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论文:2014,Vol:32,Issue(2):213-219 |
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引用本文： |
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朱战霞, 陈鹏, 唐必伟. 基于滑模方法的空空导弹一体化制导控制律设计[J]. 西北工业大学 |
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Zhu Zhanxia, Chen Peng, Tang Biwei. Designing Integrated Guidance and Control law for Air to Air Missile Based on Sliding Mode Control[J]. Northwestern polytechnical university |
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| 基于滑模方法的空空导弹一体化制导控制律设计 |
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| 朱战霞1,2, 陈鹏1,2, 唐必伟1,2 |
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1. 西北工业大学 航天学院, 陕西 西安 710072;
2. 航天飞行动力学技术国家级重点实验室, 陕西 西安 710072 |
| 摘要: |
| 对于目标任意机动的三维拦截情况,空空导弹一体化制导控制系统模型呈现非线性、耦合和不确定特性,使控制器设计困难。为此,首先对导弹非线性耦合控制系统模型进行简化,得到三通道近似线性化模型,同时认为通道间的耦合项未知有界。在此基础上,推导俯仰和偏航通道的一体化制导控制系统模型。之后考虑干扰的不确定性,利用滑模控制响应快速、对参数变化及扰动不敏感等优点,设计了空空导弹一体化滑模自适应制导控制律,并基于Lyapunov理论证明了其稳定性。数值仿真结果表明,目标任意机动情况下,该一体化制导控制律不仅能够保证导弹命中精度,而且可同时保证弹体姿态的稳定,相对于传统方法,该方法有更好的拦截效果。 |
| 关键词:
一体化制导控制律
滑模控制
空空导弹
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| Designing Integrated Guidance and Control law for Air to Air Missile Based on Sliding Mode Control |
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| Zhu Zhanxia1,2, Chen Peng1,2, Tang Biwei1,2 |
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1. College of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. National Key Laboratory of Aerospace Flight Dynamics, Xi'an 710072, China |
| Abstract: |
| For the 3D interception of an arbitrarily maneuvering target, it is difficult to design the controller of an air to air missile' s integrated guidance and control system because its model is nonlinear, coupling and uncertain. Therefore, we simplify the model of the nonlinear and coupling control system and obtain the approximately linear model with three channels. On these bases, we establish the pitch and yaw channel integrated guidance and control model. Taking into account the uncertainty of disturbance, we use the sliding mode control, which has rapid re-sponse and is not sensitive to parameter change and disturbance, to design the air to air missile' s adaptive and in-tegrated guidance and control law and then prove its stability with the Lyapunov method. To verify the effectiveness of the integrated guidance and control law, we carry out its simulation;the results, given in Figs.2 through 5 and Tables 2 and 3, and their analysis show preliminarily that the integrated guidance and control law can guarantee the accuracy of the air to air missile hitting an arbitrarily maneuvering target and guarantee the stability of its attitude;thus it is more effective for interception. |
| Key words:
air to air missiles
control
controllers
design
functions
Lyapunov functions
missiles
mathematical models
sliding model control
stability
integrated guidance and control law
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| 收稿日期: 2013-06-02
修回日期:
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| DOI: |
| 通讯作者:
Email： |
| 作者简介: 朱战霞(1973-),女,西北工业大学教授、博士生导师,主要从事飞行器飞行动力学与控制、空间操作地面实验方法研究。
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| 作者相关文章 |
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| 朱战霞 在本刊中的所有文章 |
| 陈鹏 在本刊中的所有文章 |
| 唐必伟 在本刊中的所有文章 |
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参考文献: |
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