Dynamic Modeling and Analysis of Spacecraft With Variable Tilt of Flexible Appendages

被引：22

作者：

Guy, Nicolas ^{[1
]}

Alazard, Daniel ^{[2
]}

Cumer, Christelle ^{[1
]}

Charbonnel, Catherine ^{[3
]}

机构：

[1] ONERA Ctr Toulouse, Syst Control & Flight Dynam Dept, F-31055 Toulouse, France

[2] Univ Toulouse, DMIA, ISAE, F-31400 Toulouse, France

[3] DRT SO, Thales Alenia Space, F-06156 Cannes, France

来源：

JOURNAL OF DYNAMIC SYSTEMS MEASUREMENT AND CONTROL-TRANSACTIONS OF THE ASME | 2014年 / 136卷 / 02期

关键词：

Agricultural robots - Attitude control - Closed loop control systems - Linear transformations - Robust control - Solar concentrators;

D O I：

10.1115/1.4025998

中图分类号：

TP [自动化技术、计算机技术];

学科分类号：

0812 ;

摘要：

This article describes a general framework to generate linearized models of satellites with large flexible appendages. The obtained model is parameterized according to the tilt of flexible appendages and can be used to validate an attitude control system over a complete revolution of the appendage. Uncertainties on the characteristic parameters of each substructure can be easily considered by the proposed generic and systematic multibody modeling technique, leading to a minimal linear fractional transformation (LFT) model. The uncertainty block has a direct link with the physical parameters avoiding nonphysical parametric configurations. This approach is illustrated to analyze the attitude control system of a spacecraft fitted with a tiltable flexible solar panel. A very simple root locus allows the stability of the closed-loop system to be characterized for a complete revolution of the solar panel.

引用

页数：10

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