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Launch Vehicles

Launch Vehicles. 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

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Launch Vehicles

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  1. Launch Vehicles

  2. 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

  3. 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

  4. 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) Titan IV Titan II Provides highly reliable means of placing DoD satellites into orbit

  5. 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

  6. 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

  7. 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

  8. 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

  9. 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

  10. 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

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

  12. 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

  13. 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

  14. mbefore burn mafter burn MR = F Isp = . W m r m 2 - V = a Rocket Formulas Rocket Equation Apogee DV = Ispx g x ln MR Inclination Mass Ratio V Specific Impulse Orbit Velocity Perigee Right Ascension m =14.5x1015 ft3per sec2

  15. Three Stage Booster Burn Time (sec) Weights (lbs.) Stage Weight Isp (sec) MR Structure Propellants 1st Stage 35,000 365,000 100 280 400,000 599,000 2.56 2nd Stage 10,000 125,000 120 290 135,000 199,000 2.69 3rd Stage 4,000 50,000 80 250 54,000 4.57 Payload 10,000 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,

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