97 Fiscal Year 1999 Activities f g [1966, [1958, Launch scheduled IIA [1966, Delta-7925 1968, Atlas F Atlas Centaur] Atlas Centaur] k e 3,175 1990, d i — 910 e e e e e e e e Max. Payload (kg) 7,300 6,170 e, k 5,510 380 — 210 1990 280 3,890 1,860 h (m) Orbit Orbit Orbit D Max. Dia Geosynch. Sun- b, c PPENDIX (Continued) A 73.4/ 3.05x9.14 (kilonewtons) 73.4/engine 3.05x10.05 92.53/engine 3.05x10.05 92.53/engine 3.05x10.05 a 2 2 2 2 U.S. Space Launch Vehicles Space Launch U.S. Solid 433.6 (SL) 1.01X11.16 Solid 66.4 1.25x2.04 j j Stages: Thrust x Height 185-km Transfer Synch. First 1. Orion 50S-XL1. Orion 50-XL2. Orion 383. Orion Solid120 Solid0. Castor Solid Solid 743.3 201.5 1.28x10.29 31.9 1.28x3.58 1,687.7 350 0.97x1.34 2.34x11.86 1,080 1. Orion 50S1. Orion 502. Orion 383. Orion Solid Solid Solid 484.9 118.2 31.9 1.28x8.88 1.28x2.66 0.97x1.34 RL10A-4 (2) RL10A-4 (2) RL10A-3-3A (2) RL10A-3-3A (2) engine 2. Centaur II:2. Centaur LOX/LH Pegasus 6.71x15.5 Taurus 2.34x28.3 1,400 255 1,020 Not Pegasus XL 6.71x16.93 460 — 335 1994 Atlas E 3.05x28.1 820 Hercules GEM (9) Solid 487.6 (SL) 1.01x12.95 Castor IVA (4) Castor IVA Atlas IIAS 4.2x47.5 8,640 3,606 5,800 1993, IIAS Atlas IIA 4.2x47.5 6,828 3,062 4,750 1992, Atlas Atlas II 4.2x47.5 6,580 2,810 4,300 1991, II [1966, Vehicle Engine/Motor Propellant 1. Atlas: MA-5A1. Atlas: II:2. Centaur LOX/RP-1 LOX/LH 2,110.0 (SL) 3.05x24.9 1. RS-270/A2. AJ10-118K48B 3. Star LOX/RP-1 N204/A-50 1,043.0 (SL) 3.05x38.1 42.4 2.44x5.97 Delta] [1960, 1. Atlas: MA-5A1. Atlas: II:2. Centaur LOX/RP-1 LOX/LH 2,110.0 (SL) 3.05x24.9Centaur] Atlas 1. Orion 50S1. Orion 502. Orion 383. Orion Solid Solid Solid 580.5 138.6 31.9 1.28x8.88 1.28x2.66 0.97x1.34 1. Atlas: MA-5A1. Atlas: LOX/RP-1 2,110.0 (SL) 3.05x24.9Centaur] Atlas 1. Atlas: MA-31. Atlas: MA-5 LOX/RP-11. Atlas: I:2. Centaur LOX/RP-1 LOX/LH (SL) 1,739.5 3.05x21.3 1,952.0 (SL) 3.05x22.16 LV-3A] Atlas (7920, 7925) Delta II 2.44x29.70 5,089 1,842 Atlas I 4.2x43.9 — 2,255 — 1990, I [1966, 98 ia V .x22—5,760 — 4.3x62.2 Titan IV/ ia V30x221,0 6,350 17,700 3.05x62.2 Titan IV ia I .54. 4555,000 14,515 3.05x47.3 Titan III

Aeronautics 3.05x10.0 3.05x26.4 462.8 1,214.5 and N204/A-50 N204/A-50 Space2. LR91-AJ-11 1. LR87-AJ-11 (2) Report of the President . ia VSM()Sld700031x41Titan IV 3.70x45.46 (SL) 11,790.0 Titan III Titan IIIA] LOX/LH Solid 3.05x10.0 3.11x34.1 14,110 2. Orbiter/ET: 462.5 7,000.0 3.05x26.4 1. SRB: 3.11x34.1 1,214.5/engine 3.05x10.0 7,000.0 N204/A-50 Centaur: N204/A-50 3. Solid 3.11x27.6 2. LR91-AJ-11(1) 1. LR87-AJ-11 462.8 3.05x24.0 (2) Titan IVSRM(2) 0. 6,210.0 1,214.5 Solid N204/A-50 Titan IVSRM(2) 0. N204/A-50 Solid 2. LR91-AJ-11 1. LR87-AJ-11 (2) Titan IIISRM(2) 0. eil nieMtrPropellant Engine/Motor Vehicle .L-1A- 24A5 4. .51. [1964, Titan Titan IISLV II 3.05x12.2 3.05x21.5 440.0 1,045.0 N204/A-50 N204/A-50 2. LR-91-AJ-5 LR-87-AJ-5(2) 1. Space Shuttle (7 segments) .ObtrOS N 3. Orbiter/OMS: Shuttle SRB(2) LOX/LH RL-10A-3-3A (7 segments) (5-1/2 segments) .Sa 8 oi 641.25x2.04 66.4 Solid 3. Star 48B .SRMU 4. Delta III ia I30x291,905 3.05x42.9 Titan II 3sget)79 3.3x34.3 7690 (3 segments) SE()23.79x37.24 SSME (3) .R-7 LXR- ,4. S)43. ,9 ,1 ,6 1998 6,768 3,810 8,292 4x39.1 (SL) 1,043.0 LOX/LH LOX/RP-1 2. RL-10B-2 1. RS-27A tgs hutxHih 8-mTase yc.First Synch. Transfer 185-km xHeight Thrust Stages: lin E 9 oi 0. 1.16x14.7 608.8 Solid Alliant GEM(9) OMS engines(2) n 2 0 4 MH2. 23.79x37.24 26.7 /MMH U.S. SpaceLaunch Vehicles 2 2 2 a (kilonewtons) ,6. S)84x70 (ET) 8.41x47.00 (SL) 1,668.7 344.3x9.0 73.4 1 4x8.8 110 A (Continued) PPENDIX b, c 23.79x56.14 a.DaGoyc.Sun- Geosynch. Max. Dia D m ri ri Orbit Orbit Orbit (m) h h h (orbiter) 24,900 Max. Payload(kg) o e e 5,900 1988, — — m p a l d 1989, — 1989, — 1981, — 1994, — e Launch Titan IV Columbia Centaur Gemini] [1964, g f 99 Fiscal Year 1999 Activities D oxidizer from the External Tank. The boosters stage first, with oxidizer from the External Tank. before the orbiter attains orbit. The Orbiter Maneuvering Orbiter Vehicle. m. appropriate upper stage With n. Rocket Boosters fire in parallel with the Space Shuttle Solid o. circular orbit. 204-km p. Orbit Stage. or Transfer Inertial Upper Stage With PPENDIX (Continued) A U.S. Space Launch Vehicles Space Launch U.S. Director of Space Transportation System Support Programs. Director of Space Transportation Data should not be used for detailed NASA mission planning without concurrence of the Data should not be used for detailed NASA NOTE: = Nitrogen Tetroxide 50% Unsymmetrical Dimethyl Hydrazine)50% Unsymmetrical Dimethyl j. Castor IVA motors ignited at liftoff. Two Castor IVA Two = Liquid Hydrogen k. TE-M-364-4 upper stage. With 4 2 0 2 thrust per stage. and and burn fuel, the aft end of the Shuttle Orbiter Vehicle A-50 = Aerozine 50 (50% Monomethyl Hydrazine, A-50 = Aerozine 50 (50% 1 (kerosene)RP-1 = Rocket Propellant (any type) Solid = Solid Propellant LH flight. motors ignited at approximately 57 seconds into LOX = Liquid Oxygen MMH = Monomethyl HydrazineN l. Orbit Stage. Transfer With b. at vacuum except where indicated at sea level (SL). Thrust c. Thrust per engine. Multiply by number of engines ford. of 28.5˚ except where indicated. Inclination e. AFB, CA. Polar launch from Vandenberg Shuttle Main Engines (SSME), which are mounted on Space f. First successful orbital launch [ditto of initial version]. g. First launch was a failure h. represents vehicle wing span. Diameter dimension stages next, just to fire. The External Tank continuing SSME’s the orbit of the Subsystem is then used to maneuver or change NOTES: a. used are as follows: Propellant abbreviations i. II-7925 version only. Applies to Delta