Optimization of perigee burns for manned interplanetary missions
Abstract
In choosing an engine concept for the rocket vehicle to be used for the initial manned exploration of Mars, the two main factors in the decision should be what can be feasibly built and flight qualified within approximately the next 20 years, and what level of engine performance is required to safely perform these missions. In order to reduce the overall cost in developing this next generation space transportation system, it would be desirable to have a single engine design that could be used for a broad class of missions (for example, cargo and piloted lunar and Mars missions, orbit transfers around the Earth, and robotic missions to the planets). The engine thrust that is needed for manned Mars missions is addressed in this paper. We find that these missions are best served by a thrust level around 75,000 lbf to 100,000 lbf, and a thrust-to-engine weight ratio of about three. This thrust level might best be obtained by clustering five 15,000 lbf or 20,000 lbf engines. It may be better to throttle the engines back from full power between perigee burns, rather than shutting down. 5 refs., 4 figs.
- Authors:
- Publication Date:
- Research Org.:
- EG and G Idaho, Inc., Idaho Falls, ID (United States)
- Sponsoring Org.:
- USDOE; USDOE, Washington, DC (United States)
- OSTI Identifier:
- 6366558
- Report Number(s):
- EGG-M-91031; CONF-9109226-23
ON: DE92003274
- DOE Contract Number:
- AC07-76ID01570
- Resource Type:
- Conference
- Resource Relation:
- Conference: AIAA/NASA/OAI conference on advanced space exploration initiative (SEI) technologies, Cleveland, OH (United States), 3-4 Sep 1991
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 21 SPECIFIC NUCLEAR REACTORS AND ASSOCIATED PLANTS; 32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION; PROPULSION SYSTEMS; PLANNING; THRUSTERS; EFFICIENCY; JET ENGINE FUELS; MARS PLANET; ROCKETS; SPACE FLIGHT; SPACE VEHICLES; WEIGHT; FUELS; PLANETS; VEHICLES; 210600* - Power Reactors, Auxiliary, Mobile Package, & Transportable; 320201 - Energy Conservation, Consumption, & Utilization- Transportation- Air & Aerospace
Citation Formats
Madsen, W W, Olson, T S, and Siahpush, A S. Optimization of perigee burns for manned interplanetary missions. United States: N. p., 1991.
Web.
Madsen, W W, Olson, T S, & Siahpush, A S. Optimization of perigee burns for manned interplanetary missions. United States.
Madsen, W W, Olson, T S, and Siahpush, A S. 1991.
"Optimization of perigee burns for manned interplanetary missions". United States. https://www.osti.gov/servlets/purl/6366558.
@article{osti_6366558,
title = {Optimization of perigee burns for manned interplanetary missions},
author = {Madsen, W W and Olson, T S and Siahpush, A S},
abstractNote = {In choosing an engine concept for the rocket vehicle to be used for the initial manned exploration of Mars, the two main factors in the decision should be what can be feasibly built and flight qualified within approximately the next 20 years, and what level of engine performance is required to safely perform these missions. In order to reduce the overall cost in developing this next generation space transportation system, it would be desirable to have a single engine design that could be used for a broad class of missions (for example, cargo and piloted lunar and Mars missions, orbit transfers around the Earth, and robotic missions to the planets). The engine thrust that is needed for manned Mars missions is addressed in this paper. We find that these missions are best served by a thrust level around 75,000 lbf to 100,000 lbf, and a thrust-to-engine weight ratio of about three. This thrust level might best be obtained by clustering five 15,000 lbf or 20,000 lbf engines. It may be better to throttle the engines back from full power between perigee burns, rather than shutting down. 5 refs., 4 figs.},
doi = {},
url = {https://www.osti.gov/biblio/6366558},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Jan 01 00:00:00 EST 1991},
month = {Tue Jan 01 00:00:00 EST 1991}
}