GPS IIR-19 (M)

U.S. Air ForceDelta Launch Vehicle Programs

The Delta team is proud to be the launch provider for the Air Force Global Positioning System (GPS) program by delivering replenishment satellites to orbit aboard the Delta II rocket. GPS satellites serve and protect our war fighters by providing navigational assistance for U.S. military operations on land, at sea, and in the air. Civilian usersaround the world also use and depend on GPS for directional assistance.

GPS IIR-19 (M) is the sixth of the modernized GPS satellites, incorporating various improvements to provide greateraccuracy, increased resistance to interference, and enhanced performance for users. It will be launched aboard aDelta II 7925-9.5 vehicle in March 2008 from Space Launch Complex (SLC)17A at Cape Canaveral Air Force Station(CCAFS), FL.

We wish to thank our Delta II team, which consists of the U. S. Air Force, The Aerospace Corporation, ULA, and major suppliers of ULA, for their continued hard work and commitment to mission success. We look forward to continuingour support for the Air Force aboard Delta II launch vehicles.

John Gerlitz Lt Col Rodney HouserDirector, USAF/MLV-III Program Delta II Program Manager ULA Customer Program Office Delta Launch Group

Launch & Range Systems Wing

GPS IIR-19 (M)

The Navstar Global Positioning System (GPS) is a constellation of orbiting satellites that provides navigation data to military and civilian users world wide. The system is operated and controlled by the 50th Space Wing, located atSchriever Air Force Base, CO.

GPS satellites orbit the Earth every 12 hours, emitting continuous navigation signals. With the proper equipment,users can receive these signals to calculate time, location, and velocity. The signals are so accurate that time can be figured to within a millionth of a second, velocity within a fraction of a mile per hour, and location to within 100 feet.Receivers have been developed for use in aircraft, ships, and land vehicles, and also to hand carry.

GPS provides 24-hour navigation services including:• Extremely accurate, three-dimensional location information (latitude, longitude, and altitude), velocity,

and precise time• Worldwide common grid that is easily converted to any local grid• Passive all-weather operations• Continuous real-time information• Support to an unlimited number of users and areas• Support to civilian users at a slightly less accurate level

The GPS constellation is designed and operated as a 24-satellite system, consisting of six planes with a minimum offour satellites per plane.

The GPS satellites are placed into nearly 11,000-mile circular orbits. While circling the Earth, the systems transmit signals on three different L-band frequencies—the satellites have a 10-year design life.

GPS Mission

• Vehicle configuration:

Delta II 7925-9.5

• Customer: USAF

• Launch site:

SLC-17A at CCAFS

Fairing

Secondstage

Fairing

First-stage oxidizer tank

Interstage

Wiring tunnel

Centerbody section

Third-stagemotor

First stage

GPSspacecraft

Spin table

Helium spheresNitrogen sphere

Attach fitting

Thrust augmentation solids

Conicalsection

Fairing accessdoor

Third-stage motorseparation clampband

Guidance electronicsSecond-stage miniskirt and support truss

Fuel tank

Delta II 7925-9.5 Launch Vehicle

• Transfer orbit criteria (defined at space vehicle separation)

– Apogee altitude: 10,998.00 nmi (integrated)– Perigee altitude: 104.00 nmi– Inclination: 40.00 deg– Geodetic latitude: -10.05 deg N

(at first apogee)

• Payload weight: 4,540.0 lb (2,059.3 kg) • Transfer orbit injection mode: Ascending node• Launch pad: SLC-17A

GPS IIR (M) SpacecraftMission Requirements

• Spin rate: 55 rpm

• Second-stage probabilityof command shutdown (PCS): ≥ 99.7%

• Free molecular heating rate ≤ 1 Btu/ft²-sec at fairing separation: (1,135 W/m²)

Mission Requirements(Continued)

• Delta II 7925-9.5 vehicle configuration

• Launch from CCAFS SLC-17A down flight azimuth of 110 deg

• 6/3 GEM solid motor firing sequence

• Common boost trajectory utilized for both descending and ascending node injections

• Boost trajectory designed to meet controllability, structural, and environmental constraintswhile maximizing vehicle performance

• Dogleg maneuver used to increase parking orbit inclination

– Maneuver split between booster and second-stage flightto meet Range Safety constraints

• Main engine cutoff (MECO) occurs at first-stage propellant depletion;approximately 263 sec after liftoff

• Second stage separates 8 sec after MECO; Stage II ignited 5.5 sec later

• Payload fairing jettisoned when free molecular heating rate is< 0.1 Btu/ft²-sec (1,135 W/m²)

• Second-stage first burn places vehicle in parking orbit at first cuttoff - second stage (SECO-1)

– Ascending node: 94 x 111 nmi orbit at 37.50 deg inclination

GPS IIR (M)Flight Mode Description

• Following SECO-1, vehicle is reoriented to second-stage restart and third-stage burn attitude

• At end of reorientation maneuver, vehicle is rolled at 1 deg/sec for thermal conditioning

• Following coast period of 51.7 min, second-stage restart occurs at approximately 62.5 minafter liftoff over the Guam T/M tracking station

– Restart burn duration of approximately 42.5 sec

– At SECO-2, vehicle in 103 x 670 nmi orbit at 37.95 deg inclination

• Spin-up and separation of third stage follows restart burn cutoff

• Third-stage burn and nutation control system (NCS) blowdown places spacecraft into thedesired transfer orbit

• Spacecraft separation occurs approximately 68 min after liftoff; third-stage yo deployed 2 secafter separation to tumble stage and preclude recontact with the spacecraft

• Guam tracking station provides telemetry coverage of second-stage restart through spacecraftseparation

Flight Mode Description(Continued)

Time

(min:sec)Event

Liftoff

Mach 1

Maximum dynamic pressure

Six solid motors burnout

Three solid motors ignition

Jettison three solid motors

Jettison three solid motors

Three solid motors burnout

Jettison three solid motors

Begin dogleg maneuver – Stage I

End dogleg maneuver – Stage I

MECO

Stage I-II separation

Stage II ignition

Begin dogleg maneuver – Stage II

End dogleg maneuver – Stage II

00:00.0

00:32.6

00:49.8

01:03.1

01:05.5

01:06.0

01:07.0

02:08.8

02:11.5

02:20.0

02:40.0

04:23.4

04:31.4

04:36.9

04:43.0

04:53.0

Mission Sequence of Events

Time

(hr:min:sec)Event

Jettison fairing

First cutoff – second stage (SECO-1)

Begin reorientation maneuver

End reorientation maneuver

Begin coast roll maneuver

End coast roll maneuver

Restart second stage

Second cutoff – second stage (SECO-2)

Fire spin rockets

Stage II-III separation

Stage III ignition/NCS enable

Stage III burnout (TECO)

Begin NCS blowdown

End NCS blowdown

Spacecraft separation

Stage III yo deploy

First apogee of transfer orbit

00:04:57.0

00:10:48.1

00:12:30.0

00:17:10.0

00:17:20.0

00:56:25.0

01:02:29.2

01:03:11.7

01:04:01.7

01:04:04.7

01:04:41.7

01:06:08.4

01:06:51.7

01:07:44.0

01:08:01.7

01:08:03.7

04:03:23.3

Mission Sequence of Events(Continued)

Longitude (deg)

75 N

60 N

45 N

30 N

15 N

0

15 S

30 S

45 S

60 S

75 S120 W 60 W 0 60 E 120 E 180

Lati

tud

e (

deg

)

T/M Tracking Sites

TEL-4 = Eastern Range ANT = Antigua ASC = AscensionGTS = Guam HTS = HawaiiVTS = Vandenberg AFBCTS = ColoradoNHS = New HampshireTTS = Thule, Greenland

TEL-4VTS

CTS NHS

HTSANT

ASC

HTS AOS

CTS AOS

GTS

76543

2

8

1

TTS AOS

HTS LOS

NHS AOS

VTS AOSTTS LOS

Legend (time, sec)

1 = MECO (263.4)2 = SECO-1 (648.1)3 = Restart Ign (3749.2)4 = SECO-2 (3791.7)5 = Stage–3 Ign (3881.7)6 = TECO (3968.4)7 = S/C Sep (4081.7)8 = First Apogee (14603.3)

Ascending Node Orbit Trace

• Second stage depletion burn follows primary mission to safe the stage and lower inclination tominimize casualty probability

• After Stage II-III separation, vehicle is reoriented to second stage depletion burn attitude

• Depletion burn ignition for ascending node trajectory occurs at 1 hr, 46 min, 40 sec overEastern Range Tel-4 and Antigua tracking stations

– Nominal duration of 32.0 sec through mono-propellant blowdown

– At end of nominal depletion burn second stage in a 110 x 661 nmi orbit with an inclination of 32.91 deg

Depletion Burn Flight Mode Description

PCM

Magna, Utah

Goodrich Aerospace

Albuquerque, New Mexico

CRD RIFCA

L3 CommunicationsSpace & NavigationDivision

Budd Lake, NJcommunications

CincinnatiElectronics

Cincinnati, Ohio

El Paso, Texas

Sacramento, CA

Delta ProgramHuntington Beach, CA

Canoga Park, CA

RS-27 Engine

Major Subcontractor

Major Component Flow

Launch Processing

Eastern RangeCCAFS, Florida

Integration

and Checkout

Elkton, MD

Launch VehicleAssembly

Decatur, Alabama

Graphite-Epoxy Motors

Star 48 Motor

HeadquartersLittleton, CO

VAFB

CCAFS

ITIP Engine

Ordnance Shipped Directly to CCAFS From Suppliers

Operational Flow at Eastern Range

• First stage from assembly plant

• Second-stage, fairing, interstage from assembly plant

• Space vehicle

• Upper-stage motor

• GEM graphite-epoxy motors

Delta II integration and checkout area • Receive and inspect • Mission integration and checkout • Dual composite tests • Storage • Load on pad erection trailers

• Erect and mate stages• Install solid motors• Check out subsystems• Simulated flight test• Preflight finalization

• Mate to upper stage

Area 57

Area 59

• Balance motor

• Destruct installation

• Destruct installation• Erection preparation• Leak checks

Area 55

Space Launch Complex 17

Horizontal Processing Facility

ProcessingFacility

Delta Mission Checkout (Hangar AO)

Total Vehicle Integration & Checkout at the Launch Site

0700 0900 1100 1300 1500 1700 1900

Area Conditions

Weather Briefing

2100 2300 0100 0300

LegendPad Open Amber-Limited Access Red-Pad Closed GPS S/C Activity

0500MST Preps for Removal (F2-T4)

S/C Monitoring

Support:

Briefing (F1-T1)

MST & Searchlight SupportOD5525

Freq Clear 416.5, 2241.5, 2252.5, 5690.0, 5765.0 MHz FCO, RCO & Seq

OSM

Engineering Walkdown (F1-T1A & T1B)

Prep for S/M Arming, Lanyard Tensioning, MST Removal/Securing (F1-T1B)

Whiteroom A/C Off (After East Door Open)

Deck Plate Removal and Pad Securing (F1-T2)

Press Second Stg He & GN2 (F1-T2)Hold Fire Checks (F1-T2)

Built In Hold (60 Mins)Terminal Count (F1-T3)

Photo Opportunity

S/C RF S-Band T/M ActivationGrate Removal (F1-T1) (Option)

Solid Motor TLX Connection (F1-T2) (Option)LPI Pin Pull (F1-T2)

MST Preps and Move (F1-T1B)Camera Setup

Final Prop Sys Preps (F1-T1B)

3/14 3/15

A/C Watch (F52-T1), VDS Monitor & Prop Watch (F41)S/C Battery Charge

3/14 3/15

Delta II Countdown (T-0 Day)

Delta II Terminal Count (T-0 Day)

T-Minus140 130 120 110 100 90 80 70 60 50 20 4 4 0

Launch Window Open Close

Local 02:09:00 02:23:00 UTC 06:09:00 06:23:00

14 Minute Window

Terminal Countdown Initiation & Briefing (50 Minutes into Hold)Personnel Not Involved In Terminal Count Clear Cx-17 (Sound Warning Horn)

Guidance System Turn OnSecond Stage He, Tank Press

C-Band Beacon Checks

LOX Loading

First Stage Fueling

Slew EvaluationsAuto Slews

OSM Clear Blast Danger AreaFirst Stage He & N2 Press

Weather Briefing

15

Command Carrier On

Pressurize Fuel TankTop Off He & N2

60 Min Built

In Hold

At T-150

Arm Spacecraft S&A

UTC

Local (EDT)

20 Min 00

Sec

Built In

Hold At

T-15 Min

150

Spacecraft Internal @ L-26

23:09 23:19 23:29 23:39 23:49 23:59 00:09 00:19 00:29 00:39 00:49 01:09 01:1901:24 01:49

01:5502:05:00

02:09:00

03:09 03:19 03:29 03:39 03:49 03:59 04:09 04:19 04:29 04:39 04:49 04:59 05:09 05:1905:24 05:49

06:09:0005:5506:05:00

Command Receiver Checks

10 Min 00

Sec

Built In

Hold At T-4 Min

1530

Spacecraft Launch Ready (L-3)Arm Third Stage S&A

Arm Destruct S&A

Launch

Status Checks

01:44

05:44

10

00:59

40

3/14 3/15

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

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