Reference Mission Propellant Mass Calculation Sheet Version 1.0
Fuel Calculation Sheet
ISP LTV 444.40
ISP Desc 444.40
ISP Asc 290.00
Burn Name DV Mbo Mi Mf Applied to
LEO I 10,572.00 8,600.00 18,014.19 9,414.19 LTV/Asc
TEI 3,212.00 18,014.19 22,551.57 4,537.38 LTV/Asc
Asc Liftoff/Insert/RV 6,136.00 1,600.00 3,088.34 1,488.34 Asc
Land on Moon 6,696.00 19,988.34 31,927.33 11,938.99 Desc/Hab/Asc
LTV Plane Change 159.00 20,951.57 21,185.86 234.29 LTV
LTV LUNO Circ 100.00 21,185.86 21,334.55 148.69 LTV
Desc Orbit Init 206.00 53,261.88 54,034.80 772.92 Stack
LUNO Insert 2,807.00 54,034.80 65,755.79 11,720.99 Stack
TLI 10,018.00 65,755.79 132,502.18 66,746.38 Stack
Orbit Maneuver 27.00 132,502.18 132,752.62 250.45 Stack
Total Mass to LEO 132,752.62
Total LTV Fuel 93,825.29
This is the initial release of the Reference Mission Propellant Mass
Calculation sheet. It is designed to illustrate the source of each of the
Reference Mission vehicles' propellant usage figures. Some abbreviations
are defined as follows:
- DV: Delta (or change in) Velocity, the velocity change
experienced during a burn, and is in ft/sec
- Mbo: Mass at BurnOut, the vehicle mass after the burn has
finished, and is in lb
- Mi: Initial Mass, the vehicle mass at the start of the
burn, and is in lb
- Mf: Fuel Mass, the mass of propellants consumed during the
burn, and is in lb
The engine specific impulse (ISP) values used in computing the
propellant masses are displayed at the top of the table. They are based
on using an RL-10A-3-3A engine for the LTV and Descent Stage, and 3
Kaiser Marquardt R-40A engines for the Ascent Stage.
The fuel (propellant) mass values contained in this sheet are thought
to be reasonable estimates of the fuel that would be required during each
stage of the Reference Mission if the vehicle dry masses were known.
However, since the vehicle dry masses that are used to compute these fuel
masses are subject to a good deal of uncertainty, the fuel masses
themselves must also be treated as rather uncertain.
Future version of this page will feature:
Copyright © 2007 Artemis Society International, for the
contributors. All rights reserved.
- Updated Delta-V and mass numbers
- More detailed propellant usage breakdowns for all craft
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John M. Kruep.
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Updated Sun, Aug 1, 1999.