stss atrr ula overview

8/3/2019 STSS ATRR ULA Overview

1/20

Space Tracking and Surveillance SystemAdvanced Technology Risk Reduction

Mission Overview

Delta II 7920-10C

Vandenberg Air Force Base, CA

Space Launch Complex-2 West


2/20


3/20

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.


4/20

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


5/20

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


6/20

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


7/20

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


8/20

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


9/20

Sequence of Events

Coast to Spacecraft Orbit Injection


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


10/20

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


11/20

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


12/20

Flight Profile

Second-Stage Ignitiont = 4 min, 36.9 sec

Alt = 69.9 nmiVel = 18,957 fps

MECOt = 4 min, 23.4 sec


Fairing Jettisont = 4 min, 41.0 sec


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


13/20

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


14/20

Sequence of Events

Post Separation


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


15/20

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


16/20

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


17/20

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)


18/20

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


19/20

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

stss atrr ula overview

Documents