08.T

S.06).

This

could

late

rbe

expanded

toinclude

students

controlling

actualro

bots

work

ingon

thelunarbase

,usingco

ntrolco

nso

lesloca

ted

inth

emain

controlro

om

ofth

eexhibit,and

watchingvideofeedsofth

ero

bots

from

their

classro

om.(0

8.T

S.01).

Thepote

ntialforanexcitingandinte

ractiveexhibit

thatinsp

iresandeduca

tesstudents

goes

beyond

the

examples

described

here

.This

exhibit

can

change

the

idea

ofsp

ace

disco

very

from

an

unre

alistic

thoughtto

an

ach

ievable

goalin

themindsofouryouth

,and

futu

regenera

tions.

1of1

AmericanInstituteofAeronauticsandAstronautics

AStrongly

Implicit

Meth

od

forth

eSolution

of

Tra

nsientIn

compressible

ViscousFlow

Pro

blems

NicholasDiZinno,GeorgeVradis

Polytechnic

Institute

ofNYU

Anew

meth

od

forth

eso

lution

oftime-d

ependentincompressible

viscousflow

problems

isintroduced.Themeth

od

takesadvanta

geofa

predominantflow

direction

and

strongly

couplesth

epressureandvelocityfields.

Thegoverningequations,

usingprim

itivevariables,

arediscretized

on

astaggered

grid,and

theso

lution

isgenerate

dby

aline-b

y-linesw

eep

ofth

eflow

field.Alongeach

computa

tionalline,th

eequationsareso

lved

usingan

e!cient

block-tridiagonalalgorithm.

The

meth

od

isfu

lly

implicit

and

doesnothave

any

ofth

e

drawbacksofexistingmeth

ods.

Numericalexperim

ents

show

themeth

od

toberobust

and

e!cient.

Application

ofth

emeth

od

tocanonicalproblemsin

fluid

mechanicsis

prese

nte

d.

1of1

AmericanInstituteofAeronauticsandAstronautics

AdvancingSpaceM

ission

Opera

tionsBest

Pra

ctices

betw

een

theM

ilitary

and

Civilian

Communities

JoshuaAlbers,ChrisRegan

,Jason

Price

TheJohnsHopkinsUniversity

Applied

PhysicsLab

Assp

ace

craft

opera

tionsco

ntinueto

adaptto

thefiscalausterity

ofth

epost

9/11federa

lbudgetenvironment,

thenationalse

curity

and

civilian

space

opera

tionsco

mmunitiesare

incr

easingly

task

ed

with

merg

ing

their

resp

ective

opera

tionsin

ord

erto

ach

ieve

gre

ate

re!ciency

with

limited

reso

urc

es.

Where

once

these

two

environments

existe

din

close

d,

narrowly

defined

opera

tionalse

ttings,

wenow

find

thatth

ese

twoelements

ofsp

ace

opera

-tionsmust

work

inte

rdependentlyto

ach

ievegre

ate

rco

mmonality

acr

oss

multiple

pro

gra

ms.

Both

communitieshavedevelopeddistinctly

di"

ere

ntco

nce

pts

ofsp

ace

craft

opera

tions,

and

norm

alizing

these

opera

tionsto

allow

cross-m

ission

and

intra-m

ission

coopera

tion

willbe

akey

componentin

the

continued

succ

ess

ofDepartmentofDefense

(DOD)sp

ace

mis-

sions.

Whileth

ere

are

nece

ssarily

distinct

di"

ere

nce

sbetw

een

thecivilian

and

DOD

space

missions,

commonalitiesexistaswell.

This

paperwilldiscu

ssth

evariouswaysin

which

the

civilian

and

DOD

space

mission

overlap

inth

eir

capabilities,

and

where

these

capa-

bilitiesca

nbee"ectively

managed

inord

erto

incr

ease

opera

tionale!ciency

and

reduce

dopera

tionsco

st.

By

doing

so,th

eDOD

and

civilian

space

opera

tionsco

mmunitiesmay

be

able

toincr

ease

coopera

tion

betw

een

pro

gra

ms,

there

by

enhancing

mission

capability

whileco

ntinuingto

keep

opera

tionsco

stswithin

budget.

1of1

AmericanInstituteofAeronauticsandAstronautics

SatelliteServ

icing:M

odelingFlexible

Satellite

Dynamics

JustinBrannan

University

ofMaryland

Advancesin

roboticte

chnologyhavesp

arked

anew

agein

sate

llitese

rvicingasmission-

criticalfailuresth

atwould

oncelead

toth

eend-of-life

ofasp

acecraft

can

now

beremedied

byth

euse

ofroboticse

rvicingplatforms.

Inorderto

reach

this

goal,

itis

necessaryto

test

concepts

ofth

ismission

on

Earth

by

usingmodels

and

simulationsto

proveth

efeasibility

ofsu

ch

amission.

Many

capabilitiesare

necessary

tocomplete

this

end-to-end

mission;

howeverth

ispaperfocuse

sonth

eabilityofasp

acecraft

servicerto

grapple

withasa

tellite,

mainly

how

tomodela

spacecraft

with

flexible

appendagesin

orderto

ultim

ate

lyassess

wheth

erornotany

flexible

modesareexcited.

Ifth

ese

flexible

modesareexcited,it

could

leadto

undesirable

motionduringinte

raction

withth

esp

acecraft

servicer,makingit

di!

cult

toestablish

conta

ctbetw

eensp

acecraft

and

possibly

damagingth

esa

tellite.Although

these

models

aresimple

tocreate

inADAM

Sor

Freesp

ace,it

isnecessary

tointroducea

real-timeasp

ectth

atis

abse

ntin

eitherofth

ese

simulation

environments,to

conductverification

testson

aroboticsimulation

platform.It

isth

ereforenecessary

toincrease

thefidelity

ofth

ecurrentsa

tellitemodeluse

din

ground

testingforasa

tellitese

rvicingmission,addingmorecomplexmotionto

analyzehow

flexible

body

dynamicsa"ecthow

asp

acecraft

acts

inresp

onse

toreaction

forcesfrom

arobotic

servicingplatform.

Three

single-axis

flexible

models

were

create

dincluding

avarying

numberofflexible

appendagesin

orderto

analyzealargesa

mple

ofsa

tellitestructu

res.

Foreach

model,

the

rigid

and

flexible

body

mass

and

forcing

matricesareformed

and

combined

tocreate

the

overall

equation

ofmotion

forth

esy

stem.

The

state

ispropagate

dovertime

asvarious

inputforcesandto

rquessimulate

theinte

ractionwithth

esp

acecraft

servicer.Theresu

lting

motion

provides

insightto

how

the

sate

llite

willreactduring

many

stages

ofa

robotic

servicingmission.

Currently,th

issimulation

platform

expressesth

ecombined

rigid

and

flexible

dynamics

byplottingth

ereaction

ofasa

telliteto

agiven

initialforceorto

rqueinput.

Afterfu

rth

er

testing

and

validation

against

asimilar

modelin

ADAM

S,it

willbe

possible

toassess

wheth

erornotmodesh

apeswillbeexcited

todete

rminehow

theflexible

dynamicswill

impactth

eroboticse

rvicingmission.This

modelhasth

ecapability

tobeim

plemente

don

aroboticplatform

forground

testing,and

willbeinte

grate

din

areal-timesy

stem

using

Moto

man

robots

tovalidate

thekinematicsofth

esy

stem.

1of1

AmericanInstituteofAeronauticsandAstronautics

Onboard

Sto

chastic

Constra

intSusp

ension

forVehicle

Health

Monitoring

LouisBreger

DraperLaboratory

Auto

nomousfault

managementhasre

cently

been

identified

asakey

tech

nology

forfu

-tu

resp

ace

missionsin

NASAs2010te

chnologyro

admap.Aninnovativeappro

ach

tovehicle

health

monitoring

(VHM

)is

pro

pose

dusing

constra

intsu

spension

with

parity

space

and

hypoth

esiste

sting

tech

niques.

By

using

models

ofvehicle

components

and

dynamics,

as

well

asexplicitly

usinginform

ation

aboutse

nso

rand

pro

cess

noise,aVHM

algorith

mca

nbe

synth

esize

dth

athastu

nable,pre

dicta

ble

reliability.

An

implementa

tion

ofth

isalgo-

rith

mis

describedandanalyticre

sultsare

reportedth

atdemonstra

teanim

pro

vementover

anoth

ermodel-base

dte

chniquein

thelite

ratu

reth

atdoesnotinco

rpora

teunce

rtainty

in-

form

ation.Sim

ulationre

sultsonamodeledvehicle

GN&C

system

show

similaradvanta

ges

and

demonstra

teth

eVHM

meth

od’s

valueasboth

an

onlineFDIR

tooland

asa

design

analysisto

olforassessingse

nso

rse

lection

and

senso

rplace

ment.

Thestoch

astic

constra

int

susp

ension

algorith

mhasbeen

implemente

dusingamodel-base

ddesign

meth

odology,

au-

toco

ded,and

deployed

asembedded

software

on

aflight-likepro

cessor.

1of1

AmericanInstituteofAeronauticsandAstronautics

ARobot-C

entered

Sim

ulated

LunarBase

InhwanKim

,ErikScott

WorcesterPolytechnic

Institute

The

Worc

esterLunarBase

Exhibit

isa

pro

pose

dscience

and

tech

nology

educa

tional

reso

urc

ece

nte

r,to

be

loca

ted

inth

ebase

ment

ofth

enow-vaca

nt

Worc

ester

Memorial

Auditorium.This

part

ofth

estru

cture

rece

ntly

serv

ed

asaju

venileco

urt,and

isin

much

betterre

pair

than

theupperfloors.

Also

ofinte

rest

isa

small

theate

ratoneend

ofth

ebuilding.It

ishere

thatth

epro

pose

dlunarbase

tourwould

begin,with

an

introductory

briefingand

video.

Theprimary

purp

ose

ofth

eexhibit

willbeto

help

middle

schoolstudents

(gra

des5-8)to

ach

ieveth

eeduca

tionalgoals

setbyth

eM

assach

use

ttsScience

andTech

nologyFra

mework

.Keyco

nce

pts

willbepre

sente

din

auniqueandmemora

ble

setting,withhands-onactivities

and

pra

cticalapplica

tionsofmate

rialco

vere

din

theclassro

om.These

condary

purp

ose

isto

enco

ura

geth

enextgenera

tionofcitize

nsto

beco

meinte

restedin

space

explora

tion,learn

thatso

meth

ing

like

this

ispossible

and

implicitly

make

aca

sefordoing

it.

We

envision

an

exhibit

capable

ofacc

ommodating

aminim

um

offourclassesofup

to32

students

ata

time,with

thepote

ntialto

serv

etw

oorth

reetimesth

atnumber.

The

lunar

base

exhibit

willo!er

awide

variety

ofactivities

including

simple

pro

-gra

mmable

robots,3D

simulationsofexplora

tionandmining,andoth

erare

assu

chascr

ew

residence

s,agre

enhouse

and

mate

rials

pro

cessing.Thegoalis

topro

videasauth

entican

experience

aspossible

within

thescopeofstudents

scientificknowledge.

Betw

een

9:00

am

and

2:00

pm

daily,

fourdi!

ere

ntgro

upswith

thirty

two

students

for

each

gro

up

willto

urth

eexhibit.Afterash

ort

briefingatth

eth

eate

r,th

eguidesforeach

gro

up

willlead

students

todi!

ere

ntactivity

are

as.

The

guide

willpro

vide

explanations

thatco

nta

inEarth

and

Lunar

compariso

ns,

utilizing

inte

ractive

displaysth

atwillallow

students

toactually

experience

thelessons,

notju

stre

ad

and

hearaboutth

em.

There

willbefourmain

activity

are

as:

robotre

pair,ro

botco

ntrol,

human

habitatand

environmenta

lco

ntrol,

with

indirect

exposu

reto

the

rest

ofth

ebase

via

scre

ensloca

ted

thro

ughout

the

facility.

The

exhibits

willbe

designed

tosu

pport

agenera

lfifth-gra

de

curriculum,a

robot-ce

nte

red

seventh

-gra

de

curriculum

and

ach

emistry-oriente

deighth

-gra

de

curriculum.

Eighth

gra

ders

may

also

visit

adi!

ere

nt

site

at

anearb

ybota

nical

gard

en,mock

edupto

simulate

alunargre

enhouse

.Theexhibit

willco

nta

inallth

ere

quired

pra

cticalamenities,

butth

eca

fete

riawillse

rveonly

food

you

could

pro

duce

on

themoon.

Thelunarbase

exhibit

willbea

giftofth

eco

llegesofW

orc

esterto

thepublicschools

ofW

orc

ester.

Lots

ofco

llegestudents

willhavepart-tim

ejobsand

do

pro

jectsforcr

edit

running

thefacility.There

willalso

beclassro

omsto

pro

videlecture

sto

collegestudents,

and

fortrainingte

ach

ers

how

topre

pare

their

students

togetth

emost

outofth

eultim

ate

field

trip,th

eca

pstoneto

their

science

curriculum.

Inourview

itis

notenoughto

claim

thatso

meth

ingca

nbedone.Youhaveto

show

how

itca

nbedone,andexplain

whyit

should

bedone.Forth

isre

aso

n,to

picsth

atdemonstra

teth

era

tionale

fora

lunarbase

willbeco

vere

d,su

chasadvance

daero

space

transp

ort

and

constru

ction

engineering

using

loca

lmate

rials.

We

wantstudents

toundersta

nd

how

alunar

base

could

be

create

d,how

itwillfeed

itse

lfand

pay

for

itse

lf,and

whatsu

cha

facility

could

contribute

toth

efu

ture

ofscience

and

tech

nology.

Itis

an

invitation

tobepart

ofa

gra

nd

adventu

reasth

ehuman

race

takesitsfirstte

nta

tivestepsto

colonize

anoth

erheavenly

body.

1of1

AmericanInstituteofAeronauticsandAstronautics

CCSU

HelicopterFlightSim

ulato

rDesign

&

Fabrication

Improvement

EricRichard,Nguyen

Nguyen,EricOlender,RussellHallow

ell,

Cen

tralConnecticutState

University

Stu

dents

inth

eEngineering

and

Engineering

Tech

nology

pro

gra

msare

inth

epro

cess

ofdesign

and

upgra

dingth

eexistingCCSU

Helico

pte

rFlightSim

ulato

rpro

ject.Figure

1pre

sents

the

existing

flightsimulato

rwith

pilotco

ntroland

mach

ine

partslist.

Figure

2pre

sents

students

usingmach

ineto

ols

tomach

ineflightsimulato

rpartsin

thelab

mach

ine

shop.

Figure

3pre

sents

astudentwelding

flightsimulato

rframes.

The

existing

CCSU

flight

simulato

rmotion

platform

has

two

degre

es

offreedom,ro

lland

pitch

.Figure

4sh

owsth

emaxim

um

angle

forth

epitch

and

roll

motions.

Forth

enextflightsimulato

rpro

ject,im

pro

vements

willfinish

the

mech

anicaland

electrica

ldesignsofth

esimulato

rmotion

base

and

linkth

eflightsimulato

rso

ftware

(X-P

lane9)to

themotion

platform

.An

extra

yaw

(rota

tion)degre

eoffreedom

willbeadded

by

inte

gra

ting

additionalelectro

nic

linearactuato

rswith

thesimulato

r;also,forsa

fety

purp

ose

s,fourpointsa

fety

harn

esses

willbe

added

toth

eco

ckpit

seat.

Adding

this

componentwillallow

the

use

rto

safely

opera

teth

esimulato

rwithoutmoving

aro

und

inth

eco

ckpit

seat.

Inord

erto

powerth

esimulato

rand

all

ofitselectrica

lco

mponents,wewillinstall

apowersu

pply

thatwillhave

theca

pabilitiesto

pull

atleast

twenty

ampsofcu

rrentwhilepro

vidingtw

enty

fourvoltsof

voltageco

ntinuously.

There

fore

,aBK

Pre

cision,M

odel#1964powersu

pply

willbeadded

tofu

lfill

the

electrica

lneeds.

The

flightsimulato

rso

ftware

needsto

have

the

capability

toco

ntinuously

communicate

with

the

simulato

r.The

controlelectro

nicsand

inte

rface

willhave

tobe

update

ddue

toth

eaddition

ofth

eyaw

axis

ofro

tation.

We

willneed

electrica

lhard

ware

thatwillbeable

toanalyze

realtimedata

feedback

from

thesimulato

r.An

F.P

.G.A

.,alsoknown

asaField

Pro

gra

mmable

Gate

Array,

willbeable

tosu

!ciently

fulfill

these

task

s.All

electrica

lhard

ware

and

software

willbeable

tobeco

nstru

cted

by

students

atCCSU.All

impro

vements

willbeco

mplete

dby

nextM

ay

2013.

1of1

AmericanInstituteofAeronauticsandAstronautics

ExperimentalChara

cterization

ofIsolato

rShock

Tra

in

Pro

pagation

JonathanGeerts,KennethH.Yu

University

ofMaryland

Quasi-ste

adysh

ocktrainsin

arecta

ngularisolato

rofth

easp

ectratio3werecharacte

r-

ized

with

Mach

2.5

upstream

flow

and

underslowly

varying

backpressure

conditions.

A

time-h

isto

ry

schlieren

technique,accompanied

by

simultaneousstatic

and

dynamic

pres-

sure

measu

rements,wasperformed

tobetter

understand

the

transientasp

ectofsh

ock-

boundary

layerinte

raction

leading

toinletunstarts.

Both

spanwiseand

cente

rlinestatic

pressuremeasu

rements

wereutilized

tocharacte

rizeth

epropagation

ofsh

ocktrainsinside

theisolato

r,whileth

edynamic

pressuremeasu

rements

werefu

rth

eranalyzed

inan

e!ort

tofind

any

precurso

rofunstart.

Adata

base

showing

time-reso

lved

schlieren

imageswith

corresp

onding

axialpressure

profile

and

pressure

gradientprofile

wasconstructe

d.

The

preliminary

resu

ltsrevealed

acleardi!

erencebetw

een

visible

shock

train

length

and

the

exte

ntofth

epressuregradientin

theisolato

r.In

vestigation

on

thesh

ock

train

dynamics

revealed

ahighly

oscillato

ry

natu

reofth

epropagating

shock

trains.

Additionalrese

arch

isin

progress

tocharacte

rizeth

esh

ock

train

motion

and

thedynamic

behaviorwith

the

downstream

pressuredistu

rbancecharacte

ristics.

1of1

AmericanInstituteofAeronauticsandAstronautics

APROTOTYPE

MULTICOPTER

LOW

ALTITUDE

AUTONOM

OUS

NAVIGATION

DEVICE

SpencerHamblin

Northwood

APROTOTYPE

MULTIC

OPTER

LOW

ALTIT

UDE

AUTONOM

OUSNAVIG

ATIO

N

DEVIC

E

Theobjectiveofth

ispaperis

tosh

ow

thefeasibilityanduse

fulness

oflow

altitudemulti-

copte

rnavigation

usingacombination

ofcompute

rvision

and

operato

rcontrol.

Currently

thereis

noso

lution

available

thatwould

allow

amulticopte

rto

safely

navigate

below

tree

levelorunderobstacles.

This

multicopte

rwould

be

able

togetunderth

etree

line

and

tag

anim

als;additionally

this

devicecan

beuse

dforremote

access

ofdangerousareasto

collectsa

mples.

This

proto

typemulticopte

rdesignta

kesadvanta

geofamoto

rto

moto

rsizeof36inches.

Thelargersizeallowsforalargerpayload.Themulticopte

remploys6brush

less

moto

rsth

at

aresu

pplied

by

a5

amp

lith

ium

polymerbattery.A

flightcontrollerboard

handlesbasic

levelingand

coordination

ofth

emoto

rs.

Forte

stingand

emergency

controla2.4ghzradio

system

isutilizedwhichallowsforfast

switchingto

manualcontrol.

Videodata

isanalyzed

usingasm

all

compute

rrunningth

eOpen

Compute

rVision

library.An

avrATM

EL

chip

isuse

dto

handle

pulse

width

modulation.

Senso

rdata

forth

egyro,acceleromete

r,and

magneto

mete

rarehandled

via

I2C.Finally

videotransm

ission

tohomebase

isvia

an

800

milliwatt

900M

Hzvideotransm

ission

system.

The

multicopte

rdescrib

ed

above

isinexpensive

tobuild

and

can

go

into

hostile

envi-

ronments

tocollectsa

mplesand

taganim

als.

1of1

AmericanInstituteofAeronauticsandAstronautics

Warer-B

ased

TransferofNanomaterials

Thin

Films

Sepideh

Parvinian,HongliZhu,ZhiqiangFang,LiangbingHus

university

ofMaryland,CollegePark

Here

wepro

pose

asimple

and

cost

e!ectivemeth

od

oftransferring

nanomate

rialth

infilm

svia

wate

rassiste

dtransferprintingmeth

od

(WTP).

Asm

ooth

and

thin

film

ofhighly

conductiveSW

CNT

istransferred

tononco

nventionalsu

bstra

tes,

such

asglass

and

plastic

afterco

ating

on

wate

rtransferprinting

paperand

exposing

towate

r.Thewate

rtransfer

paper

ismade

offour

distinct

layers:

image

acc

epting

layer,

where

CNT

thin

film

isexpose

d,polymericbinderlayer,

wate

rslidinglayerand

pre

-coatinglayer.

Inth

ispro

cess,

wate

rpenetrate

sinto

theinte

rface

sofbinderand

slidinglayerand

thus,

thewate

rso

aked

binderca

nbeslid

o!,leavingath

infilm

on

theta

rgetsu

bstra

te.Theth

ickness

ofth

efilm

isdete

rmined

by

the

thickness

ofco

iled

wireson

the

Meyerro

ds.

This

transfermeth

od

yield

e"ciency

ofappro

xim

ate

ly100%

and

CNT

film

adhere

swell

toth

esu

bstra

te.

The

sheetre

sistance

and

transm

itta

nce

aftertransferand

wash

ingo!

thebinderare

1000

! sqand

betw

een

83to

88%

resp

ectively.

1of1

AmericanInstituteofAeronauticsandAstronautics

Developmentofasm

all

satelliteattitude

determ

ination

and

controlsimulation

testbed

Matthew

Disher

United

StatesNavalAcadem

y

Thepro

pose

dre

search

willco

nsist

ofdevelopingan

attitudedete

rmination

and

control

simulation(A

DCS)te

stbedin

ord

erto

impro

veperform

ance

andexpandth

escopeofsm

all

sate

llitemissions,

cubesa

ts(referringto

standard

ized

small

sate

llitedevelopmentarchitec-

ture

).This

willallow

forth

einte

gra

tion

ofmore

capabilitiesincluding

an

activeattitude

controlsy

stem

usingmomentu

mexch

angedevicessu

chasre

actionwheels.There

hasbeen

an

incr

easing

need

insu

pporting

theinte

gra

tion

and

testing

forth

ese

actively

controlled

cubesa

ts.Usingalarg

erADCSte

stbedmodelth

athasbeenwork

edonin

past

years

atth

eNavalAca

demy,

this

rese

arch

willbefocu

sed

on

developingan

attitudedete

rmination

and

controlsimulation

testbed

with

realistic

hard

ware

components

and

compute

rpre

cessors

thatca

nperform

close

d-loop

attitudedynamicsand

controlsimulation

inth

elabora

tory

environment.

Africtionless

air

bearing,which

hasbeen

rece

ntly

purchase

d,willbeinte

-gra

tedto

help

simulate

on-orb

itenvironment.

This

rese

archhopesto

create

anopera

tional

testbed

thatca

nbeuse

din

astro

nautica

lengineeringclassesatUSNA

inth

efu

ture

.

1of1

AmericanInstituteofAeronauticsandAstronautics

ABoltzm

ann

Sim

ulation

forM

ulti-grid

Inertial

Electro

staticConfinem

ent(IEC)

Andrew

Chap

University

ofMarylandCollegePark

Extra-solarexplora

tion

requiresa

powersy

stem

with

ahigh

energ

yto

fuelmass

ratio

thatca

nbe

scaled

down

e!ectively.

InertialElectro

staticConfinement(IEC)Fusion

has

thepote

ntialto

pro

videahigh

poweroutp

utwith

little

tonora

dioactiveby-p

roduct,but

todate

,no

IEC

reactor

has

demonstra

ted

apower

out

topower

inra

tio

gre

ate

rth

an

10-5.

ConventionalIE

Csemploy

two

conce

ntric

spherica

lsh

ell

grids.

The

inner

grid

ismainta

ined

ata

lowerpote

ntialth

an

the

oute

rgrid

tocr

eate

an

ion-confining

pote

ntial

well.Theionscy

clera

diallyback

and

forth

thro

ugh

theco

re,with

ach

ance

tofu

seateach

pass.Thusahigh

energ

yand

density

can

bemainta

ined

inth

eco

re,and

significa

ntfu

sion

can

occ

ur.

Howeverth

ere

are

anumberofenerg

ylossesinhere

ntin

two-grid

designsth

at

makenetpowergenera

tion

physica

llyim

possible.Theinnerca

thodegrid

hasadefocu

sing

e!ect

thatca

use

sionsto

stra

yonto

non-radialpath

s,quickly

resu

ltingin

collisionswithth

egrid.In

addition,dueto

themutu

alelectro

staticre

pulsion

oflike-charg

ed

ions,

ara

ndom

scattering,known

asth

erm

aliza

tion,occ

urs

thro

ughoutth

ech

amber,

which

alsore

sultsin

non-radialtrajectoriesand

aloss

offocu

sing

inth

eco

re.

The

addition

offocu

sing

grids

incr

ease

sion

confinementtimesovertraditionaltw

ogrid

configura

tions.

These

focu

sing

gridsare

positively

charg

ed

and

serv

eto

push

stra

yionsback

into

desire

dbeam

path

s.Io

nbunch

ing

isalso

obse

rved

toocc

urasth

ere

sult

ofth

epote

ntialwell

geometry

along

with

energ

yexch

angesbetw

een

particles.

Themono-energ

eticpack

ets

can

beopera

ted

ina

low

energ

yre

sonance

mode,co

nducive

toth

euse

ofaneutronic

p-B

11

fueland

direct

energ

yco

nversion.Ourcu

rrentre

searchinvolvesanumerica

lmodelofiontransp

ort

within

the

IEC

chamber.

The

ion

distribution

ismodeled

inposition-velocity

phase

space

with

aBoltzm

ann-P

oisso

nsy

stem

and

numerica

lly

appro

xim

ate

dwith

atime-splitting

scheme.

Inth

eone-d

imensionalmodel,

thetransp

ort

ofionsth

rough

phase

space

issp

litinto

two

linearadvection

equations.

Atw

o-d

imensionalmodelhasalso

been

developed.However,

ourinte

rest

atth

ispointliesin

thedevelopmentofafast

one-d

imensionalmodelth

atca

nbesimulate

dup

toth

eth

erm

aliza

tion

timescale

(1000sofpasses).Coulomb

collisionsare

modeled

with

the

Fokker-Planck

equation

inLandau

form

(FPL).

The

opera

tordi!

use

sth

edistribution

invelocity

space

inasitu

ation

where

low

angle

scatteringdominate

s.

1of1

AmericanInstituteofAeronauticsandAstronautics

RBSP

SPACECRAFT

COM

MISSIONING:

ATTITUDE

CONTROL

ACTIVITIES

MadelineKirk

JHU

Applied

PhysicsLab

The

Radiation

Belt

Sto

rmPro

bes(R

BSP)sp

ace

craft

are

apair

ofsa

tellitesdesigned

tostudy

the

Van

Allen

radiation

beltsaspart

ofNASAsLiving

With

aSta

rGeosp

ace

Pro

gra

m.

The

twin

space

craft

were

launch

ed

on

August

30,2012

into

highly

elliptica

lorb

itsth

atpass

thro

ugh

the

radiation

beltswhere

they

willre

main

thro

ughoutth

etw

oyearprimary

science

mission.A

suiteoffiveinstru

ments

on-b

oard

RBSP

willinvestigate

how

relativisticelectro

nsandionsin

thebeltsare

form

edandare

a!ectedbyso

laractivity

thro

ugh

measu

rement

ofparticle

energ

y,density,and

distribution,as

well

as

the

loca

lelectricand

magneticfields.

These

measu

rements

and

trendswillpro

videth

edata

needed

topro

duce

models

ofth

era

diation

beltsth

atwill,

amongoth

erth

ings,

allow

engineers

tobetterdesign

radiation

hard

ened

space

craft

and

fore

casters

topre

dictgeomagneticstorm

sth

atmay

pose

ath

reatto

space

craft

and

astro

nauts.

Thetw

inRBSP

space

craft

are

major-axis

spinners

with

noon-b

oard

attitudedete

rmi-

nation

orco

ntrol.

Theguidance

and

control(G

&C)hard

ware

on

thesp

ace

craft

includes

aSun

senso

rsy

stem,th

rusters

inamono-p

ropellantpro

pulsion

system,and

passivenuta

-tion

dampers.A

flux-gate

magneto

mete

r,included

inoneofth

escience

instru

mentsu

ites,

isuse

dasan

attitude

senso

rin

combination

with

the

Sun

senso

rsto

dete

rmine

attitude

histo

ryon

the

gro

und.

The

gro

und

base

dattitude

estim

ation

and

controlre

sulted

ina

busy

commissioningphase

forth

eG&C

flightte

am

whoplanned

and

execu

ted

maneuvers,

supported

instru

mentdeployment,

ran

daily

attitudeestim

ation

software

,and

monitore

dsp

ace

craft

attitudetrends.

Thefirstse

tofmaneuvers

perform

ed

inth

eco

mmissioning

phase

pro

vided

calibra

tion

data

on

thru

sterperform

ance

and

began

toco

nfigure

thesp

ace

craft

forscience

data

col-

lection.An

initialsp

in-u

pmaneuverbro

ughtth

esp

ace

craft

toitsnominal5.5

RPM

spin

rate

,delta-V

maneuvers

furtherse

para

ted

the

sate

llitesin

orb

it,and

asm

all

pre

cession

maneuveradju

stedth

esp

inaxis

pointingdirection.Thro

ughoutco

mmissioning,additional

spin-u

pand

pre

cession

maneuvers

were

execu

ted

toplace

thesp

ace

craft

inth

edesire

dat-

titu

deforinstru

mentdeployments.Themost

significa

ntim

pact

on

thesp

ace

craft

attitude

wasth

edeploymentoffour50mete

rsp

inplanebooms.

These

boomswere

deployed

over

aperiod

oftw

oweeksin

5-10

mete

rse

gments

thro

ugh

aca

refu

lly

planned

sequence

of

spin-u

pmaneuvers

and

boom

exte

nsionsin

ord

erto

mainta

inan

appro

priate

space

craft

spin

rate

.The

RBSP

space

craft

are

scheduled

tostart

the

primary

two

yearscience

mission

inlate

October2012.

1of1

AmericanInstituteofAeronauticsandAstronautics

Investigation

ofBuoyantTra

nsp

ort

Systemsth

at

Exploit

Martian

Wind

Pattern

s

JakeTynis

Old

DominionUniversity

This

rese

arch

hasdemonstrate

dhow

Martian

wind

patternscan

beexploited

utilizing

buoyancy-controlledballoontransp

ortsy

stemsth

atincorporate

auto

nomousnavigationca-

pabilities.

Polartransp

ortofth

eprim

ary

atm

osp

heric

constituent,

carbon

dioxide,hasa

significante!ecton

planeta

ry

weath

erpatterns.

This

globaltransp

ortproducesnominal

wind

speedsth

ataresu

"cientlyhigh

tofacilitate

planet-widetraverse

s.This

rese

arch

will

demonstrate

thatth

ese

aso

nalwind

variationsoccurin

apredicta

ble

mannerth

atcan

be

exploited.These

e!ects

havebeen

examined

usingnumericalsimulationsand

verified

sur-

facemeasu

rements,startingwith

theVikingLandersand

subse

quentlyfrom

currentrover

andorbitalsp

acecraft.This

rese

archhasutilizedth

eM

ars-GRAM

weath

ersimulationpro-

gram

toexplore

wind

conditionsovercandidate

surface

launch

locationsth

roughoutth

e

Martian

year.Thedata

collecte

dprovidesinsighton

desirable

base

locationsand

nominal

launch

opportu

nitiesforse

rialroboticballoon

missions.

Itis

possible

tota

rgetarangeof

launch

date

sin

orderto

reach

selecte

ddownwind

locations.

Foran

expedition

launching

inth

eNorth

ern

hemisphere,th

eprevailingwindsareEast

toW

est

forsignificantperiods

ofth

eM

artian

year.However,th

eNorth

ern

hemispheresu

mmerso

lsticesh

owsash

iftin

the

prevailing

winds,

nota

bly

the

flow

changesto

West

toEast

fora

shortperiod.

This

changein

flow

direction

isstrongly

driven

by

thesu

blimation

ofth

epolaricecaps.

This

flow

direction

shiftcoupled

with

shearlayerswithin

theatm

osp

hereprovidepossible

nav-

igation

techniques.

These

e!ects

and

oth

ersprovide

alogicalbasisfornavigation

using

atm

osp

heric

soundingte

chniquesand

buoyancecontrolto

e!ectnavigation

similarto

sail-

ing.Exploitingpredicta

ble

weath

ervariationscan

lead

toexploration

ofvast

areasofth

e

planetoraccess

tooth

erwiseinaccessible

locations.

1of1

AmericanInstituteofAeronauticsandAstronautics

Flightstabilization

with

flappingwingsin

gusty

environments

ChaoZhang,ZhengLingxiao,TysonHedrick,RajatMittal

TheJohnsHopkinsUniversity

Sta

bility

offlightwith

flapping

wings,

which

isth

enatu

ralinstinct

ofinse

ctflyers,is

oneofth

emajorch

allengesfordesigningM

icro

Air

Vehicles(M

AV).

Tobetterundersta

nd

how

inse

ctflyers

could

stabilizeitse

lfduringhovering,weuse

fully

coupled

computa

tional

model,

which

combinesth

eNavier-Strokesequationsand

theequationsofmotion

in6de-

gre

esoffreedom

(NS-6-D

OF)to

mim

icth

ehoveringmoth

flightboth

inca

lmenvironment

and

gusty

environments.Thro

ugh

analysisofco

mputa

tionalre

sultsand

compariso

nwith

experimenta

ldata

,a

simple

active

controlstra

tegy

isfound

for

stabilizing

the

moth

inpitch

,which

isalso

validate

din

fully

coupled

CFD

simulation.

More

over,

inth

epre

sent

study,

pro

jection

theory

isemployed

which

pro

jectseach

term

ofth

eNavier-Sto

kesequa-

tion

onto

avectorsp

ace

spanned

by

pro

perly

chose

nharm

onic

vectors

soth

atth

eforc

eexerted

on

theinse

ctbody

could

bequantita

tively

studied

inte

rmsofadded-m

ass

e!ect,

the

vectorsu

mofnorm

alsu

rface

induce

dby

free

vorticity

and

the

visco

ussk

infriction.

This

rese

arch

issu

pported

by

AFOSR.

1of1

AmericanInstituteofAeronauticsandAstronautics

E!ects

ofmean

and

fluctu

atingpressure

gra

dients

on

boundary

layertu

rbulence

PRANAV

JOSHI,XIA

OFENG

LIU

,JOSEPH

KATZ

TheJohnsHopkinsUniversity

Turb

ulentboundary

layers

are

subjected

tofavora

ble

pre

ssure

gra

dients

(FPG)in

avariety

ofengineeringapplica

tionslikeflow

thro

ugh

turb

omach

inebladepassagesand

over

wings.

Although

these

flows

have

been

studied

since

long,th

ere

levantflow

physics

isnotwell

understo

od.

Inth

epre

sentwork

,we

investigate

the

e!ect

ofa

mean

FPG

on

atu

rbulent

boundary

layer,

by

perform

ing

time

reso

lved

two-d

imensionalParticle

Im-

age

Velocimetry

(PIV

)measu

rements.

The

mean

FPG

isim

pose

dby

asink

flow.

The

time-reso

lved

measu

rements

enable

usto

calculate

the

stre

amwise

and

wall-n

orm

al(x

,y)

components

ofth

emate

rialacc

elera

tion

(Du/Dtand

Dv/Dt,

resp

ectively),

which

are

inte

-gra

tedsp

atiallyto

obta

inth

epre

ssure

distribution.Thus,

theim

pact

oflarg

escale

pre

ssure

gra

dientfluctuationson

the

stru

cture

oftu

rbulence

can

be

studied

non-intrusively.

The

mean

FPG

pre

vents

vorticalstru

cture

sfrom

rising

away

from

the

wall,decr

easing

the

Reynoldsstre

ssesin

oute

rre

gion.Larg

escale

pre

ssure

fluctuation

gra

dients

involveth

ree

dim

ensionalflow

stru

cture

s.In

both

,ze

ropre

ssure

gra

dient(Z

PG)and

FPG

boundary

layers,larg

escale

fluctuatingadversepre

ssure

gra

dients

(p/x¿0)are

pre

fere

ntially

associ-

ate

dwith

sweeps,

asfluid

appro

ach

ingth

ewall

isdece

lera

ting.Conse

quently,

theoutw

ard

transp

ort

ofsm

all-sca

letu

rbulence

issu

ppre

ssed,and

the

near-wall

enstro

phy

incr

ease

s.Conversely,ejections,

high

wall-n

orm

alenstro

phy

flux,and

visco

usvorticity

pro

duction

occ

ur

mostly

during

p/x¡0

asth

efluid

acc

elera

tesby

moving

away

from

the

wall.

The

near-wallenstro

phyfluxpeaksdueto

theinhere

ntnearwall3D

stru

cture

swhenp/x¡0

and

u¿0.Resu

ltsalsoindicate

thatth

ese

regionsoffluctuatingadverseand

favora

ble

pre

ssure

gra

dients

are

likely

tobeassociate

dwith

theoutb

oard

and

inboard

sides,

resp

ectively,of

very

larg

escale

inclined

rollerstru

cture

s,se

vera

lboundary

layerth

icknessesin

length

.Sponso

red

by

NSF.

1of1

AmericanInstituteofAeronauticsandAstronautics

Modelingofmagneto

-electric

and

mech

anical-electric

e!ects

inmagneto

strictive-p

iezoelectric

composites:

Application

toth

eenerg

yharv

estingpro

blems

Arm

anjHasan

yan,David

Piliposyan

Virginia

Tech

Wedevelop

theore

tica

lmodelforth

ere

sonance

enhance

mentofmagneto

electric(M

E)

ormech

anical-electricinte

ractionsatfrequenciesco

rresp

ondingto

bendingoscillationsfor

ferroelectric-ferromagneticorferroelectric-elastic

bi-layerco

mposite

s.A

dynamic

theory

of

bi-layerlaminate

dmagneto

-elasto-electricbars

wasco

nstru

cted.Theore

tica

lmodelwhich

included

bending

vibra

tion

e!ectswasdeveloped

forpre

dicting

theM

Ee!ectsorenerg

yharv

estingco

e"cientin

alaminate

barco

mposite

stru

cture

consistingofmagneto

strictive,

piezo

electriclayers.Theth

ickness

dependence

ofstre

ss,stra

in,and

magneticand

electric

fieldswithin

asa

mple

are

taken

into

acc

ountso

thatth

ebending

deform

ationsco

uld

be

considere

din

anappliedmagnetics,appliedmech

anicalloadorelectricfield.Thefrequency

dependence

ME

voltage

coe"cientand

electrica

lharv

esting

coe"cienthave

obta

ined

by

solving

electro

static,

magneto

static,

and

elastodynamic

equations.

Weco

nsiderboundary

conditionco

rresp

ondingto

thatis

freeto

vibra

teatboth

endsandmech

anicallysu

pported

attw

oarb

itra

rypoints.

Asa

demonstra

tion,ourth

eory

forbi-layerM

Eco

mposite

swas

then

applied

toferromagnetic-ferroelectricbilayers.Themodelis

applied

toasp

ecificca

seofM

etg

las-PZT

orPZT-E

lastic

bilayer.

Ath

eore

tica

lmodelis

pre

sente

dforstatic(low-

frequency

)M

Ee!ectsin

bilayers

asaparticularca

se.Dependingon

support

loca

tionsand

geometricaland

physica

lpara

mete

rs,wediscu

ssca

seswhen

energ

yharv

esting

coe"cient

ormagneto

-electricco

e"cientappro

ach

ingze

roorappro

ach

ingto

his

maxim

um

values.

1of1

AmericanInstituteofAeronauticsandAstronautics

OpenM

PScalabilityofan

OversetCFD

SolverUsing

Shared

Memory

Para

llelPro

gra

mming

Benjamin

Jim

enez

University

ofMarylandCollegePark

An

overse

t,compressible,Reynolds-Averaged

NavierSto

kesso

lverwasmodified

from

itsse

rialversionto

includesh

aredmemoryparallelprogrammingdirectiveswithOpenM

P.

Serialcodeprofilingwith

gprofidentified

themost

time-consu

mingsu

broutines.

OpenM

P

parallelconstructs

added

toth

ecode

prese

rved

the

serialversion

while

improving

the

performancecharacte

risticson

multi-corecompute

rarchitectu

res.

Asteady

and

unsteady

case

ofan

airfoil

with

inte

graltrailingedgeflap

and

leadingedgeslatin

awind

tunnelare

examined

forcomputa

tionale!ciency.Theprocess

ofincrementa

lly

addingparallelism

to

theexistingCFD

codewasverifiedfordouble

precisionresu

lts.

Characte

risticsofth

ese

rial

codeth

atareuniquely

di!

cult

toim

plementwith

OpenM

Paredescrib

ed

inaqualita

tive

analysis,

providingguidanceforCFD

engineerswhomay

exploreth

epossibility

ofadding

OpenM

Pto

their

existing

codes.

Scheduling

ofth

read

and

oth

erloop

optimization

tech-

niquesaredescrib

ed

usingFortran

examplesto

illustrate

best

practices.

Thescalabilityof

theparallelcodewasinvestigate

don

an

AM

DOpte

ron

6136,usingphysicallyand

logically

shared

memory

up

to8coresperprocessor.Futu

rework

willinvestigate

ahybrid

parallel

programmingapproachforth

e3D

versionofth

eso

lverusingM

PI+

OpenM

P,andexplore

theuse

ofoth

erarchitectu

resatgreate

rscales.

1of1

AmericanInstituteofAeronauticsandAstronautics

Combined

EnvironmentTestingto

ReducePayload

Mass,Cost

and

Mission

Risk

FrankArute,Jin

Kan

g,

DrexelUniversity

Inth

esp

aceindustryto

day,exhaustiveenvironmenta

lte

stingis

performed

on

payloads

priorto

flightto

ensu

reth

atth

epayload

can

withstand

theextremeenvironment,

which

it

willbesu

bjecte

dto

upon

launch.Someofth

ese

testsincluderandom

vibration,accelera-

tion,and

shock

testing.W

ith

currentvibration

test

devices,

itis

notpossible

tosimulate

environments

such

asrandom

vibration

and

sustained

ordynamic

g-loadssimultaneously.

These

testsalso

simulate

loadsfarbeyond

actu

allaunch

environmentand

overstress

the

payload

toensu

reth

epayload

can

survivelaunch

conditions.

Usingcurrentte

stmeth

ods,

thereis

also

adegreeofuncerta

inty

inth

ete

stresu

ltsdueto

thefactth

atth

ete

stsare

only

replicatingoneportionofth

elaunchenvironmentatatime.Forexample,if

apayload

wereto

havese

nsitivese

nso

rson

board

and

they

need

tobete

sted,th

edata

they

would

record

during

testing

would

notbeexactbecause

thete

stwould

belacking

thesu

stained

gfacto

rfelt

duringlaunch.Bydevelopingacapabilityto

inte

grate

acceleration,vibration,

and

shock

testing

using

astate

-of-th

e-artcentrifuge,it

ispossible

tote

stforsy

nergistic

e!ects

ofth

ese

combined

environments.Thete

stse

tup

thathasbeen

developed

tocreate

acombined

environmentconsistsofacentrifugewith

amodalexciterand

test

fixtu

rein-

stalled

on

itsgondola.This

test

setu

pwillbeable

toprovideboth

sustained,and

dynamic

g-loads,

aswell

assimultaneousvibration

loadsin

two

independentaxes.

With

combined

environmentte

sting,it

willbepossible

toprovidea

much

morerealistic

launch

environ-

ment.

By

providing

amorerealistic

test

environment,

combined

environmentte

sting

has

thepote

ntialto

reducecost

and

risk,sa

vetime,and

increase

performance.This

prese

nta

-

tion

willhighlightth

emodelingand

analysisperformed

on

ourte

stpayload,DragonSat-1,

tohelp

predictth

ee!ects

ofcombined

environments

and

theideallocationsfordata

ac-

quisition

devicesforreal-world

testing.It

willalso

highlightth

ete

stactivitieswhich

will

beperformed

on

Octo

ber26,2012with

somepreliminary

resu

lts.

1of1

AmericanInstituteofAeronauticsandAstronautics

Mission

Design

forSatellitesin

theProxim

ityofSmall

Bodies

Martin

Ozimek,Christopher

Scott

TheJohnsHopkinsUniversity

Applied

PhysicsLaboratory

When

asa

telliteis

within

thepro

xim

ity

ofa

small

body,

such

asa

moon,astero

id,or

comet,

itstrajectory

isoften

subject

toa

complica

ted

dynamicalenvironmentwhere

the

perturb

ationsfrom

non-spherica

lgra

vity,

solar

radiation

pre

ssure

,or

third-b

ody

e!ects

beco

me

significa

nt.

These

dynamics

pose

challenges

inexploring

the

trajectory

design

trade

space

when

asa

tellite

enco

unte

rssu

chbodies.

This

analysisdeta

ilsa

robust

and

systematic

appro

ach

forgenera

ting

science

orb

itsco

nnected

by

fueloptimaltransfers

inth

esm

all

body

regim

eforboth

impulsiveand

low-thru

stpro

pulsion

systems.

Forim

pulsivesy

stems,

theClohessey-W

iltshireequationspro

videan

analytica

lmeans

toglobally

inte

rpre

tth

edesign

space

allowingadesignerto

quickly

investigate

familiesof

science

orb

itsandobta

inclose

d-form

optimaltransfers.Solutionsare

refinedwithmultiple

shooting

and

nonlinearpro

gra

mming

totransition

the

resu

ltsinto

Hill’sequations,

and

finally,

ahigh-fi

delity

ephemerismodel.

Thefinalre

sult

isan

acc

ura

teso

lution

reta

ining

theinitialdesignch

ara

cteristicswithth

epote

ntialforfu

rtherfu

elsa

vingsth

atare

available

from

exploitingth

ehigh-fi

delity

perturb

ations.

Forlow-thru

stsy

stems,

the

solution

space

issu

bstantially

expanded

due

toth

epre

s-ence

ofa

time-vary

ing

thru

stmagnitude

and

direction

forth

esp

ace

craft,re

sulting

ina

challenging

optimalco

ntrolpro

blem

betw

een

two

obits.

Pse

udosp

ectra

loptimization

has

beendemonstra

tedto

yield

robust

converg

ence

tosu

chpro

blems,

however,

explicitlypro

p-

agate

dso

lutionsare

often

soughtas“truth

”forflightmissionsdueto

higheracc

ura

cyand

smooth

,im

plementa

ble

controlhisto

ries.

We

demonstra

teth

eim

portance

ofco

nnecting

pse

udosp

ectra

lto

indirect

low-thru

sttrajectory

optimization

within

this

regim

e,where

converg

ence

isnoto

riously

challenging,and

high

acc

ura

cyis

stillso

ught.

Fro

ma

coarse

initialguess,oneca

nre

adily

obta

ina

discr

etize

doptimaltrajectory

thatfacilita

tesra

pid

converg

ence

toth

eindirect

pro

blem

via

multiple

shooting.Pre

-defined

thru

st/co

ast

arc

sare

unnece

ssary

inth

isappro

ach

and

many-revolution

transfers

aboutsm

all

bodiesare

possible.

Applica

tion

ofth

ere

sultingalgorith

mson

test

pro

blemsre

vealth

atamission

designer

isable

tora

pidly

map

outcr

iticalperform

ance

metrics(e

.g.time-of-flightand

fuelusa

ge)

forth

eentire

designsp

ace

,th

uspre

ventingth

eneedto

rely

onsu

b-optimalpointso

lutions.

There

sult

isare

peata

ble,sy

stematicappro

ach

thatfacilita

testh

ese

lection

ofsm

all-b

ody

transfertrajectoriesforagiven

mission.

1of1

AmericanInstituteofAeronauticsandAstronautics

DART-C

ONCEPT

NAVIGATION

OVERVIEW

Justin

Atchison,Mark

Jensenius

JHUAPL

TheDouble

Astero

idRedirection

Test

(DART)is

apro

pose

dco

nce

ptto

impact

asm

all

body

ina

near-Earth

binary

astero

idsy

stem.

DART

isone

part

ofth

eAstero

idIm

pact

&Deflection

Assessment(A

IDA),

ajointpro

posa

lbetw

een

NASA

and

ESA.Theprimary

goalofth

emission

isto

measu

reand

chara

cterize

akineticim

pactors

ability

todeflect

an

astero

id.There

sultsofsu

chate

stwould

haveim

plica

tionsforplaneta

rydefense

,human

space

flight,

and

near-Earth

object

(NEO)science

and

reso

urc

eutiliza

tion.

Given

many

constra

ints,th

ebinary

system

Didymos

was

selected

as

ata

rget.

The

goalofth

emission

isto

impact

the

smaller,

seco

ndary

astero

idwithin

the

system.

The

NavigationTeam

hasth

ech

allengeofdevelopingaca

pabilityto

impact

the150m

diamete

rta

rgetwithaclosingvelocity

ofro

ughly

6km/s.

Thevehicle

hasavery

narrow

field-of-view

camera

asan

optica

lpayload,and

use

sch

emicalpro

pellantforattitudeco

ntroland

delta-v

maneuvers.

The

navigation

conce

pt-of-opera

tions

isto

divide

the

trajectory

into

thre

edistinct

modes:

coast,primary

-targ

eting,andte

rminalguidance

.Duringth

eco

ast-m

ode,th

evehi-

cleis

guided

usinggro

und-b

ase

dmeasu

rements

and

commands.

When

theastero

idsy

stem

isdete

ctable

usingth

eon-b

oard

camera

,navigation

transitionsto

primary

-targ

etingmode

and

use

soptica

lnavigation

forupdate

s.Finally,

afew

hours

priorto

impact,when

the

primary

and

seco

ndary

astero

idsca

nbe

reliably

di!

ere

ntiate

d,th

esy

stem

transitionsto

auto

nomouste

rminal-guidance

mode.This

modeemployshigh-rate

sensingand

on-b

oard

guidance

algorith

msto

org

anicallymaneuverto

targ

etth

eim

agece

ntroid

ofth

ese

condary

astero

id,withouthelp

from

thegro

und.This

appro

ach

isin

contrast

totraditionalmeth

-odsth

atuse

gro

und-b

ase

dso

ftware

toperform

few

care

fully-targ

ete

dmaneuvers.In

this

case

,th

ehighclosingvelocity,sm

allta

rget,

andro

und-triplighttimedonoto!ersu

"cient

pro

cessingtimeforhumans-in-the-loop.

When

inte

rminal-guidance

mode,th

evehicle

repeate

dly

compute

sestim

ate

softh

elinearize

dze

roe!ort

missdista

nce

and

ofth

ere

maining

divert

fuel.

Using

an

appro

ach

derived

from

pro

portionalnavigation,th

evehicle

perform

smaneuvers,asnece

ssary

,to

minim

izeth

efinaldista

nce

toth

eim

agece

ntroid

ofth

eastero

id.

This

pre

senta

tion

willgive

pre

liminary

simulate

dacc

ura

ciesand

fuel-use

fornominal

and

degra

ded

appro

ach

conditions.

1of1

AmericanInstituteofAeronauticsandAstronautics

TheM

ESA+

Pro

gra

m,EducationalOutreach

,and

TheAirplanePro

ject

Arm

andNok

bak

Nyembe,

Julien

A.Hou

nzangli,SyedMan

zerHasan

,

OzinoOdharo,

Claudio

Sidi,Dim

itriTito

MontgomeryCollege-Rockville

The

MESA

(Math

,Engineering,and

Science

Ach

ievement)

Pro

gra

mhasopera

ted

inM

ontg

omery

County

for

nearly

9years.

Montg

omery

College

wasth

efirstco

mmunity

collegein

Mary

landto

create

aM

ESA

chapte

r.In

2010,in

ane!ort

tore

ach

more

students,

Mary

land

MESA,M

ontg

omery

County

PublicSch

ools,and

Montg

omery

College

agre

ed

tosh

iftitsoutreach

e!ortsth

rough

themiddle

schoolscience

curriculum,which

wasbeing

rolled

outinto

all

middle

schools

inth

eco

unty.

We

called

this

new

pro

gra

m,M

ESA+.

TheM

ESA+

Pro

gra

mhasallowed

bro

ad

participation

formiddle

schooland

high

school

students,th

eir

teach

ers,and

Montg

omery

Collegestudents.-Ambassadors

org

anized

ITco

nfere

nce

forM

iddle

Sch

oolgirls.Delivere

dinstru

ctionson:

Dre

amweaver

ALIC

Eand

Scr

atch

pro

gra

mming

-W

ork

shops

were

held

for

middle

schoolstudents

over

the

2012

SummeratM

CDelivere

dinstru

ctionsand

held

competition

on:

Sea

Perch

Calculato

rRobot-M

ESA+

Ambassadors

are

also

helping

Montg

omery

County

publicschools

sta!

with:

Thetraditionalpre

-engineeringM

ESA

pro

gra

m(loca

ted

in2middle

schools

and

2high

schools)

Theco

ord

ination

ofwork

shops&

trainingsforoth

erM

ESA+

ambassadors,

Middle

schoolstudents,and

teach

ers.

Satu

rday

Sch

ooltu

toring

Middle

Sch

oolvisitsin

classro

om

THE

AIR

PLANE

PROJECT

(compose

dofth

reete

ams)

Theory

team

oExplainsth

ePhysics

conce

pts

behind

theflyingpro

cess

Sim

ulation

team

oTra

insmembers

on

how

tofly

an

RTF

plane,using

simulation

software

.Assembly

team

oBuildsth

eaircr

aft

and

gainsan

understa

ndingofth

epurp

ose

,ofeach

componentofth

eaircr

aft.

AIR

PLANE

COM

PETIT

ION

(Futu

rePhase

ofTheAirplanePro

ject)

Use

there

search

pro

vided

by

theairplanepro

ject

crew

todevelop

specifica

tions,

challenges,

and

guidelines

forM

ESA

high

schoolco

mpetitions.

1of1

AmericanInstituteofAeronauticsandAstronautics

NovelTech

nologyforBra

nd

Pro

tection

and

Anti-C

ounterfeitingM

easu

resusingFluoro

phore

and

DNA

Sanjula

Singhal

Ward

MelvilleHighSchool

Counte

rfeitingnotonly

damagesth

enameofapro

duct

and

theeco

nomy,

butca

nalso

compro

misequality

and

e!ca

cyofpro

ducts,

such

asth

eco

unte

rfeitingofmicro

chipsuse

din

aero

space

.W

ith

this

tech

nology,

DNA

and

fluoro

phore

were

bound

tosu

bstra

testo

pro

vide

bra

nd

pro

tection.

The

DNA

isa

unique

mark

er,

while

fluoro

phore

allowsra

pid

auth

entica

tion,as

itis

aco

mpound

that

fluore

sces

under

UV

light.

Fluoro

phore

was

added

toth

esu

bstra

tevia

two

linkers,a

short

linker(n

=2)and

along

linker(n

=9).

Alinkeris

aca

rbon

chain

with

asu

perre

activegro

up

thatbindsco

mpoundsto

geth

er.

The

reactionwaste

stedonafluoro

mete

r,whichsh

owedfluoro

phore

boundto

fabric,

leadingto

optimization

ofth

ere

action.DNA

wasth

en

added

toanoth

erlinker(e

pichloro

hydrin

or

epibro

mohydrin),

andru

nonagelelectro

phore

sis.

Thelinkerwasable

tobindto

theDNA,

dete

rminedbyth

edi"

ere

nce

inmolecu

larweightofDNA

withandwithoutth

elinker.

DNA

was

also

bound

tofluoro

phore

,with

both

an

alkaline

and

acidic

reagent,

and

analyze

don

agelelectro

phore

sis.

These

reactions

pro

vide

an

anti-counte

rfeiting

tech

nology,

as

fluoro

phore

and

DNA

are

able

tobind

tolegitim

ate

pro

ducts.

These

mark

ers

are

then

dete

cted

underUV

lightand

DNA

analysis,

forra

pid

and

definiteauth

entica

tion.

1of1

AmericanInstituteofAeronauticsandAstronautics

OptimizingCurrentCollection

inM

icro

bialFuelCells

Kushagra

Singhal

SUNY

StonyBrook

Currently,th

ereis

an

energy

crisis

inth

eworld,in

which

impoverished

nationsarenot

equipped

toprovidecheap

powerto

their

inhabitants.Their

health

isjeopardized

without

access

tobasicenergyrequiredto

heatfood,sa

nitizewate

r,orevenpowerelectricaldevices.

Providing

energy

toth

ese

nationsis

very

feasible

and

cost

e!cientif

weuse

microbial

fuelcells.

These

fuelcellsuse

self

sustainingbacte

ria

asth

ebioreacto

rs,

which

provideth

e

energyto

powersm

all

electricaldevices.

Thefu

eluse

dto

powerth

ese

bioreacto

rsis

found

inwastewate

r;in

addition

tobeing

acheap,readily

available

reso

urce

which

isusu

ally

dispose

dof,

itis

alsobeneficial,

sinceth

efu

elcellsasasidee"ectprocess

and

breakdown

thewastewate

r,reducingcostsrequired

intreatm

entfacilities.

The

microorganismsform

abiofilm

on

the

anode,where

they

transfer

the

electrical

charge,so

metimeswith

theaid

ofamediato

r.From

theanode,th

eelectronsflow

through

an

exte

rnalcircuit,th

en

back

toth

efu

elcell,into

the

cath

ode,where

the

electronsare

picked

up

by

oxygen.

Oxygen

hasa

high

reduction

capacity,and

the

excess

electronsat

thecath

odereadily

reduceto

wate

r.

Acurrentlimitation

forusingmicrobialfu

elcellsasan

energy

sourceis

thelow

power

outp

ut.

This

isameliorate

dby

ouroptimization

ofth

edesign

ofth

efu

elcell.

Forth

e

electrodes,

variousmate

rials

havebeenuse

din

variousconfigurations,

suchasstainless

steel

mesh

es,

graphite

anodes,

and

graphite

brush

es.

Were

designing

microbialfu

elcellswith

electrodes

that

incorporate

nanomate

rials.

These

nanomate

rials

increase

power

outp

ut

tenfold,dueto

very

high

electricalconductivity

ofth

ese

nanoparticles,

and

their

inherent

surfaceroughness

and

largesu

rfacearea,which

ispreferred

foradhesion

with

bacte

ria.

Currently,werete

stingvariousstructu

resofcarbon:fu

llerenes,

nanoribbons,

and

nanoplate

lets.Additionallydrop

casting,vacuum-fi

ltration,and

spraycoatingofnanopar-

ticles,

all

di"

erentmeth

odsofpreparingth

eelectrodes,

isbeinganalyzed.

This

rese

arch

isan

asset

for

aeronautics

and

astronautics

for

futu

re

extrate

rrestrial

colonization

missions.

Conventionalenergy

sourcessu

ch

assu

nlight,

natu

ralgase

s,and

nuclearenergy

mightnotsu

!ce.

Itis

expensive

totransp

ortfu

els,and

building

energy

plants

would

takemany

yearsto

establish

.Asa

supplementa

ry

energy

source,microbial

fuelcells

would

lift

some

burden

for

futu

re

energy

needs,

while

providing

waste-w

ate

r

treatm

ent.

1of1

AmericanInstituteofAeronauticsandAstronautics

E!ects

ofM

odelScalingon

Sedim

entTra

nsp

ort

in

Brownout

MarkGlucksm

an-G

laser,Anya

Jon

es

University

ofMaryland

Bro

wnoutis

ahighly

coupled

aero

dynamicsand

sedim

enttransp

ort

phenomenon

that

occ

urs

when

aro

torc

raft

opera

tesovera

bed

ofloose

sedim

ent.

The

purp

ose

ofth

isre

-se

arch

isto

investigate

the

e!ects

ofscaling

on

roto

rcra

ftbro

wnout.

Currentre

search

hasfocu

sed

on

labora

tory

-sca

leexperiments

which

can

be

perform

ed

more

readily

than

full-sca

lete

sting.Thee!ectsofscalingfrom

thelabora

tory

-sca

leto

full-sca

leare

notfu

lly

understo

od.

Alabora

tory

-sca

lero

torte

sted

inwate

rin

hoverovera

sedim

entbed

was

compare

dto

similarstudiesperform

ed

inair.Testingin

wate

rallowed

forth

eexplora

tion

ofch

ara

cteristicsnotach

ievable

inair.Sim

ilarity

para

mete

rssu

chasth

eflow

velocity

tose

dim

entte

rminalvelocity

ratiowere

moved

close

rto

full-sca

lere

sultsasco

mpare

dto

lab-

ora

tory

testsin

air.Oth

erpara

mete

rssu

chasdensity

ratiowere

reduce

dasco

mpare

dto

full-and

labora

tory

-sca

lete

sting

inair.Tim

e-reso

lved

and

phase

-reso

lved

particle

image

velocimetry

(PIV

)meth

odswere

use

dto

measu

reth

evelocity

field

underth

ero

torand

chara

cterize

pattern

sofse

dim

entuplift

and

dispersion.Velocity

field

measu

rements

show

thatinstanta

neousvelocitiesca

nbemany

timesgre

ate

rth

an

time-orphase

-avera

ged

ve-

locities.

Instanta

neousvelocity

excu

rsions150%

larg

erth

anphase

-avera

gedvelocitieswere

regularly

obse

rved,and

even

more

extremedi!

ere

nce

swere

note

dbetw

een

instanta

neous

and

time-avera

ged

resu

lts.

Dual-phase

flow

visualiza

tion

showed

sedim

entuplift

focu

sed

aro

und

the

upstre

am

edge

ofpassing

vortices.

Itwasth

eorize

dth

atsh

earstre

ssesand

high

velocities,

both

tangentialand

para

llelto

the

sedim

entbed

played

importantro

les

inse

dim

entmobilization.There

fore

,similarity

para

mete

rsth

atacc

ountforth

eloca

lun-

steadych

ara

cteristic

velocities(o

pera

tionalpara

mete

rs)are

more

likely

topro

videacc

ura

tescalingth

anth

ose

thatdonot(g

eometric

para

mete

rs).

ABuck

ingham-P

ianalysiswasper-

form

ed

on

somepara

mete

rsexpected

tobeim

portantto

bro

wnout,

e.g.particle

and

fluid

density,sw

irlvelocity,vortex

stre

ngth

,se

dim

entte

rminalvelocity,and

sedim

entparticle

size

.New

scalingpara

mete

rs,su

chasmaxim

um

swirlvelocity

toparticle

term

inalvelocity

ratio

and

vortex

stre

ngth

toparticle

term

inalvelocity

and

particle

size

ratio

were

found

using

the

Buck

ingham-P

imeth

od.

Dual-phase

flow

visualiza

tion

allowed

forpre

liminary

measu

rementofbro

wnoutse

verity

asafu

nction

ofth

enew

similarity

para

mete

rs.Futu

rete

stsatinte

rmediate

valuesofth

enew

similarity

para

mete

rsmayaid

inth

edevelopmentof

apre

dictivebro

wnoutse

verity

modelca

pable

ofbridgingth

ere

sultsfrom

labora

tory

-sca

leto

full-sca

leflightenvironments.

1of1

AmericanInstituteofAeronauticsandAstronautics

LLCD

ExperimentalJitterTestingand

Model

Validation

BrandonDilworth

MIT

Lincoln

Laboratory

TheLunarLase

rCommunicationDemonstra

tion(L

LCD)pro

gra

matM

ITLinco

lnLabo-

rato

ryis

thefirstsp

ace

lase

rco

mmunicationsy

stem

forNASA.Theoptica

lco

mmunications

term

inalwillbeca

rried

into

lunarorb

itby

theLunarAtm

osp

here

and

Dust

Environment

Explore

r(L

ADEE)sp

ace

craft

which

isscheduled

tolaunch

in2013.Theprimary

goalof

theLLCD

pro

gra

mis

todemonstra

teoptica

lco

mmunicationfrom

lunarorb

itto

theEarths

surface

.Optica

lco

mmunication

systemshavemany

advanta

gesoverra

dio

frequency

(RF)sy

s-te

mswhichincludeach

ievinghigherdata

rate

susinglowersize

,weightandpower(S

WaP).

Optica

lco

mmunication

systemsre

lyon

much

narrowerbeamsth

an

RF

systemsto

ach

ieve

these

advanta

ges;

thepenality

isth

atth

eoptica

lbeam

must

havegood

stability

inord

er

tomainta

inth

eco

mmunication

link

betw

een

the

transm

istterand

rece

iver.

There

are

anumberoffactors

thatplay

aro

lein

the

stability

ofth

eoptica

lbeam,butth

efocu

sof

this

talk

ison

the

residualline-of-sight(L

OS)jitterre

sulting

from

unre

jected

space

craft

excita

tion.

During

early

pro

gra

mdevelopmentmath

ematica

lanalyse

s,starting

from

simple

hand

calculationsandevolvingth

roughco

mplexco

mputa

tionalte

chniques,

are

use

dto

driveth

edesign.

Aswith

any

type

ofanalytica

lanalyse

s,many

assumptionsare

use

dto

identify

di!

ere

ntch

ara

cteristicsofth

esy

stem.

Aspro

gra

msdevelop,th

ese

math

ematica

lmodels

are

use

dto

driveth

edesignso

there

isastro

ngdesire

tovalidate

these

models

asth

edesign

continuesto

matu

re.

Experimenta

tion

with

physica

lhard

ware

isa

common

meth

od

for

validatingmath

ematica

lmodels,includingre

sidualLOSjittermodels.TheLLCD

pro

gra

mdeveloped

ate

stbench

inord

erto

validate

there

sidualLOS

jittermodelwhich

pro

vides

higherco

nfidence

inth

eco

mputa

tionalre

sults.

This

pre

senta

tion

willpro

videan

overv

iew

ofth

eLLCD

pro

gra

m,su

mmarize

someof

the

components

ofth

eOptica

lM

odule

and

todescribe

the

e!ortsbehind

validating

the

residualLOS

jittermodelusingexperimenta

lte

chniques.

This

work

issp

onso

red

by

the

NationalAero

nautics

and

Space

Administration

under

Air

Forc

eContract

#FA8721-05-C

-0002.Opinions,

inte

rpre

tations,

conclusionsandre

com-

mendationsare

those

ofth

eauth

orand

are

notnece

ssarily

endorsed

by

theUnited

Sta

tes

Govern

ment.

1of1

AmericanInstituteofAeronauticsandAstronautics

Design

and

ControlofaCycloidal-Roto

rAircra

ft

ElenaShrestha,Moble

Benedict,Vikram

Hrishikeshavan,InderjitChopra

University

ofMaryland,CollegePark

This

rese

archdescribesth

edesignandco

ntrolofahover-ca

pable

cycloidal-ro

toraircr

aft

(Cycloco

pte

r)atM

icro

Air

Vehicle

(MAV)scale.

Cycloidalro

toris

are

volutionary

con-

ceptand

hasbeen

pro

ven

tobemore

e!cientth

an

conventionalro

tors.

Fro

ma

controls

perspective,oneadvanta

geofaCycloco

pte

ris

thatth

eth

rust

vectorofeach

cycloidalro

tor

can

beinstanta

neously

changed,th

ere

by

impro

vingth

emaneuvera

bility

ofth

eM

AV.The

hybrid

Cycloco

pte

rutilize

stw

ocy

cloidalro

tors

and

aco

nventionalro

torforth

eta

il.An

e"ective

controlstra

tegy

wasdeveloped

tosu

ccessfu

lly

demonstra

tepitch

,ro

ll,and

yaw

capabilitiesofth

eCycloco

pte

r.In

addition

toopen

loop

control,

close

dloop

controlwas

also

enabled

by

an

onboard

pro

cessorunit

equipped

with

tri-axialgyro

s,acc

elero

mete

r,micro

pro

cessor,

andwireless

communicationco

mponents.Alongwithapilot,

thefeedback

controlsy

stem

wasable

toco

ntrolth

evehicle

forastable

hover.

1of1

AmericanInstituteofAeronauticsandAstronautics

ChemiluminescenceSenso

rDevelopmentforReal-Tim

e

MonitoringofGasTurb

ineCombustorDynamics

JasonBurr

University

ofMarylandatCollegePark

Chemiluminescence

Senso

rDevelopment

for

Real-Tim

eM

onitoring

of

Gas

Turb

ine

CombustorDynamicsJaso

nBurr,Underg

raduate

Rese

archeratth

eUniversity

ofM

ary

-land Chemiluminescence

isate

chniquewidely

use

din

theco

mbustionco

mmunityto

measu

reequivalence

ratios

and

heat

release

rate

swithin

aco

mbustion

reaction.

Typically

this

involvesth

euse

ofphoto

sensitivedevicesto

measu

reth

ephoto

nic

emission

from

excite

dfree

radicals

inth

eco

mbustion

field.

These

radicals

include

CH*

and

OH*.

Pre

vious

experimenta

tion

hassh

own

CH*

and

OH*

can

bere

late

dto

the

equivalence

ratio

ofth

ere

action,whileth

elatteris

considere

dastro

ngindicato

rofheatre

lease

rate

.Common

meth

odsforgath

ering

data

relate

dto

these

emissionsinvolveeitherth

euse

ofphoto

multipliers

(PM

Ts)

oran

inte

nsified

charg

e-coupled

device(ICCD)ca

mera

.Both

isolate

thewavelength

sofCH*

and

OH*

(430

nm

and

308

nm,re

spectively)th

rough

the

use

ofopticfilters

foranalysis.

Whileth

ePM

Tis

use

dforastro

ngte

mpora

lre

solution

of

these

changesin

an

isolate

dre

gion

ofth

eflow,th

eIC

CD

camera

isco

mmonly

employed

foritssp

atialre

solution.

Inmany

configura

tionsboth

are

employed

tobenefitfrom

its

counte

rpartsweaknesses.

Regre

ttably,both

are

also

typically

only

capable

ofmeasu

ring

thetw

owavelength

sindependently.

Toso

lveth

ispro

blem,te

stsare

oftenre

-rununderth

esa

meco

nditionsto

perform

themeasu

rements

again

with

adi!

ere

ntfilter.

There

searchdiscu

ssedin

this

pre

senta

tionfocu

sesonanaltern

ativeappro

ach

:re

solving

the

tempora

lre

solution

for

both

wavelength

susing

asingle

senso

r,th

us

allowing

both

equivalence

ratioandheatre

lease

rate

measu

rements

toocc

urco

ncu

rrently.

Opticoutp

uts

from

thete

stse

ction

are

analyze

dbyadual-PM

Tsy

stem

thatinco

rpora

testh

ero

bustness

ofth

ePM

Tte

mpora

lre

solutionwithauniquese

nso

rth

atallowsfrom

somevary

ingsp

atial

reso

lution.These

designim

plementa

tionswillallow

forsimplifica

tionin

theappara

tuss

use

and

pote

ntially

furtheradvance

ments

inth

eco

mbustion

field.

Ifsu

ccessfu

l,su

chse

nso

rdevelopmentca

nlead

toa

new

opportunity

for

revolutionizing

gas-tu

rbine

combustion-

controlte

chnology

by

making

iteasier

toapply

aclose

d-loop

active

controlfor

in-situ

engineperform

ance

optimization.

Ongoingre

searchincludesth

ephysica

lmach

iningandmanufacture

ofth

ecu

rrentdesign.

Once

assembled,ca

libra

tionsto

these

nso

rwillbeach

ieved

via

amodelco

mbustor.

The

resu

ltswillhopefu

llyim

pro

veth

eabilityto

acc

ura

tely

map

theequivalence

ratioand

heat

release

rate

during

combustion

with

the

use

ofco

mbining

customized

signal-pro

cessing

opto

electro

nicswith

o!

thesh

elf

optics

and

opto

mech

anicalparts.

1of1

AmericanInstituteofAeronauticsandAstronautics

Developmentand

chara

cterization

ofatu

bular

Dielectric

ElectroActivePolymeractu

ato

rwith

a

pre-strain

mech

anism

OscarAlvarado,AlisonFlatau

University

ofMarylandCollegePark

This

rese

arch

explore

sth

edevelopmentand

chara

cteriza

tion

ofamultilayere

dtu

bular

actuato

rmadeofadielectricelastomerwithco

mpliantelectro

des.

Electro

ActivePolymers

(EAPs)

are

very

attra

ctivein

theactuato

rco

mmunity

dueto

their

muscle

likeopera

tion,

light

weight,

low

electrica

lpower

consu

mption

and

no

noise.

Dielectric

Electro

Active

Polymers

(DEAPs)

belongto

thefamily

ofEAP

inwhich

theactuation

isca

use

dby

elec-

trostatic

forc

esbetw

een

two

electro

deswhich

squeeze

the

polymerin

planardirections.

ForourDEAP

actuato

rdesigns,

an

exte

rnalmech

anism

toapply

constantuniaxialpre

-stra

inis

use

dto

incr

ease

thesu

rface

are

aofmate

rialwhilere

ducing

itsth

ickness.Base

don

Maxwellselectro

staticstre

ssequation,a

smallerth

ickness

allowsfora

larg

erelectro

-static

pre

ssure

forth

esa

me

voltage

levelapplied,hence

highermate

rialelongation.

Inth

isstudy,

the

actuato

rsare

base

don

Danfoss

PolypowerA/S

Dielectric

Electro

Active

polymer(D

EAP)mate

rial.

This

DEAP

mate

rialutilize

sasilico

ne-b

ase

delastomer,

Elas-

tocilRT

625,co

mbined

with

smart

compliantmeta

lize

delectro

de

tech

nology

inwhich

asp

ecialco

rrugate

dsu

rface

isim

printe

din

the

elastomerto

allow

elongation

inonly

the

compliantdirection.Themaxim

um

stra

inin

themate

rialis

limited

to30%.Theco

nstru

c-tion

pro

cess

ofth

ese

manually-rolled

actuato

rsis

pre

sente

d,aswell

asadiscu

ssion

ofth

edi!

ere

ntpre

-strain

mech

anismsco

nsidere

d.Strain

and

forc

edata

issh

own

foractivation

voltagesra

nging

from

0to

2500

Voltsin

which

asp

ring

base

dpre

-strain

mech

anism

isuse

d.Thre

esp

ringsofdi!

ere

ntsti!

ness

are

considere

dand

thre

epre

-strain

levels

foreach

spring

studied.

Actuato

rtransientre

sponse

toelectrica

lstim

ulusis

pre

sente

daswell

asimple

dynamic

modelth

atpre

dicts

theactuato

rsfirstmodeofvibra

tion.

1of1

AmericanInstituteofAeronauticsandAstronautics

TheCratersville

StudentContest

Gregory

Sharp,JoeCacaccio

WPI

TheCra

tersville

Stu

dentConte

st:Design

aSim

ulate

dLunarBase

Science

Exhibit

By

Jose

ph

Caca

ccio

and

Gre

gory

Sharp

Imagineth

atyou

are

a5th

gra

der,

ten

years

old,and

there

isasp

ecialSpace

Enrich

ed

Science

Educa

tion

curriculum

experimentgoing

on

inyourschool.

Thus,

inyourscience

class

whenyouare

dealingwithse

ctionsonmatter,

motion,forc

es,

lightandso

und,energ

yand

electricity

there

isan

activitydealingwith

oneofth

ech

allengesoflivingand

work

ing

on

themoon.Someofth

ese

challengesincludese

para

tingth

emeta

lsmixed

inth

ere

golith

togetbuilding

mate

rials,figuring

outhow

tominewate

rand

transp

ort

there

sulting

ice

from

the

bottom

ofa

crate

r,and

how

touse

the

reso

urc

esathand

towire

the

base

for

electricity.Sim

ple

solutionsto

these

pro

blemsare

possible

once

onehasmastere

din

the

basicco

nce

pts

inth

e5th

gra

descience

curriculum.

Then

asa

6th

gra

derth

ere

isa

unit

thatre

turn

sto

this

themeto

examineth

ebiologicalissu

es,

focu

sing

on

gre

enhouse

food,

fibers,th

ebiosp

here

and

wate

rre

pro

cessing.These

topicswillexaminehow

life

on

earth

can

bere

plica

ted

on

amuch

smallerscale

toallow

fora

self-su!cientbase

on

theM

oon.

Thestudents

willlearn

how

theM

oon

base

willhaveto

modify

tolivingco

nditionsofth

eplants

toallow

foracc

elera

ted

gro

wth

and

higheryield.A

spiralcu

rriculum

with

alunar

base

themewould

flow

from

5th

gra

deall

theway

up

toth

e9th

gra

de.Thech

allengeof

this

conte

stis

tohaveco

llegestudents

inaero

space

,architecture

,andoth

erfields,

team

up

toenvision,visualize

and

dra

wup

imagesofwhatth

isperfect

field

trip

capstoneexhibit

should

look

likeyearby

yearTheco

nte

stuse

sth

efloorplan

ofth

eW

orc

esterAuditorium

asth

esp

ace

forth

epro

pose

dexhibit.

TheW

orc

esterAuditorium,a

warmemorialbuilt

inth

e1930s,

wasch

ose

nbeca

use

ofitsvast

base

ment.

Itis

underg

round,hasmany

tight

twisting

hallways,

and

thecu

rrentbuilding

isunuse

d.W

orc

esteris

an

esp

ecially

suitable

site

dueto

thefact

thatRobert

Goddard

,th

efounderofmodern

rock

etry

inaloca

lhero

Inth

ispre

senta

tion

wewillexplain

where

theco

nte

stca

mefrom,stre

ssing

itsorigins

ina2010architectura

llunarbase

design

conte

stru

nby

Shiftb

oston.Cra

tersville

wasone

of102

entries.

Ittied

forfirston

tech

nicalfeasibility

and

elegance

,co

uld

feed

itse

lfand

pay

foritse

lf.W

ewillth

en

show

imagesofth

eAuditorium

and

go

into

ahisto

ryofwhy

Worc

estermightcr

eate

such

an

exhibit

hers,th

ough

thesp

onso

rsofth

eco

nte

stare

not

committe

dto

havingth

elunarbase

exhibit

there

.Thebase

gre

enhouse

would

pro

bably

be

atth

enearb

yTowerHillBota

nicalGard

en.In

summation,ourgoalis

topre

pare

theway

forpapers

tofollow

onwhatth

esimulate

dlunarbase

should

looklikegivenitseduca

tional

goals.If

this

curriculum/exhibit

pre

cedentdisse

minate

sit

could

beavery

big

dealforth

eaero

space

work

forc

epip

eline.

1of1

AmericanInstituteofAeronauticsandAstronautics

ASTEROID

IMPACT

AND

DEFLECTIO

NASSESSM

ENT

(AID

A)M

ISSIO

NCONCEPT

ZacharyFletcher,Andrew

Cheng

JHU/A

PL

TheEarth

isco

ntinually

bombard

ed

by

astero

ids,

themajority

ofwhich

are

very

small

and

bre

ak

up

harm

lessly

inth

eatm

osp

here

.However,

there

isalso

arisk

oflarg

escale

damagefrom

astero

idim

pacts.

Impactssu

chasth

ose

inTungusk

ain

1908,whichflattened

nearly

2000sq

uare

km

offore

stin

Russia,occ

urevery

few

hundre

dyears.

Inan

ord

erto

mitigate

theth

reatoffu

ture

impactsto

Earth,NASA

hasta

ken

resp

on-

sibility

for

conducting

asu

rvey

ofall

Near

Earth

Astero

ids(N

EA),

and

assessing

their

likelihood

toim

pact

earth.W

hileth

emajority

ofth

epopulation

oflarg

erastero

idsis

be-

lievedto

havebeendisco

vere

d,th

ere

remain

manyastero

idsth

athaveyetto

bedisco

vere

dth

atare

ofsimilarsize

toth

atofth

eTungusk

aim

pact.

Inaddition

tofinding

pote

ntially

haza

rdousastero

ids,

there

needsto

bea

meth

od

for

deflection

them

should

ahaza

rdous

object

be

found.

There

have

been

severa

loptions

discu

ssed

forhow

this

deflection

could

beacc

omplish

ed,ra

nging

from

akineticim

pact

toagra

vity

tractor.

This

pre

senta

tion

focu

seson

the

Astero

idIm

pact

and

Deflection

Assessment(A

IDA)

mission

conce

pt

that

combines

aJHU/APL

developed

conce

pt

ofth

eDouble

Astero

idRedirectionTest

(DART)sp

ace

craft

withanESA

developedco

nce

ptofth

eAstero

idIm

pact

Mission

(AIM

).TheDART

space

craft

isa

simple,low-cost

space

craft

designed

toim

pact

theastero

id65803Didymos.

Itse

rvesasate

chnology

demonstra

tion

ofakineticim

pactor,

whose

pri-

mary

goalis

todete

rmineth

ee!ectiveness

ofakineticim

pactorfordeflection

an

astero

id.

Itwillalsopro

videim

agesand

basicch

ara

cteriza

tion

ofth

eDidymosastero

idsy

stem.

TheAIM

space

craft

isalow-cost

space

craft

whichwillch

ara

cterize

andobse

rveDidymos

prior,

during

and

post

impact

with

DART.It

isan

ESA

design

base

don

the

SM

ART-1

space

craft

bus,

hosting

severa

lscience

payloads.

Itwillpro

videinsightinto

theDidymos

binary

astero

idsy

stem

andpro

videanincr

ease

dscience

retu

rnifable

toobse

rveth

eim

pact

forDART.

1of1

AmericanInstituteofAeronauticsandAstronautics

Pro

jectile

Aero

dynamics

AlistairAndrulis

WashingtonLatinPublic

Charter

School

Pro

jectileAero

dynamicsby

Alistair

Andru

lis,

Febru

ary

16,2012

Question:

Which

of3

nose

cone

shapeson

aro

cketwillhave

the

least

dra

gand

go

thefu

rthest/highest?

#1

Bullet(h

alf

sphere

w/flatbottom)#2

Sphere

;#3

TearShape

Hypoth

esis:

#3

willgo

the

furthest

and

the

highest

ofth

eth

ree

rock

ets

beca

use

itwill

bre

ak

thro

ugh

the

air

and

the

tapere

dsh

ape

willre

duce

the

dra

gbehind.

Purp

ose

:To

calculate

the

di!

ere

nce

indra

gth

atocc

urs

by

manipulation

ofonly

apro

jectilessh

ape,

keepingoth

ervariablesco

nstant.

Pro

cedure

:

1.Assemble

thero

ckets

withdi!

ere

ntsh

apednose

cones.

Conduct

2ru

nseach

ofvertical

and

45degre

eangle

testsforeach

shape.

2.Use

aca

mera

tore

cord

thero

cket’stimeforth

everticalte

st.Aftereach

rock

ethas

been

launch

ed

twice,re

cord

thedata

and

avera

geit.

3.Repeatth

ete

stru

nslaunch

ingth

ero

ckets

ata45degre

esangle.M

easu

reth

edista

nce

each

rock

ettraveled

with

string,re

cord

itfor2launch

eseach

,th

en

avera

geit.

Resu

lts/

Conclusion:

My

testing

pro

ved

my

hypoth

esis:

that

Rock

et

#3

with

its

tear-

shapednose

conewillth

egre

ate

stflightdura

tionanddista

nce

ofth

eth

reero

ckets,beca

use

itwillbre

ak

thro

ugh

theair

and

theta

pere

dsh

apewillre

duce

thedra

gbehind

thehalf-

sphere

front.

Bydoingth

ete

stsIam

able

tostate

thatth

isro

cketcr

eate

dth

eleast

amount

ofdra

gdueto

itssh

aped

conedesign.

This

rock

etoutp

erform

ed

all

ofth

eoth

erro

ckets

by

agood

marg

in.

1of1

AmericanInstituteofAeronauticsandAstronautics

SolarEnerg

yforaBrighterFutu

re!

SonyaDatta

River

HillHighSchool

This

studydete

rminedth

ee!ectofte

mperatu

reonth

eoutp

utofaso

larpanelbyheating

andcoolingth

eso

larpanelto

acerta

inte

mperatu

reandth

enmeasu

ringth

ecurrentwitha

multi-mete

r.Thehypoth

esiswas:

ifth

eso

larpanelis

cooled,th

enth

eoutp

utwillincrease

because

theconductivityin

themeta

lwould

increase

andincrease

abso

rption.Thepurpose

ofth

isprojectwasto

do

indepth

rese

arch

on

alternativesth

at,

ifputon

alarge

scale,

could

supply

energyforAmerica.Because

solarenergyis

dependentonth

esu

n,aninfinite

reso

urce,so

larenergywould

belargely

beneficialif

use

din

theUnitedSta

tes.

Peakoiland

largeenergydependencecould

beupcomingproblemsth

atprese

ntth

emse

lvesto

America,

leaving

large

gaps

inall

manufactu

ring

industries

and

everyday

life

energy

use

s.This

experim

entexpandson

ongoing

rese

arch

aboutth

emost

e"cientway

touse

solarpanels

and

increase

theenergy

they

giveo!

soth

ey

arereliable.

1of1

AmericanInstituteofAeronauticsandAstronautics

UsingDielectric

ElectroActivePolymerSenso

rsto

DetectPressure

ChangeoveraSmooth

Surface

YitAkyuz

University

ofMaryland,CollegePark

Back

gro

und:

Dielectric

Electro

Active

Polymer(D

EAP)film

isan

experimenta

lfilm

pro

duce

dby

Danfoss

Polypower.

DEAPsare

fundamenta

lly

capacito

rsth

atch

angeth

eir

capacita

nce

whenavoltageis

appliedasth

epolymeris

compre

ssedin

thickness

andexpands

inare

adueto

theelectricfield.W

hen

mech

anicallystra

ined,th

ech

angein

capacita

nce

of

the

elementis

pro

portionalto

the

stra

inand

load.

The

basicdesign

ofa

senso

rco

nsists

ofa

section

ofPolyPowerDEAP

mate

rialwith

electrica

lco

nnections.Rese

arch:Thegoal

ofourre

search

hasbeen

touse

theDEAP

film

asapre

ssure

senso

roverasm

ooth

surface

(i.e.

an

airplane

wing).

Afterpre

paring

the

senso

rs,th

ey

are

taken

toth

ewind

tunnel

forte

sting.These

nso

ris

connected

thro

ugh

an

electriccirc

uit

toaLabview

pro

gra

mth

at

can

logth

eavera

geca

pacita

nce

atany

given

time.Thewind

tunnelis

alsoco

nnected

toa

manomete

rth

atca

ndete

ctpre

ssure

changeinsideth

etu

nnel.

Asth

evelocity

inth

ewind

tunnelincr

ease

s,th

epre

ssure

insideth

etu

nneldecr

ease

s,and

theca

pacita

nce

ofourfilm

incr

ease

s.Conclusion:Id

eally,

wewould

wanta

linearre

lationsh

ipbetw

een

thepre

ssure

changeand

theca

pacita

nce

ofth

efilm

.Although

ourcu

rrenttrials

haveyielded

positive

resu

lts,

there

are

someissu

eswith

repeata

bility.

All

ofth

etrials

havesimilartrendsbut

slightlydi!

ere

ntvalues.

Thenextstep

inourre

search

isto

reduce

theSignal/Noisera

tio.

Wewillexperimentwithusingslightlyco

rrugate

dsu

rface

sto

incr

ease

theelongationofth

efilm

.W

ewillalso

use

larg

erse

nso

rs,and

variousdi!

ere

ntadhesivesto

mountth

ese

nso

r.Finally,

wewillattemptto

connect

twose

nso

rsin

para

llelto

incr

ease

theoutp

ut.

1of1

AmericanInstituteofAeronauticsandAstronautics