Launch Vehicles

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Launch Vehicles
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LAUNCH SYSTEM CONCEPTS

• SHROUD
• PROTECTS THE SPACECRAFT

STEP 7 MECHANICAL DEPLOYMENTS

• UPPER STAGE
• ORBIT INSERTION ROCKET ENGINES AND PROPELLANT
  TANKS

STEP 6 SATELLITE INITIAL CHECKOUT AND POWERING UP
STEP 5 ORBIT INSERTION THRUSTING

• MAIN VEHICLE
• PRIMARY LIQUID OR SOLID ROCKET PROPELLANT TANKS

STEP 4 SHROUD OPENING
STEP 3 MAIN ENGINE CUT-OFF AND SEPARATION

• BOOSTER PACKS
• SOLID STRAP ONS FOR SOME ROCKETS TO INCREASE
  INITIAL THRUST

STEP 2 BOOSTER CUT-OFF AND SEPARATION
STEP 1 IGNITION AND LAUNCH

• ENGINE / NOZZLES
• MECHANISM FOR COMBINING PROPELLANTS AND FOCUSING
  THRUST

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

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Launch Vehicles Current Capabilities
60,000 50,000 40,000 30,000
20,000 10,000 Lbs 0
350 300 250 200 150 100
50 0 Ft
53,500 13,500 5,200
HEAVY
47,700 19,000 11,500
Weight (lbs) to LEO
39,000 14,000 10,000
Weight (lbs) to GTO
MEDIUM
Weight (lbs) to GEO
19,050 8,450
14,950 6,500
16,050 6,970
SMALL
11,110 4,010
4,200 Polar
2,750 860
1,030
800
Pegasus/XL Taurus Titan II
Delta II Atlas II Atlas IIA Atlas IIAS
Titan IV Titan IV
Space Shuttle
SRM SRMU


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Titan Space Launch Vehicles Mission Description

• Mission
• Titan IV provides heavy lift capability to
  deliver the Nations 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)

Titan IV
Titan II
Provides highly reliable means of placing DoD
satellites into orbit
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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
UPPER STAGE
STAGE 2
STAGE 1
STAGE O
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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 2
STAGE 1
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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

Atlas IIA
Delta II
Primary systems providing medium lift capability
for DOD satellites
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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 2
STAGE 1
STAGE O
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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 2
STAGE 1
STAGE O
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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
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LAUNCH SYSTEM UPPER STAGES
Gross Mass (lb)
Length (ft)
Engine Type
Thrust (lb)
Engine Manufacturer
Diameter (ft)
Stage Manufacturer
Name
Propellant
29.5
16,500 (each)
RL-10A-3-3A (two)
Pratt Whitney
Lockheed Martin
Centaur (Titan)
14.2
LOX/LH2
52,600
9.75
41,611 17,629
Orbus 21 Orbus 6
United Technologies
22,770 8,650
HTPB
IUS
Boeing
17
6.7
4.1
McDonnell Douglas
PAM-D
HTPB
Star 48B
15,000
Thiokol
4,721
OSC - Lockheed Martin
11.2
TOS
11
HTPB
SRM-1
45,000
United Technologies
23,800
The IUS contains two separate stages
Centaur
IUS
PAM-D
TOS
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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

Mission Orbit
DSP
Low Earth Orbit
IUS
TITAN IV
The only system providing transfer of DSP
satellites to mission orbit
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Why Staging?

• Increases efficiency of total launch vehicle
• Upper stages get progressively smaller
• Dont keep accelerating dead weight
• More flexibility in performance
• Combinations of stages to best meet mission
  requirements
• We have done calculations of the process

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Rocket Formulas
Rocket Equation
Apogee
DV Isp x g x ln MR
Inclination
Mass Ratio
V
Specific Impulse
Orbit Velocity
Perigee
Right Ascension
m 14.5x1015 ft3per sec2
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Three Stage Booster
All three stages
DV1 (280)(32.2)ln (2.56) 8,475 ft/sec DV2
(290)(32.2)ln (2.69) 9,238 ft/sec DV3
(250)(32.2)ln (4.57) 12,232 ft/sec
Vl 29,945 ft/sec
Vposigrade 29,535 ft/sec Vretrograde 30,183
ft/sec
Can place payload in posigrade orbit, but not in
retrograde orbit,