Ocean Surface Topography Mission (OSTM/Jason-2) · United Launch Alliance (ULA) is proud to launch the OSTM/Jason-2 mission. Jason-2 will be launched aboard a Delta II 7320 launch

Ocean Surface Topography Mission(OSTM/Jason-2)Mission Overview

Delta II 7320Vandenberg Air Force Base, CASpace Launch Complex-2 West

United Launch Alliance (ULA) is proud to launch the OSTM/Jason-2 mission. Jason-2 will belaunched aboard a Delta II 7320 launch vehicle from Vandenberg Air Force Base (VAFB), California.The launch vehicle will deliver the Jason-2 spacecraft into a low-Earth orbit, where it will begin itsmission to acquire topographical measurements of ninety-five percent of the Earth’s ice-freeoceans.

ULA provides the Delta II launch service under the NASA Launch Services (NLS) contract with theNASA Kennedy Space Center Launch Services Program. We are delighted that NASA has chosenthe Delta II for this international-partnered mission between the Jet Propulsion Laboratory (JPL) andthe French Centre National d’Etudes Spatiales (CNES). I congratulate the entire team for their sig-nificant efforts that resulted in achieving this milestone. ULA looks forward to continued launchesof scientific space missions.

Kristen T. WalshDirector, NASA Programs

Delta Launch Vehicles

OSTM

• Based on Alcatel's Proteus bus

• Total mass: 505.9 kg (1115.3 lbs)

• Power: 500W

• Reaction wheels and magnetic torque rods maintain three-axis stabilization and nadir-pointing

• Hydrazine propellant system provides orbital maintenance

OSTM/Jason-2 Spacecraft

OSTM/Jason-2 Science Objectives

• Extend the time series of ocean surface topography measurements beyond TOPEX/Poseidon (T/P)and Jason-1 to accomplish two decades of observation

• Provide a minimum of three years measurement of global ocean surface topography

• Determine the variability of ocean circulation at decadal time scales from combined data recordwith T/P and Jason

• Improve the measure of time-averaged ocean circulation

• Improve the measure of global sea-level change

• Improve open ocean tide models

OSTM/Jason-2 Orbit Description

• Altitude: 1336 km

• Orbit: circular, non-sun-synchronous, 66° nominal inclination

• Global data coverage between 66°N and 66°S latitude

• 10-day repeat of ground track (±1-km accuracy)

• Coverage of 95% of ice-free oceans every ten days

OSTM/Jason-2 Payload Sensors

• CNES Poseidon-3 altimeter (C- and Ku-band) measures height above sea surface

• NASA Advanced Microwave Radiometer (AMR) three-frequency radiometer measures total watervapor along altimeter path to correct for pulse delay

• CNES Doppler Orbitography and Radiopositioning Integrated by Satellite (DORIS) Doppler trackingantenna receives ground signals for precise orbit determination, satellite tracking, and ionospheic correction data for CNES altimeter

• NASA Global Positioning System Payload (GPSP) receiver provides precise orbit ephemeris data

• NASA Laser Retroreflector Array (LRA) works with ground stations to track satellite and calibratethe other satellite location systems, and verify altimeter measurements

• Initial Launch Opportunity 15 June 2008

• Launch Window- Daily nine-minute window- Launch time ~ 1:47am PDT on 15 June 2008- Launch time moves about 12 minutes earlier each day

• Spacecraft Mass 505.9 kg (1115.3 lb)

• Orbit Requirements (defined at first ascending node after spacecraft separation) - Semi-Major Axis 7711.594 km (4163.928 nmi)- Eccentricity 0.000502- Inclination 66.0501 deg- Argument of Perigee 10.979 deg- Earth-Fixed Longitude (+West) -60.312 deg

• Coast Phase Thermal Conditioning- Rotation axis (+XLV) perpendicular to the orbit plane- Angle between sun direction and roll axis between 0 and 93 deg

• Spacecraft Separation Orientation and Time- +ZSC (+YLV) nadir- Pointing error less than 30 deg from the separation direction - Minimum seven minutes of visibility from Hartebeesthoek tracking station after separation

OSTM/Jason-2 Mission Requirements

Delta II 7320-10C

First Stage

Second Stage

Solid Motors

Jason-2 spacecraft

Payload Fairing

Guidance Section

3715 Payload Attach Fitting

Interstage

Wiring Tunnel

Centerbody Section

First Stage OxidizerTank

First Stage Fuel Tank

Second Stage Miniskirtand Support Truss

Nitrogen SpheresHelium Spheres

Payload Fairing

• Launch from VAFB SLC-2W down a flight azimuth of 196 deg

• Three solid motors ignited at liftoff, jettisoned at 1 min, 39 seconds

• Dog-leg maneuver (1 min, 40 sec to 2 min, 20 sec) performed to attain required orbital inclination

• Main engine cutoff (MECO) occurs approximately 4 min, 24 seconds after liftoff

• Stage II separated 8 seconds after MECO; ignited 5.5 seconds later

• Payload fairing jettisoned when free molecular heating rate ≤ 0.10 BTU/ft2-sec

• Command receiver decoders (CRDs) turned off at 7 min, 31 sec

• Second stage first burn places vehicle in a 100 x 763-nmi (185 x 1414-km) orbit at 66.47-deginclination

• Following SECO-1, vehicle is reoriented to perform coast phase thermal maneuvers- Rotation axis (+XLV) perpendicular to the orbit plane- 1 deg/sec nominal roll rate, with direction reversed halfway through the maneuver- Angle between sun direction and roll axis between 0 and 93 deg

OSTM/Jason-2 Flight Mode Description

Sequence of EventsBoost to Orbit

Event Time (HR:MIN:SEC)

LiftoffMaximum dynamic pressure3 Solid motors burnoutJettison 3 solid motorsBegin dog-leg maneuverEnd dog-leg maneuverMECOStage I/II separationStage II ignitionJettison fairingTurn off command receiver decoders (CRDs)First cutoff - Second Stage (SECO 1)Begin maneuver to coast attitudeEnd maneuver to coast attitudeBegin coast phase thermal rollEnd coast phase thermal roll

0:00:00.00:00:48.30:01:04.00:01:39.00:01:40.00:02:20.00:04:24.20:04:32.20:04:37.70:04:54.00:07:31.00:10:27.40:12:20.00:17:20.00:17:30.00:37:40.0

• First second stage restart begins at 48 min, 50.5 sec- Occurs in view of Hartebeesthoek tracking station - Burn duration of 24.2 sec- At end of restart burn, vehicle in an orbit of 711 x 718 nmi (1317 x 1329 km) with an

inclination of 66.03 deg

• Following SECO-2, second stage is reoriented for Jason-2 separation in view ofHartebeesthoek tracking station- Spacecraft is separated 55 min after liftoff

• Separation velocity provided by spring separation system- +ZSC (+YLV) nadir nominally- Spacecraft reaches first ascending node approximately 1 hr, 6 min after liftoff, at which

point the orbit requirements are met

OSTM/Jason-2 Flight Mode Description (continued)

Sequence of EventsRestart to Spacecraft Orbit Injection


Begin maneuver to restart attitudeEnd maneuver to restart attitudeRestart Second StageSecond Cutoff - Second Stage (SECO 2) Begin maneuver to separation attitudeEnd maneuver to separation attitudeSeparate Jason-2 spacecraftJason-2 reaches ascending node

0:38:20.00:46:40.00:48:50.50:49:14.70:50:30.00:53:00.00:55:00.01:06:07.3

OSTM/Jason-2 Flight Mode Description (continued)

• Following Jason-2 separation, second stage is reoriented for cold gas evasive maneuver (CGEM)- CGEM is 25 seconds long, beginning at 1 hr, 10 min, 50 sec after liftoff

• Increases separation distance between spacecraft and second stage in preparation forevasive burn

• Velocity of 1.1 fps imparted to second stage

• Restart burn to raise apogee begins at 1 hr, 35 min in view of Poker Flats tracking station- Burn duration of 31 seconds- At end of restart burn, vehicle in an orbit of 715 x 2295 nmi (1324 x 4250 km) with an

inclination of 65.84 deg

• Following restart burn, second stage is reoriented for depletion burn to raise perigee- Depletion burn begins 2 hr, 4 min, 10 sec after liftoff, in view of VAFB tracking station- Nominal burn time is 41.4 seconds- At end of nominal depletion burn, second stage in a 1332 x 2605-nmi (2468 x 4824-km)

orbit at 64.91-deg inclination

Sequence of EventsPost Separation


Begin maneuver to cold gas evasive attitudeEnd maneuver to cold gas evasive attitudeBegin CGEMEnd CGEMBegin maneuver to evasive burn attitudeEnd maneuver to evasive burn attitudeRestart Second Stage - evasive burnThird Cutoff - Second Stage (SECO 3)Begin maneuver to depletion burn attitudeEnd maneuver to depletion burn attitudeRestart Second Stage - depletion burnDepletion Cutoff - Second Stage (SECO 4)

1:01:40.01:10:40.01:10:50.01:11:15.01:23:20.01:32:30.01:35:00.01:35:31.01:38:20.01:48:20.02:04:10.02:04:51.4

Flight Profile

Liftoff

Solid Motor Impact

Solid Motor Burnout (3)

t = 1 min, 4.0 secAlt = 9.1 nmi (16.8 km)V1 = 2,160 fps (658 mps)

Solid Motor Jettison (3)

t = 1 min, 39.0 secAlt = 18.0 nmi (33.4 km)V1 = 2,559 fps (780 mps)

MECO

t = 4 min, 24.2 secAlt = 56.9 nmi (105.4 km)V1 = 16,424 fps (5,006 mps)

Second Stage Ignition


Payload Fairing Jettison


SECO 1

t = 10 min, 27.4 secAlt = 108.3 nmi (200.6 km)VI = 26,586 fps (8,103 mps)

ORBIT:

100 x 763 nmi (185 x 1,414 km)66.47 deg-inclination

SECO 2

t = 49 min, 14.7 secAlt = 723.7 nmi (1,340.4 km)V1 = 23,586 fps (8,103 mps)

ORBIT:

711 x 718 nmi (1,317 x 1,329 km)66.03 deg-inclination

Jason-2 Separation

t = 55 min, 0.0 secAlt = 721.0 nmi (1,335.4 km)V1 = 23,593 fps (7,191 mps)

Jason-2 ORBIT:


Jason-2 at Asc Node

t = 1 hr, 6 min, 7.3 secAlt = 718.0 nmi (1,329.7 km)V1 = 23,599 fps (7,193 mps)

Jason-2 ORBIT at Asc Node:


Evasive and

Depletion Burns:

Remove Stage 2 from

vicinity of spacecraft

0

30 N

60 N

90 N

30 S

60 S

90 S

180 150 W 120 W 90 W 60 W

VTSx1

MTx 2

Ground TraceBoost to Orbit

Events (Time After Liftoff, hr:min:sec)1 = MECO (0:04:24.2) 2 = SECO 1 (0:10:27.4)

T/M Tracking StationsVTS = Vandenberg AFBMT = Mobile Telemetry

0

30 N

60 N

90 N

30 S

60 S

90 S

0 30 E 60 E 90 E 120E

HBK

34

5

xx

x

Ground TraceRestart to Spacecraft Separation

Events (Time After Liftoff, hr:min:sec)3 = Restart Ignition (0:48:50.5) 4 = SECO 2 (0:49:14.7)5 = Jason-2 Separation (0:55:00.0)

T/M Tracking StationsHBK = Hartebeesthoek, South Africa

30 N

0

30 W

120 W

90 W

60 W

60 N

150 W

180

150 E

0

90 N

FCS

VTS

3

7

9

6

8

x

x

xx

x

Ground TracePost-Separation

Events (Time After Liftoff, hr:min:sec)6 = Evasive Burn Restart (1:35:00.0) 7 = SECO 3 (1:35:31.0) 8 = Depletion Restart (2:04:10.0)9 = Depletion Cutoff (2:04:51.4)

T/M Tracking StationsFGS = Poker Flats, AlaskaVTS = Vandenberg AFB

0800 1000 1200 1400 1600 1800 2000 2200 0000 0200 0400

SUPPORT

0600

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

0600

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 PULLLANYARD TENSIONING

FAIRING AND WHITEROOM PREPS

V1T2 S/M TLX CONN. & ISDS PIN PULLV1T2 LAUNCH MOUNT SECURING

WEATHER BRIEFING FOR MST REMOVAL

01:47:17 PDT LAUNCH

PHOTO OP (1630 - 1730)

ALL PERSONNEL CLEAR SLC-2W

MST REMOVAL& SECURING

V57 ITEM 15 P.C. SECURING

OD TEST 80416.5, 2241.5, 5690.0, 5765.0 MHZ

SLC-2W AREA CONDITIONS

A/C & VAPOR DET WATCH (V41)

FINAL S/C ACCESS PRIOR TO LAUNCHV1T1 ENGINEERING WALKDOWN

S/C CURRENT COMPENSATION

S/C CLOSEOUTS/RF HAT REMOVAL

SECURE EEB DOOR

Delta II Countdown (T-0 Day)

Delta II Terminal Count (T-0 Day)

L-180

GMT (HH:MM:SS OR HHMM)

T-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 CHECKSCOMMAND 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

22:47:17 2307 2317 2327 2337 2347 2357 0007 0017 0027 0037 00472257 0057 0127 01:47:17

SOUND EMERGENCY EVACUATION KLAXON

VEHICLE ARM

08:47:170843

0833082708170747073707270717070706570647063706270617060705:47:17

15

0117

07570557

VEHICLE ENGINE SLEWS

1ST STG HE & N2 PRESS

0133

OPEN CLOSE

LAUNCH WINDOW

GMTLOCAL

08:56:1701:56:17

9 MINUTE LAUNCH WINDOW

08:47:1701:47:17

60MIN

BUILTIN

HOLD

ATT-150MIN

10MIN

BUILTIN

HOLD

ATT-4MIN

10MIN

BUILTIN

HOLD

ATT-4MIN

170 160 150 140 130 120 110 100 90 80 70 60 50 30 20 14 4 04015

20MIN

BUILTIN

HOLD

ATT-15MIN

PRESSURIZE FUEL TANK

SPACECRAFT LAUNCH READY (T-3 MIN)

S/C SWITCH TO INTERNAL (L-20 MIN)

TOP OFF HE & N2

STATUS CHECKS

RF LINK CHECKS

VEHICLE TRANSFER INTERNALS/C COUNTDOWN

0807

S/C CURRENT COMPENSATION

0107

NOTE: TIME INDICATIONS ARE ABBREVIATED – I.E., T-100 ISACTUALLY 06:37:17 GMT

PDT (HH:MM:SS OR HHMM)

Graphite-Epoxy Motors

PCM

Magna, Utah

CRD RIFCA

L3 CommunicationsSpace & NavigationDivision

Teterboro, NJcommunications

L

Second Stage

Sacramento, CA

Ordnance shippeddirectly to WRfrom vendors

VAFB

CCAFS

WesternRange VAFB

Launch Processing

ITIP Engine

Guidance

Major Subcontractor

Major Component Flow

Delta ProgramEngineering SupportHuntington Beach, CA

Canoga Park, CA

Pratt & Whitney Rocketdyne

L3 CommunicationsCincinnati Electronics

Cincinnati, Ohio

RS-27 Engine

Composite FairingAlliant Techsystems

Iuka, Mississippi

Second Stage

Launch VehicleAssembly

Decatur, Alabama

Albuquerque, New Mexico

Goodrich Aerospace

El Paso, Texas

HeadquartersLittleton, CO

First Stage, Interstage, PLFFirst- and

Second-StageTank Assembly

Delta II Operational Flowat Western Range

Vehicle Processing• Erect and mate – First stage – Interstage – Solid motors – Second stage• Erect and store fairing• Align solid motors• Interface checkout• Simulate flight test• Countdown preparationSV/DPAF Mate andIntegrated Testing• Mate SV/DPAF assembly• Flight program verification• Ordnance installations• Mate fairing• Second-stage propellant loading• RIFCA, beacon, and RS checks

Terminal Countdown and Launch

AstrotechSV Processing Facility• SV receiving inspection• DPAF receiving inspection• Checkout and install ordnance• Pressurize• Load hydrazine• Mate SVs to DPAF• Weigh Spacecraft• Encapsulate SV/DPAF assembly

• Space vehicle (SV)

• 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• Offload stages and dispenser• Receiving inspection/storage• Transport first stage and second stage to HPF• Transport interstages to SLC-2• Offload fairing, install LEA, and transport to SLC-2• Transport dispenser to SV processing facility

Hazardous ProcessingFacility (HPF)First-Stage Processing• Receiving inspection• Destruct installation• Transport to SLC-2

Second Stage Processing• Receiving inspection• Nozzle installation• Destruct installation• Transport to SLC-2

• Fairing

• DPAF

• Transport SV/DPAF assembly to SLC-2

Total Vehicle Integration & Checkout at the Launch Site

Copyright © 2008 United Launch Alliance, LLC. All Rights Reserved.

United Launch Alliance • P.O. Box 277005 Littleton, CO 80127-7005 • (720) 922-7100 • www.ulalaunch.com

Documents

Ocean Surface Topography Mission (OSTM/Jason-2) · United Launch Alliance (ULA) is proud to launch the OSTM/Jason-2 mission. Jason-2 will be launched aboard a Delta II 7320 launch