Table II. Lunar cargo mission—nuclear thermal propulsion (NTR) Lunar delivery (cargo)—NTR Orbital sequential weights/performance Status date: Jan 30, 1989 Lunar transit stage—NTR I (sec): MPS: 756.0 RCS: 220.0 B/O Rate (kg/day): 3.8 Reserves (%): MPS: 2 RCS: 10 Lunar cargo: 48000 Stage: 41467 Brake: 3581 Tank: 7995 Sequential wt Delta V Time MPS fluids RCS ------------------- Mission event MPS RCS day boiloff Nominal fluids Other kg lb LEO departure 125912 277 585 MPS perigee burn 1 1548 0 1.0 —3.8 —14 252 0 -14 255 31428 MPS perigee burn 2 1606 0 2.0 —7.6 —24 522 0 -24 529 54077 MPS lunar capture 869 0 1.0 ±93.8 —6639 0 -6642 -14 644 Drop tankset 0 0 0.0 0.0 0 0 -7995 -7995 -17626 Separate cargo vehicle 0 0 0.0 0.0 0 0 -48 000 -48 000 -105821 Start earth return 53 382 117687 MPS Earth transit 870 0 4.0 -15.3 -5909 0 -524 -13061 Earth aeromaneuver weight 47 458 104 626 MPS post aeromaneuver correction 215 0 0.0 0.0 —1357 0 1357 -2991 Less aerobrake 0 0 0.0 0.0 0 0 -3581 -3581 -7895 MPS reserves 0 0 0 0 -1054 -1054 -2323 RCS reserves 0 0 0 0 0 0 0 End of mission, excluding reserves 41 467 91 418 Total delta weight 5108 0 8.0 0 -30.6 -52677 0 -60630 Fluid reserves —1054 0 Total usable fluid weight—kg —53 762 0 Total usable fluid weight—lb —118 524 0
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