| 运载器饱和非线性姿态控制系统稳定性分析 |
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| 引用本文： | 甘永梅,周凤岐,周军.运载器饱和非线性姿态控制系统稳定性分析[J].航天控制,1999(2). |
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| 作者姓名： | 甘永梅 周凤岐 周军 |
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| 作者单位： | 西北工业大学航天工程学院 |
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| 摘 要： | 简要介绍了用描述函数分析饱和非线性系统稳定性的方法，然后在此基础上给出了适合于工程的饱和非线性系统稳定裕度的定义，研究了舵偏角不满足近似关系时，正弦函数非线性对姿控系统稳定性的影响，最后计算了某运载器的伺服机构处于饱和状态时姿态控制系统的稳定裕度。
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| 关 键 词： | 运载火箭 非线性系统 姿态控制 稳定性分析 |
Stability Analysis of Stature Nonlinear Attitude Control System for Launch Vehicle |
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| Gan Yongmei\ Zhou Fengqi\ Zhou Jun College of Astronautics,Northwestern Polytechnical University,Xian.Stability Analysis of Stature Nonlinear Attitude Control System for Launch Vehicle[J].Aerospace Control,1999(2). |
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| Authors: | Gan Yongmei\ Zhou Fengqi\ Zhou Jun College of Astronautics Northwestern Polytechnical University Xian |
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| Institution: | Gan Yongmei\ Zhou Fengqi\ Zhou Jun College of Astronautics,Northwestern Polytechnical University,Xian 710072 |
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| Abstract: | The analysis method of stability for stature nonlinear system with describing function is introduced in the paper at first. Then, on the basis of it, the concepts of stability margin similar to those usually used in engineering is defined and the influence of sine nonlinear function to the stability of attitude control system is studied when the steer bias angle is very large. At last, the stability margin of attitude control system is calculated when the servo mechnism of the launch vehicle is statured. |
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| Keywords: | Launch vehicle\ Nonlinear system\ Attitude control Stability analysis |
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