Launch Vehicles

LAUNCH SYSTEM CONCEPTSSHROUD• PROTECTS THE

SPACECRAFT

SHROUD• PROTECTS THE

SPACECRAFT

MAIN VEHICLE• PRIMARY LIQUID OR

SOLID ROCKET PROPELLANT TANKS

MAIN VEHICLE• PRIMARY LIQUID OR

SOLID ROCKET PROPELLANT TANKS

ENGINE / NOZZLES• MECHANISM FOR

COMBINING PROPELLANTS AND FOCUSING THRUST

ENGINE / NOZZLES• MECHANISM FOR

COMBINING PROPELLANTS AND FOCUSING THRUST

BOOSTER PACKS• SOLID STRAP ONS FOR

SOME ROCKETS TO INCREASE INITIAL THRUST

BOOSTER PACKS• SOLID STRAP ONS FOR

SOME ROCKETS TO INCREASE INITIAL THRUST

LAUNCH FACILITY• ROCKET ASSEMBLY AND PREPARATION• LAUNCH PAD • LAUNCH CONTROL CENTER

LAUNCH FACILITY• ROCKET ASSEMBLY AND PREPARATION• LAUNCH PAD • LAUNCH CONTROL CENTER

STEP 2: BOOSTER CUT-OFF AND SEPARATION

STEP 3: MAIN ENGINE CUT-OFF AND SEPARATION

STEP 4: SHROUD OPENING

STEP 5: ORBIT INSERTION THRUSTING

STEP 6: SATELLITE INITIAL CHECKOUT AND POWERING UP

STEP 7: MECHANICAL DEPLOYMENTS

UPPER STAGE• ORBIT INSERTION

ROCKET ENGINES AND PROPELLANT TANKS

UPPER STAGE• ORBIT INSERTION

ROCKET ENGINES AND PROPELLANT TANKS

STEP 1: IGNITION AND LAUNCH

Pegasus/XL Taurus Titan II Delta II Atlas II Atlas IIA Atlas IIAS Titan IV Titan IV Space Shuttle

SRM SRMU

60,000

50,000

40,000

30,000

20,000

10,000

Lbs 0

800

2,750860

1,030

4,200Polar

11,1104,010

14,9506,500

16,0506,970

19,0508,450

39,00014,00010,000

47,70019,00011,500

53,50013,5005,200

Launch VehiclesCurrent Capabilities

Weight (lbs) to LEO

Weight (lbs) to GTO

Weight (lbs) to GEO

350

300

250

200

150

100

50

0 Ft

SMALL

MEDIUM

HEAVY

Titan Space Launch Vehicles Mission Description

Mission

• Titan IV provides heavy lift capability to deliver the Nation’s highest priority satellites into orbit from Cape Canaveral AS, FL, and Vandenberg AFB, CA

• Titan II provides medium lift capability from Vandenberg AFB using 14 refurbished Titan II ICBMs

Capabilities

• Titan IVA: 38,500 lbs to Low Earth Orbit (LEO). T-IVB: 47,000 lbs to LEO. T-IV Supports DSP, Milstar, NASA (Cassini), and National User

• Titan II: 4,200 lbs to LEO. Supports DMSP and NOAA (Tiros)

Provides highly reliable means of placing DoD satellites into orbit

Titan II Titan IV

CURRENT DEPLOYMENT: TITAN IVA

WEIGHT: 1,907,500 LB (WITH CENTAUR OPTION)

SIZE: LEN. - 204 FT, CORE DIAMETER - 10 FT

SHROUD SIZE: DIA .- 16 FT, OPTIONAL LEN. TO 86 FT

FIRST LAUNCH: JUNE 1989

BOOSTER ROCKETS (STAGE 0): 2 SOLID MOTORS - 1,600,000 LB

THRUST EACH

STAGE 1: 2 AEROJET LR-87 LIQUID ENGINES - 274,000 LB THRUST

EACH

STAGE 2: 1 AEROJET LR-91 LIQUID ENGINES - 105,000 LB THRUST

UPPER STAGE: CENTAUR, INERTIAL UPPER STAGE (IUS), OR NONE

(NUS)

PRIME CONTRACTOR: LOCKHEED-MARTIN

CAPABILITIES:

10,000 LB PAYLOAD TO GEO

39,000 LB PAYLOAD TO LEO

31,100 LB PAYLOAD TO POLAR LEO

STAGE O

STAGE 1

UPPERSTAGE

STAGE 2

CURRENT DEPLOYMENT: TITAN II

WEIGHT: 340,000 LB

SIZE: LEN. - 140.8 FT, DIA. - 10 FT

SHROUD SIZE: LEN. - 25 FT, DIA. - 10 FT

FIRST LAUNCH: SEPT 1988

STAGE 1: 2 AEROJET LR-87 LIQUID ENGINES - 237,000

LB THRUST EACH

STAGE 2: 1 AEROJET LR 91 LIQUID ENGINES - 100,000

LB THRUST

PRIME CONTRACTOR: LOCKHEED-MARTIN

CAPABILITIES:

4,200 LB PAYLOAD TO POLAR LEO

STAGE 1

STAGE 2

Medium Launch Vehicles Mission Description

Mission

•Provides highly reliable means of placing DOD satellites into their required orbits

Delta II Launches Global Positioning System (GPS) and Space Test Program (STP) satellites

Atlas IIA/IIAS launches Defense Satellite Communication System (DSCS) and National User satellites

Capabilities

• Delta II: 4,670 lbs to GPS Transfer Orbit

• Atlas IIA:

6,125 lbs to Geosynchronous Transfer Orbit

• Atlas IIAS (National User)

8,075 lbs to Geosynchronous Transfer Orbit

Primary systems providing medium lift capability for DOD satellites

Delta II Atlas IIA

CURRENT DEPLOYMENT: ATLAS IIAS

WEIGHT: 515,900 LB

SIZE: LEN. - 156 FT, DIA . - 10 FT

SHROUD SIZE: LEN. - 34 FT, DIA. - 10 OR 14 FT

FIRST LAUNCH: DEC 1993

BOOSTER ROCKETS (STAGE 0): 4 THIOKOL CASTOR IVA SOLID

ROCKETS - 97,520 LB THRUST EACH

STAGE 1: 2 ROCKETDYNE MA-5A LIQUID BOOSTER ENGINES -

207,000 LB THRUST EACH, 1 ROCKETDYNE MA-5A LIQUID

SUSTAINER ENGINE - 59,000 LB THRUST

STAGE 2: 2 PRATT & WHITNEY RL10A-4 LIQUID ENGINES - 22,300

LB THRUST EACH

PRIME CONTRACTOR: GENERAL DYNAMICS

CAPABILITIES:

19,050 LB TO LEO

16,100 LB TO POLAR LEO

7,950 LB TO GEO TRANSFER ORBIT

STAGE O

STAGE 1

STAGE 2

CURRENT DEPLOYMENT: ATLAS IIAS

WEIGHT: 515,900 LB

SIZE: LEN. - 156 FT, DIA . - 10 FT

SHROUD SIZE: LEN. - 34 FT, DIA. - 10 OR 14 FT

FIRST LAUNCH: DEC 1993

BOOSTER ROCKETS (STAGE 0): 4 THIOKOL CASTOR IVA SOLID

ROCKETS - 97,520 LB THRUST EACH

STAGE 1: 2 ROCKETDYNE MA-5A LIQUID BOOSTER ENGINES -

207,000 LB THRUST EACH, 1 ROCKETDYNE MA-5A LIQUID

SUSTAINER ENGINE - 59,000 LB THRUST

STAGE 2: 2 PRATT & WHITNEY RL10A-4 LIQUID ENGINES - 22,300

LB THRUST EACH

PRIME CONTRACTOR: GENERAL DYNAMICS

CAPABILITIES:

19,050 LB TO LEO

16,100 LB TO POLAR LEO

7,950 LB TO GEO TRANSFER ORBIT

STAGE O

STAGE 1

STAGE 2

CURRENT DEPLOYMENT: PEGASUS

WEIGHT: 41,500 LB

SIZE: LEN. - 50.9 FT, DIA. - 4.2 FT

SHROUD SIZE: LEN. - 14.5 FT, DIA. - 4.2 FT

FIRST LAUNCH: APRIL 1990

PLATFORM: L-1011 CARRIER AIRCRAFT

STAGE 1: ALLIANT TECHSYSTEMS SOLID ROCKET

MOTOR - 109,400 LB THRUST

STAGE 2: SOLID MOTOR - 27,600 LB THRUST

STAGE 3: SOLID MOTOR - 7,800 LB THRUST

STAGE 4: OPTIONAL HYDRAZINE LIQUID

PROPULSION SYSTEM

PRIME CONTRACTOR: ORBITAL SCIENCES CORP

CAPABILITIES:

700 LB PAYLOAD TO LEO ORBIT

NameLength

(ft)Propellant

EngineType

Thrust(lb)

EngineManufacturer

Centaur(Titan)

IUS

PAM-D

LockheedMartin

Boeing

29.5

17

6.7

14.2

9.75

4.1

LOX/LH2

HTPB

HTPB Star 48B

16,500(each)

41,61117,629

15,000

Orbus 21Orbus 6

TOS 11 11.2 HTPB SRM-1 45,000

Diameter(ft)

StageManufacturer

McDonnellDouglas

OSC -Lockheed

Martin

RL-10A-3-3A(two)

Pratt &Whitney

UnitedTechnologies

Thiokol

UnitedTechnologies

GrossMass

(lb)

52,600

22,770 8,650 *

4,721

23,800

* The IUS contains two separate stages

Centaur IUS PAM-DTOS

LAUNCH SYSTEM: UPPER STAGES

Inertial Upper Stage (IUS) Mission Description

Mission

• Transfer Defense Support Program (DSP) spacecraft from a Titan IV low earth orbit to its mission orbit

Capabilities

• Two-stage, high altitude, solid rocket motor booster used in conjunction with either the Titan IV or Space Shuttle

• Delivers spacecraft of over 5000 pounds from Titan IV or Space Shuttle park orbit to geostationary orbit or to interplanetary trajectories

• 100% successful and highly accurate for DoD missions

• Reliable as a result of redundant systems and capable of retargeting

The only system providing transfer of DSP satellites to mission orbit

Low Earth Orbit

Mission Orbit

DSP

IUS

TITAN IV

Why Staging?

• Increases efficiency of total launch vehicle– Upper stages get progressively smaller– Don’t keep accelerating dead weight– More flexibility in performance

• Combinations of stages to best meet mission requirements

• We have done calculations of the process

V = Isp x g x ln MR

Rocket Equation

Mass Ratio

Specific Impulse

MR = mbefore burn mafter burn

Isp =W.F

Rocket Formulas

Apogee

Perigee Right Ascension

Inclination

V

Orbit Velocity

=14.5x1015 ft3per sec2

a2

V =

r

Three Stage Booster

Weights (lbs.)

1st Stage 35,000 365,000 100 280 400,000599,000 2.56

2nd Stage 10,000 125,000 120 290 135,000199,000 2.69

3rd Stage 4,000 50,000 80 250 54,000 4.57Payload 10,000

Structure Propellants

Burn Time(sec)

Isp

(sec)

StageWeight MR

V1 = (280)(32.2)ln (2.56) = 8,475 ft/secV2 = (290)(32.2)ln (2.69) = 9,238 ft/secV3 = (250)(32.2)ln (4.57) = 12,232 ft/sec

Vl = 29,945 ft/sec

Vposigrade = 29,535 ft/sec

Vretrograde = 30,183 ft/secCan place payload in posigrade orbit,but not in retrograde orbit,

All threestages