deisgnII - Mission Mercury Gemini Apol o Vostok Voshkod...

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Unformatted text preview: Mission Mercury Gemini Apol o Vostok Voshkod Soyuz Shenzhou US Years 1961-1963 1968-1975 1961-1963 1964-1965 1967-present 2003-present Crew 1 2 3 1 2 3 3 5 Launch Vehicle Redstone, Atlas Titan I Saturn 1, 1B, VR-7 R-7 R-7 varient CZ-2F Length 108 132 127 91 91 82 87 Diameter 75 90 154 91 91 106 110 height 138 Weight(lb) 4265 7495 65256 10361 11684 15211 17196 lower dia 36 Command Mod Wght 2900 7000 13000 5423 6393 6393 higher dia 170 Volume 103680 155520 376514 208526 208526 244094 area 997286 11929.98 Tvolume 159043.128087983 279915.9 788521.9537 394568.852926386 394568.852926386 542721.126482 620091.5 crew 5 parachute 18820.423 chutes at 89 ft in diameter weight 15154 para volum 5183.673in^3 1727.891each volume 427481.07 tvolume 1009216 parachute 3110 5432 16338 10645 12916 power 13 155 690 24 124.8 276.562 struct mass 748 1403.6 3447.4 5915.43 heat sheild 598.4 316.8 1865.6 reaction control 88 292.6 880 recovery equip 132 215.6 539 906.03 navagation 88 138.6 1111 telemetry 110 112.2 440 electrical 176 277.2 1540 communications 44 57.2 220 crew seats&provisions 176 937.2 1210 2015 crew 158.4 316.8 475.2 contingacy 220 440 propel ant 30.8 72.6 165 250 environmental 110 440 weight/kw 13.5384615385 1.788387 2.231884058 414.843 0.5 1 1.5 2 2.5 3 3.5 2000 4000 6000 8000 10000 12000 14000 f(x) = 2767.5x + 1316.5 R² = 0.5480392763 Passengers Weight (lb) 2000 4000 6000 8000 10000 12000 14000 50000 100000 150000 200000 250000 300000 350000 400000 f(x) = 25.4553728317x + 41735.846376795 R² = 0.8435838557 Weight (lb) Volume (in^3) 0.5 1 1.5 2 2.5 3 3.5 50000 100000 150000 200000 250000 300000 350000 400000 f(x) = 77100.5x + 61942.3333333333 R² = 0.553758173 Volume (in^3) Passengers 0.5 1 1.5 2 2.5 3 3.5 100000 200000 300000 400000 500000 600000 700000 800000 900000 f(x) = 194253.728950282x + 37946.4814646191 R² = 0.6744965849 Passengers Total Volume(in^3) 2000 4000 6000 8000 10000 12000 14000 2000 4000 6000 8000 10000 12000 14000 16000 18000 f(x) = 1.2761828576x - 464.5561120605 R² = 0.8268778815 Parachute Weight (lb) Area (ft^2) 0.5 1 1.5 2 2.5 3 3.5 100 200 300 400 500 600 700 800 f(x) = 194.45x - 187.54 R² = 0.4821026351 Power Crew Power (kW) 0.5 1 1.5 2 2.5 3 3.5 100 200 300 400 500 600 f(x) = 203.5x - 111.4666666667 R² = 0.8962865324 Recovery Crew Weight (lb) 0.5 1 1.5 2 2.5 3 3.5 200 400 600 800 1000 1200 1400 f(x) = 517x - 259.6 R² = 0.9307793434 Crew Seat s Crew Weight (lb) 0.5 1 1.5 2 2.5 3 3.5 20 40 60 80 100 120 140 160 180 f(x) = 67.1x - 44.7333333333 R² = 0.9547553883 Propel ant Crew Weight (lb) 0.5 1 1.5 2 2.5 3 3.5 500 1000 1500 2000 2500 3000 3500 4000 f(x) = 1349.7x - 833.0666666667 R² = 0.9189864872 Propel ant Crew Weight (lb) Radial divisions 16 22.5 =body geometry input Main 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 0 X Z Y X,Y,Z Bot om 17.2227 1 out radial 17.216-8.636-12.7581 0.028 0.025869 0.019799 0.010715 1.71451E-018 -0.010715-0.019799 -0.025869-0.028-0.025869 -0.019799 -0.010715-5E-018 0.010715 0.019799 0.025869 normal rad 8.6088....
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This note was uploaded on 10/22/2011 for the course EAS 4710 taught by Professor Staff during the Spring '08 term at University of Florida.

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deisgnII - Mission Mercury Gemini Apol o Vostok Voshkod...

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