Dynamic Inversion Control of Liquid-filled Spacecraft Attitude and Fuel Sloshing Suppression

被引：0

作者：

Zhu Le-mei ^{[1
]}

Yue Bao-zeng ^{[1
]}

Xie Fang ^{[2
]}

Xu Qun-feng ^{[1
]}

Shi Xiao-qiang ^{[1
]}

机构：

[1] Beijing Inst Technol, Beijing 100190, Peoples R China

[2] AVIC Shenyang Aircraft Design Res Inst, Beijing, Peoples R China

来源：

2013 32ND CHINESE CONTROL CONFERENCE (CCC) | 2013年

关键词：

Liquid-filled spacecraft; Equivalent mechanical model; Dynamic inversion control; Fuel sloshing suppression; Input shaping;

D O I：

暂无

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

Input shaping technique was applied to fuel sloshing suppression induced by the duration of attitude maneuver. A Single pendulum model of liquid-filled spacecraft was built, whose dynamical coupled equations were deduced, and a nonlinear dynamic inversion control also established. The ZVD input shaper was designed basing on the frequency and damping of fuel sloshing. The lows between preset controlling system ZVD input shaper and shaping of input commands were revealed. At the end of this paper, the results of numerical simulation were used to verify the effectiveness of attitude stabilization of spacecraft when using the new controlling system.

引用

页码：363 / 368

页数：6

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