PULSE-MODULATED CONTROL SYNTHESIS FOR A FLEXIBLE SPACECRAFT

被引：64

作者：

ANTHONY, TC ^{[1
]}

WIE, B ^{[1
]}

CARROLL, S ^{[1
]}

机构：

[1] NASA,GEORGE C MARSHALL SPACE FLIGHT CTR,DIV CONTROL SYST,HUNTSVILLE,AL 35812

来源：

JOURNAL OF GUIDANCE CONTROL AND DYNAMICS | 1990年 / 13卷 / 06期

关键词：

D O I：

10.2514/3.20574

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The describing function method is employed for the nonlinear control analysis and design of a flexible spacecraft equipped with pulse-modulated reaction jets. The method provides a means of characterizing the pulse modulator in terms of its gain and phase for structural mode limit-cycle analysis. Although the describing function method is inherently inexact and is not widely used in practice, a new way of utilizing it for practical control design problems is presented. It is shown that the approximations inherent in the method can be accounted for as a modeling uncertainty for the nonlinear control robustness analysis. The pulse-modulated control system of the INTELSAT 5 spacecraft is used as an example to illustrate the concept and methodology developed in the paper. The nonlinear stability margins predicted by the describing function analysis are verified from nonlinear simulations.

引用

页码：1014 / 1022

页数：9