Computational modeling of low reynolds number micronozzle performance

Computational modeling of low reynolds number micronozzle performance

Due to their simplicity, low thrust cold-gas propulsion systems have the potential to provide orbital maneuvering capability for small, micro- and even nano-satellites. Each specific mission where cold gas thrusts will be used places a unique set of requirements on the system. For example, micro-spa...

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Veröffentlicht in:Scientific and technical aerospace reports 2003-02, Vol.41 (4)
Hauptverfasser: Ketsdever, Andrew D, Wadsworth, Dean C, Ivanov, Mikhail S, Markelov, Guenadi N
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Ivanov, Mikhail S
Markelov, Guenadi N
description Due to their simplicity, low thrust cold-gas propulsion systems have the potential to provide orbital maneuvering capability for small, micro- and even nano-satellites. Each specific mission where cold gas thrusts will be used places a unique set of requirements on the system. For example, micro-spacecraft with masses of 1 - 50 kg, will require thrust levels for typical orbital maintenance maneuvers of 0.1 - 1OmN. Missions which require precise attitude control, where the most important factor is a very low thrust will require thrust levels between 10 - 100 micro N. to obtain these low thrust values, small nozzle dimensions and low chamber pressures are usually used.
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source U.S. Government Documents; Alma/SFX Local Collection
title Computational modeling of low reynolds number micronozzle performance
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