1. Launch Vehicles

2. LAUNCH SYSTEM CONCEPTS SHROUD 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

3. 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 2,750 860 1,030 4,200 Polar 11,110 4,010 14,950 6,500 16,050 6,970 19,050 8,450 39,000 14,000 10,000 47,700 19,000 11,500 53,500 13,500 5,200 Launch Vehicles Current 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

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

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 STAGE O STAGE 1 UPPER STAGE STAGE 2

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 1 STAGE 2

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: è 4,670 lbs to GPS Transfer Orbit Atlas IIA: è 6,125 lbs to Geosynchronous Transfer Orbit Atlas IIAS (National User) è 8,075 lbs to Geosynchronous Transfer Orbit Primary systems providing medium lift capability for DOD satellites Delta II Atlas IIA

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 O STAGE 1 STAGE 2

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 O STAGE 1 STAGE 2

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. Name Length (ft) Propellant Engine Type Thrust (lb) Engine Manufacturer Centaur (Titan) IUS PAM-D Lockheed Martin Boeing 29. 5 17 6.76.7 14.2 9. 75 4.14.1 LOX/LH2 HTPB Star 48B 16,500 (each) 41,611 17,629 15,000 Orbus 21 Orbus 6 TOS11 11. 2 HTPBSRM-145,000 Diameter (ft) Stage Manufacturer McDonnell Douglas OSC - Lockheed Martin RL-10A-3-3A (two) Pratt & Whitney United Technologies Thiokol United Technologies Gross Mass (lb) 52,600 22,770 8,650 * 4,721 23,800 * The IUS contains two separate stages CentaurIUSPAM-D TOS LAUNCH SYSTEM: UPPER STAGES

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

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.  V = I sp x g x ln MR Rocket Equation Mass Ratio Specific Impulse MR = m before burn m after burn I sp = W. F Rocket Formulas Apogee Perigee Right Ascension Inclination V Orbit Velocity  =14.5x10 15 ft 3 per sec 2 a 2 V=  rr 

15. Three Stage Booster Weights (lbs.) 1st Stage 35,000 365,000 100 280400,000 599,000 2.56 2nd Stage 10,000 125,000 120 290135,000 199,000 2.69 3rd Stage 4,000 50,000 80 250 54,000 4.57 Payload 10,000 StructurePropellants Burn Time (sec) I sp (sec) Stage Weight MR  V 1 = (280)(32.2)ln (2.56) = 8,475 ft/sec  V 2 = (290)(32.2)ln (2.69) = 9,238 ft/sec  V 3 = (250)(32.2)ln (4.57) = 12,232 ft/sec V l = 29,945 ft/sec V posigrade = 29,535 ft/sec V retrograde = 30,183 ft/sec Can place payload in posigrade orbit, but not in retrograde orbit, All three stages