March 22, 2007

Timothy B. Bendel, PresidentMark Marasch

Shariar “Jack” GhalamJim Amos

Space Access Society2007

Team

What We Do

• Frontier Astronautics is a mild-mannered subcontractor, supplying the burgeoning Entrepreneurial Space industry with hard to obtain technology– Attitude Control Systems– Rocket Engines– Rocket Propellants– Test Facilities

Attitude Control Systems

• Attitude Control Systems (“Guidance Systems”)

– Classical vs. State Space design

• Classical– Typically considers each axis independently (single input, single

output or SISO), cross coupling is fudged– Uses “Transfer Functions”; no modeling of internal physics– Uses relatively simple control laws (integrals and derivatives)

• State Space– Originally developed by Soviet space program– Correctly models multiple input multiple output (MIMO) systems– Models system physics using a set of simultaneous differential

equations (can be linear and non-linear)– Control law solutions are inherently coupled and model the entire

system more accurately

State Space vs. Classical ACS

• Boeing Delta 2 ACS was modified for Delta 3

Notice the similarities of the two launch vehicles. Boeing felt that they could modify the Delta 2 guidance system to work on the Delta 3

• The Result:

State Space vs. Classical ACS

• A roll oscillation mode, never before the primary oscillation mode for the Delta 2, became the primary oscillation mode for the Delta 3 due to the larger strap on solid rockets

• Guidance system misinterpreted this oscillation as a disturbance, and expended all of its hydraulic fluid trying to fight it

• This could not have happened if a State Space model were used as the simultaneous differential equation modeling of the kinematics of the vehicle would automatically take this into account (Disclaimer: I have never worked for Boeing, but the explanation of the failure belies the problem)

• A very similar failure occurred when Arianespace used a modified Ariane 4 control system on an Ariane 5

– Attitude Control Systems

• We can provide complete Attitude Control Systems for your prototype vehicle

– Inertial guidance

– GPS

– State Space theory, full state feedback design

– State Estimator design

Attitude Control Systems

Masten XA-0.1 ACS

• Pilot will command vehicle rates to the ACS• GPS data used to correct IMU for drift• GPS also used to guide pilot to target• To be flown for the Lunar Lander Challenge• Masten XA-0.1 is the prototype for their

suborbital space vehicle

Masten XA-0.1 ACS

• Masten XA-0.1 has four engines located on the circumference of the base

X

Y

Z

y

x

z

g

Aeropressure

Engine thrusts

Hinge angle, α,15º max

Engines may hinge in one plane(not gimbal) tangent to the

cylinder body, ±15 degrees off axis

ConstraintHinge mount angle, β, fixed(assume 0º)

β

α

Fixed hinge mount angle, β,0º

System to be controlled

Masten XA-0.1 ACS

g

F

Fz

Fx

g

Md Mh

Lateral flight for a typical VTVL rocket

Lateral flight for Masten XA-0.1

Md: Moment due to differential thrustMh: Moment due to hinge angleMd = Mh

Engines are individually throttled and hinged

Fx

• Frontier Astronautics’ design allows an ACS to accelerate the vehicle laterally without tipping the vehicle

• This “Crabbing” maneuver helps landing on rough terrain as well as terminal landing accuracy

Masten XA-0.1 ACS

g

Md Mh

Fx

• Frontier Astronautics’ design allows an ACS to accelerate the vehicle laterally without tipping the vehicle

• This “Crabbing” maneuver helps landing on rough terrain as well as terminal landing accuracy

g

Md Mh

Fz

g

Md Mh

Fx

g

Md Mh

Fz

g

Md Mh

Fz

g

Md Mh

Fz

g

Md Mh

Fz

Attitude Control Systems

• ACS Simulation

SpeedUp ACS

• SpeedUp Lunar Lander Challenge vehicle

• “Laramie Rose”• Prototype vehicle to

prove concept of SpeedUp’s “Flying Motorcycle”

SpeedUp ACS

g

F

Fz

Fx

Lateral flight for “Laramie Rose”

• Frontier Astronautics’ design allows for accurate landing on a pre-determined location

• Hands-off flight • Three control vanes

g

F

Fz

Fx

AccelerationConstant Velocity

Deceleration

Stationary Hover Over Landing Pad

Landing location is known so ACS can initiate brake at the correct time

FF

nozzle

vane

SpeedUp ACS

• “Pilot” presses button• Vehicle flies a pre-programmed trajectory• GPS used to correct IMU for drift

mm

m

Rocket Engines

• Viper™ engine– Pressure fed LOX/Kerosene – 7500 lbf thrust

• Designed to be clustered for 30,000 lbf

– Removable inexpensive ablative liner– Low injector pressure drop allows lighter

flight system (tanks)

Viper™ Engine

Viper™ Engine

• Modular design for ease of maintenance

• Ablative nozzle designed to be replaced in minutes for fast turn around flights

• Patent Office notice of publication granted, to be published 4/12/07

• We are willing to license this technology

Viper™ Engine

• Injector designed for stable combustion despite having a low pressure drop across the injector face

• This allows the use of a pressure fed system (no turbo pump) without heavy propellant tanks

Viper™ Engine

• General Concept:– Dimension injector for harmonics to destructively

interfere– Combustion instability is mitigated without the need

to have a large injector pressure drop

Viper™ Engine

• Helmholtz resonators located around periphery of injector face• The resonators damp the tangential, longitudinal and radial primary frequencies• Used on Shuttle OMS engines

• Spintle™ is also dimensioned to damp the tangential, longitudinal and radial primary frequencies

• Fuel and oxidizer is injected to mix at the half-integer of the primary wavelength as well

• This results in combustion oscillations being damped before they have a chance to amplify and affect the engine

Rocket Engines

• Asp™: engine– Pressure fed hydrogen peroxide– 1500 lbf thrust– Uses a dual catalyst for rapid warm up– Does not need the catalyst pack to be

loaded under pressure by hydraulic press; lowers servicing requirements

– Design reduces hydrogen peroxide blow-by (wasted energy)

– Throttle Range: 300 lbf to 1500 lbf

Asp™ Engine

• Frontier Astronautics designed, built and tested the Asp™ Rocket Engine for SpeedUp

• 80% - 99% Hydrogen Peroxide• Catalyst pack does not require compression loading• Design reduces hydrogen peroxide blow-by (wasted

energy)• Throttle Range: 300 lbf to 1500 lbf

-insert picture here-

Asp™ Engine

– Vertical Engine Test

Insert Asp picture / mpg here

Services

Vehicle Design, Assembly and Testing

SpeedUp’s “Laramie Rose”

Site Services

– Test your rocket engines• Engine testing: horizontal

Site Services

– Engine testing: vertical

Site Services

Services AvailableFull vehicle testing (hardware in the loop)

• Vehicle ACS is tested simultaneously with engine test

• Hardware performance is measured, not simulated, to validate the ACS design prior to flight

Propellants

Hydrogen peroxide production

• This would not our sole product so we will be available for the smaller company

• We are currently firing rocket motors using imported hydrogen peroxide

• We will invest in equipment to produce it ourselves if we can develop an anchor customer(s)

Insert picture of h2o2

Site Services

– Main Shop Area

Insert picture of shop

Research and Development

• Propellant Research

47-ton Blast Door

Drive-in capability

Site Services

– Services Available• Machining assistance• Secure storage space available for rent

– SpeedUp currently on lease– 90% of storage space is still available– Intellectual Property will be maintained

• Test flights– Started the application to FAA/AST for Suborbital test

license – Wyoming Economic Development Council supports idea

of Private Spaceport– Launch support

Site Services

Site Services

Launch License

“Plans for future infrastructure include a functioning2,225,000-newton (500,000-pound-force)vertical test stand for engine testing, a horizontalengine test stand, up to three vertical launch pads,on-site machine shop, and shooting range.”

Federal Aviation Administration Office of Commercial Space Transportation

Contact Information

• www.FrontierAstronautics.com

• Info@FrontierAstronautics.com

• Phone: 307-331-3043

• FAX: 866-867-3701