stss atrr ula overview
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Space Tracking and Surveillance SystemAdvanced Technology Risk Reduction
Mission Overview
Delta II 7920-10C
Vandenberg Air Force Base, CA
Space Launch Complex-2 West
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Vernon L. Thorp
NASA Program Manager
United Launch Alliance
STSS ATRR
United Launch Alliance (ULA) takes great pride in launching the Space Tracking and
Surveillance System (STSS) Advanced Technology Risk Reduction (ATRR) mission for the United
States Missile Defense Agency (MDA). STSS ATRR will be launched aboard a ULA Delta II 7920-10C
launch vehicle from Vandenberg Air Force Base (VAFB), CA.
The STSS ATRR mission is a space-based sensor component of a layered Ballistic Missile
Defense System (BMDS) to detect, track, and intercept ballistic missiles.
ULA provides the Delta II launch service under the NASA Launch Services (NLS) contract with
the NASA Kennedy Space Center Launch Services Program. We are pleased that NASA once
again selected the Delta II for this mission, after many successful commercial, foreign, andgovernment launches to Earth orbit and destinations throughout the solar system. My congrat-
ulations to the entire Delta team for its continued efforts in achieving this milestone.
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STSS ATRR
Mission Requirements Launch Period: 1 April 1 October 2009
Launch Attempts: One Daily
Launch Window: 28 minutes
Orbit: Polar, Near Circular
Second Stage Probability of Commanded Shutdown: 99.7
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First Stage
Second Stage
Graphite Epoxy
Motors GEMs
STSS ATRR SC
Payload Fairing
Guidance Section
6915 Payload Attach Fitting
Interstage
Wiring Tunnel
Centerbody Section
First-Stage Oxidizer Tank
First-Stage Fuel Tank
Payload Fairing
Delta II 7920-10C
Launch Vehicle
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7920-10C launch from Vandenberg Air Force Base SLC-2W
Flight azimuth of 196 deg
6/3 GEM solid motors firing sequence
Separation of ground-lit GEMs at 1 min, 26 sec and 1 min, 27 sec to ensureclearance of coastal oil platforms
Dog-leg maneuver (1 min, 30 sec to 2 min, 12 sec) performed to attain requiredorbital inclination
Main engine cutoff (MECO) occurs at first-stage propellant depletion; nominally at4 min, 23.4 sec after liftoff
First stage separated 8 sec after MECO; second stage ignited 5.5 sec later
Payload fairing jettisoned when free molecular heating rate 0.1 BTU/ft2-sec
(1135 W/m2) Command Receiver Decoders (CRDs) turned off at 6 min, 20.5 sec
Second stage, first burn places vehicle in initial Earth orbit
Instrumented Aircraft (IA) required for coverage of last portion of stage II burn
Flight Mode Description
Boost to Orbit
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Sequence of Events
Boost to Orbit
Event Time (HR:MIN:SEC)
Liftoff
Mach 1Maximum Dynamic PressureSolid Motor Burnout (6 ground-lit)Solid Motor Ignition (3 air-lit)Solid Motor Separation (3 ground-lit)
Solid Motor Separation (3 ground-lit)Begin Dog-leg ManeuverSolid Motor Burnout (3 air-lit)Solid Motor Separation (3 air-lit)End Dog-leg ManeuverMain Engine Cutoff (MECO)First-Stage SeparationSecond-Stage IgnitionJettison FairingTurn Off CRDsFirst Cutoff Second Stage (SECO-1)
0:00:00.0
0:00:32.40:00:45.70:00:64.00:00:65.50:01:26.0
0:01:27.00:01:30.00:02:09.70:02:11.50:02:12.00:04:23.40:04:31.40:04:36.90:04:41.00:06:20.50:10:04.6
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Flight Mode Description
Coast and Restart
Following SECO-1, vehicle reoriented to desired coast attitude
No thermal conditioning roll required
Following 28.5 min of coast, vehicle reoriented to second-stage restart burn
attitude Second-stage restart occurs at 52 min, 51.9 sec over the Hartebeesthoek, South
Africa tracking station
Restart burn duration of 21.1 sec
At end of the second stage restart burn, vehicle is in final Earth orbit Required orbit occurs at first ascending node after liftoff (1 hr, 0 min, 37.1 sec)
Following second-stage restart, vehicle reoriented to desired attitude for spacecraftseparation
Spacecraft separation will occurs at 58 min, 0.0 sec over Hartebeesthoek trackingstation
STSS ATRR uses a 6915 payload attach fitting (PAF) with a secondary latch system
PAF separation bolts released at 57 min, 30 sec, and secondary latches arereleased at 58 min, 0.0 sec separating the spacecraft
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Sequence of Events
Coast to Spacecraft Orbit Injection
Event Time (HR:MIN:SEC)
First Cutoff Second Stage (SECO-1)Maneuver to Coast AttitudeSTSS ATRR Coast PeriodManeuver to Restart AttitudeSecond-Stage Restart Ignition
Second Cutoff Second Stage (SECO-2)Maneuver to Separation AttitudeRelease Separation BoltsSeparate Spacecraft (Secondary Latch Release)
0:10:04.60:11:00.0 0:16:00.0
0:16:00.0 0:44:30.0
0:44:30.0 0:50:30.0
0:52:51.9
0:53:13.00:54:03.0 0:56:40.0
0:57:30.0
0:58:00.0
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0
30 N
60 N
90 N
30 S
60 S
90 S
180 150 W 120 W 90 W 60 W
VTS
1
IA
2
x
Orbit Trace
Boost to Orbit
Legend (time, sec)1 Main Engine Cutoff (263.4)2 SECO-1 (604.6)Telemetry SitesVTS AFSCN VandenbergIA Instrumented Aircraft
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Orbit Trace
Coast to Restart
0
30 N
60 N
90 N
30 S
60 S
90 S
0 30 E 60 E 90 E 120E
HBK
34
5
x
x
xLegend (time, sec)3 First Restart (3171.9)4 SECO-2 (3193.0)5 Spacecraft Separation (3480.0)Telemetry SitesHBK Hartebeesthoek, South Africa
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Flight Profile
Second-Stage Ignitiont = 4 min, 36.9 sec
Alt = 69.9 nmiVel = 18,957 fps
MECOt = 4 min, 23.4 sec
Alt = 65.5 nmiVel = 18,952 fps
Fairing Jettisont = 4 min, 41.0 sec
Alt = 71.1 nmiVel = 18,994 fps
Second-Stage Restartt = 52 min, 51.9 sec
Spacecraft Separationt = 58 min, 0.0 sec
SECO-2t = 53 min, 13.0 sec
t = Time from liftoffAlt = AltitudeVel = Inertial Velocity
SECO-1t = 10 min, 4.6 sec
Alt = 89.6 nmi
GEM Jettison (3)
t = 2 min, 11.5 secAlt = 30.1 nmiVel = 6,593 fps
GEM Jettison (6)t = 1 min, 26.0 sec/1 min 27.0 sec
Alt = 15.1 and 15.4 nmiVel = 3,097 and 3,160 fps
Liftoff
GEM ImpactGEM Impact
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Following spacecraft separation, second-stage retro initiated to move second stageaway from spacecraft
Relative separation velocity of 1.0 fps from retro system
Helium retro nozzles canted at 35 deg from launch vehicle centerline Following a coast of 17 min, 58 sec, vehicle reoriented to second-stage evasive burn
attitude
5-second burn provides additional separation between second stage and thespacecraft
Following evasive burn maneuver, vehicle reoriented to second-stage depletionburn attitude
Second-stage depletion burn occurs at 1 hr, 43 min, and 20 sec over the Hawaiitracking station
Nominal burn duration of 1min, 34.2 sec At end of nominal depletion burn, second stage in a 97 x 480 nmi (180 x 889 km)
orbit with an inclination of 112.78 deg
Second-stage maneuvers and depletion burn following STSS ATRR separation
ensure a worst case spacecraft contamination level of
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Sequence of Events
Post Separation
Event Time (HR:MIN:SEC)
Separate Spacecraft
Begin Second-Stage RetroEnd Second-Stage Retro
Maneuver to Evasive Burn Attitude
Second-Stage Evasive Burn Ignition
Second Cutoff Second Stage (SECO-3)
Maneuver to Depletion Burn Attitude
Second-Stage Restart Ignition (Depletion Burn)
Depletion Cutoff Second Stage (SECO-4)
0:58:00.0
0:58:00.50:58:42.0
1:16:40.0 1:25:40.0
1:30:00.0
1:30:05.0
1:33:00.00 1:41:40.0
1:43:20.0
1:44:54.2
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30 N
0
30 W
120 W
90 W
60 W
60 N
150 W
180
150 E
0
90 N
HTS
TTSTSTTS
98
7 6
xx
xx
Legend (time, sec)
6 Evasive Burn Ignition (5,400.0)7 SECO-3 (5,405.0)8 Depletion Burn Ignition (6,200.0)9 SECO-4 (6,294.2)Telemetry SitesTTS Thule, GreenlandHTS Hawaii
Orbit Trace
Post Separation
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Delta II Countdown (T-0 Day)
L-18 L-16 L-14 L-12 L-10 L-8 L-6 L-4 L-2 L-0
SUPPORT
L-20H
S/C OP
PAD CLOSED
MEETING
DELTA TASK
HAZ OP
PAD CLOSEDESSENTIAL PERSONNEL
RANGE OP
S/C OP
PAD CLOSED
MEETING
DELTA TASK
HAZ OP
PAD CLOSEDESSENTIAL PERSONNEL
RANGE OP
V1T1 BRIEFING
CAMERA SETUP (PHOTO SQUADRON)
V1T1 MST MOVE PREPS
HEATED RP-1 RE-CIRCULATE A/R
AIR COND SETUPS
BUILT IN HOLD (60 MINS)
(V1T3) TERM'L COUNT
PREP SM TLX CONN & ISDS PIN PULL
LANYARD TENSIONING
FAIRING AND WHITEROOM PREPS
V1T2 S/M TLX CONN. & ISDS PIN PULL
V1T2 LAUNCH MOUNT SECURING
ILC
PHOTO OP
ALL PERSONNEL CLEAR SLC-2W
MST REMOVAL & SECURING
V57 ITEM 15 P.C. SECURING
OD TEST 80
421, 2241.5, 5690.0, 5765.0 MHZ
SLC-2W AREA CONDITIONS
A/C & VAPOR DET WATCH (V41)
FINAL S/C ACCESS PRIOR TO LAUNCH
V1T1 ENGR WALKDOWN
S/C COUNTDOWN & LAUNCH PREPS
S/C FINAL PAD CLOSEOUTS
CDPS HEALTH CHECKS
WEATHER BRIEFING FOR MST REMOVAL
V1T1 PROP ENGR WALKDOWN
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L-180T-150(2:30)
CSO CLEAR MISSILE HAZARD AREA
2ND STG HEX FILL & INITIAL PRESS TO 1100 PSIG
RIFCA TURN ON
FIRST STAGE FUELING
WEATHER BRIEFING
C-BAND BEACON CHKS TASK 03B
COMMAND RECEIVER CHECKS
COMMAND CARRIER ON
FIRST STAGE HYD ON
LOX LOADING & DECAY CHKS
2nd STG He, N2 & TANKS PRESS
130(2:10)
120(2:00)
110(1:50)
100(1:40)
90(1:30)
80(1:20)
70(1:10)
60 50 40 30 20 10 4 4 0
LAUNCH
TERMINAL COUNTDOWN INITIATION & BRIEFING
140(2:20)
AIR COND HIGH HEAT ON
SOUND EMERGENCY EVACUATION KLAXON
VEHICLE ARM
15
VEHICLE ENGINE SLEWS
1ST STG HE & N2 PRESS60
MIN
BUILT
IN
HOLD
AT
T-150
MIN
10
MIN
BUILT
IN
HOLD
AT
T-4
MIN
10
MIN
BUILT
IN
HOLD
AT
T-4
MIN
170 160 150 140 130 120 110 100 90 80 70 60 50 30 20 14 4 04015
20
MIN
BUILT
IN
HOLD
AT
T-15
MIN
PRESSURIZE FUEL TANK
SPACECRAFT LAUNCH READY (T-3 MIN)
S/C SWITCH TO INTERNAL (L-12 MIN)
TOP OFF HE & N2
STATUS CHECKS
RF LINK CHECKS
VEHICLE TRANSFER INTERNALS/C COUNTDOWN
S/C TRICKLE CHG
Delta II Terminal Count (T-0 Day)
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Delta II Operational
Flow at Western Range
Graphite-Epoxy Motors
PCM
Magna, UT
CRD RIFCA
L3 CommunicationsSpace & NavigationDivision
Teterboro, NJcommunications
L
Second Stage
Sacramento, CA
Ordnance shippeddirectly to WRrom vendors
VAFB
CCAFS
Western
Range VAFB
Launch Processing
ITIP Engine
Major Subcontractor
Major Component Flow
Delta ProgramEngineering SupportHuntington Beach, CA
Canoga Park, CA
Pratt & Whitney Rocketdyne
L3 CommunicationsCincinnati Electronics
Cincinnati, OH
RS-27 Engine
Composite FairingAlliant Techsystems
Luka, MS
Second Stage
Launch VehicleAssemblyDecatur, AL
Albuquerque, NM
Goodrich Aerospace
El Paso, TX
HeadquartersLittleton, CO
First Stage, Interstage, PLFFirst- and
Second-StageTank Assembly
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Vehicle Processing Erect and mate
First stage Interstage Solid motors Second stage
Erect and store airing Align solid motors Interace checkout
Simulate fight test Countdown preparationSC Mate andIntegrated Testing Flight program verication Ordnance installations Mate airing Second-stage propellant load RIFCA, beacon, and RS checkTerminal Countdown and Launch
SC Processing Facility SC receiving inspection DPAF receives inspection Checkout and install ordnance Pressurize Load hydrazine Mate SCs to DPAF Weigh Spacecrat
Encapsulate SC/DPAF assembly
Spacecrat (SC)
Interstage
Second stage
First stage
Solid motors Solid Motor Building 1670 Receive and inspect Solid motor buildup Leak-check motor Install nose cone
Inspect grain
Solid Motors Transport to SLC-2
Building 836 South VAFB Ofoad stages and dispenser
Receive inspection/storage Transport rst stage andsecond stage to HPF
Transport interstages to SLC-2 Ofoad airing, install LEA,
and transport to SLC-2 Transport dispenser to SC
processing acility
Hazardous ProcessingFacility (HPF)
First-Stage Processing Receive inspection Destruct installation Transport to SLC-2
Second-Stage Processing Receiving inspection Nozzle installation Destruct installation Transport to SLC-2
Fairing
Transport SCassembly to SLC-2
Total Vehicle Integration
& Checkout at the Launch Site
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