ADVANCED PROPULSION SYSTEMS FOR SPACE STATION APPLICATIONS.

被引：0

作者：

Fearn, D.G. ^{[1
]}

Wallace, N.C. ^{[1
]}

机构：

[1] Royal Aircraft Establishment, Farnborough, Engl, Royal Aircraft Establishment, Farnborough, Engl

来源：

JBIS. Journal of the British Interplanetary Society | 1987年 / 40卷 / 01期

关键词：

PROPULSION - Aerospace Applications;

D O I：

暂无

中图分类号：

学科分类号：

摘要：

From a consideration of the propulsion requirements of the various elements of the NASA/International Space Station, it is concluded that propellant consumption will be a major cost factor, especially for functions requiring large total impulses. Electric propulsion (EP) systems offer exhaust velocities at least an order of magnitude higher than those of chemical thrusters, so can reduce propellant masses by the same factor. Consequently, it is advocated that EP systems be employed for high impulse tasks such as drag compensation and orbit transfer. It is shown that the propellant mass required for drag compensation on the main Space Station can be reduced from several tonnes annually to a few hundred kilogrammes, and that the Polar Platform's initial orbit transfer manoeuvre can be accomplished for well under 100 kg, rather than the 500-1000 kg needed by a bi-propellant system.

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页码：3 / 10