共 3 条
- [1] SANSEVERO VJ, 1973, 9TH AIAA SAE PROP C
- [2] SANSEVERO VJ, 1978, 14TH AIAA SAE PROP C
- [3] SUTHERLA.GS, 1966, J SPACECRAFT ROCKETS, V3, P1153
EMPIRICAL SIMULATION-MODEL FOR HYDRAZINE ATTITUDE-CONTROL THRUSTERS
被引：0
作者：
GARG, S
机构：
[1] University of Toronto, Institute for Aerospace Studies, Toronto, ON
基金：
加拿大自然科学与工程研究理事会;
关键词：
Engine performance;
Spacecraft dynamics and control;
Spacecraft simulation;
D O I：
10.2514/3.28016
中图分类号：
V [航空、航天];
学科分类号：
08 ;
0825 ;
摘要：
A simple model of low-thrust catalytic monopropellant hydrazine thrusters is presented for attitude control simulation purposes. It is derived from test results and represents thrust histories much better than a first-order lag over a wide range of pulse widths, for the thrusters used on the Hermes spacecraft. The structure of the model should be applicable to other cases as well. © American Institute of Aeronautics and Astronautics, Inc., 1979, All rights reserved.
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页码：389 / 393
页数：5
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