Launch Vehicles
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Transcript of Launch Vehicles
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