| 基于特征模型的再入飞行器制导律设计 |
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| 引用本文： | 张钊,胡军,王勇.基于特征模型的再入飞行器制导律设计[J].空间控制技术与应用,2010,36(4):12-17,30. |
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| 作者姓名： | 张钊 胡军 王勇 |
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| 作者单位： | 北京控制工程研究所;空间智能控制技术国家级重点实验室; |
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| 摘 要： | 研究了一种大升阻比的高超声速飞行器的再入制导问题．应用基于特征模型的自适应控制理论，提出了一种跟踪参考阻力加速度的制导方法，同时通过跟踪飞行方位角，来修正飞行器侧向航程．这种基于特征模型的自适应控制方法不需要通过数据拟合来获得气动升力与阻力的解析表达式，克服了飞行器在再入飞行中，气动数据不断变化时造成的困难．通过跟踪飞行方位角来修正倾斜角指令，可以获得比倾斜角翻转方法更精细的对侧向航程的控制能力．六自由度仿真结果表明，文中设计的制导方法可以达到调整侧向航程的目的，但其代价是损失总航程．
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| 关 键 词： | 再入制导 特征模型 阻力加速度 |
Characteristic Model-Based Reentry Vehicle Guidance Law Design |
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| ZHANG Zhao,HU Jun,WANG Yong.Characteristic Model-Based Reentry Vehicle Guidance Law Design[J].Aerospace Contrd and Application,2010,36(4):12-17,30. |
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| Authors: | ZHANG Zhao HU Jun WANG Yong |
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| Institution: | ZHANG Zhao1,2,HU Jun1,WANG Yong1,2(1.Beijing Institute of Control Engineering,Beijing 100190,China,2.National Key Laboratory of Science and Technology on Space Intelligent Control,China) |
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| Abstract: | A novel drag acceleration tracking guidance law is proposed for a hypersonic reentry vehiclewith high lift-drag ratio.By applying the characteristic model-based adaptive control method,a drag ac-celeration tracking guidance method is proposed together with a flight azimuth angle tracking used to mod-ify lateral distance.The characteristic model-based adaptive control method do not need the analyticalform of the aerodynamic lift and drag forces,which are often obtained by curve fitting of the trimmedflight d... |
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| Keywords: | reentry guidance characteristic model drag acceleration |
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