| 临近空间飞行器建模及气动力/RCS组合控制系统仿真 |
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| 引用本文： | 徐星光,李树盛,魏清新,等. 临近空间飞行器建模及气动力/RCS组合控制系统仿真[J]. 战术导弹技术, 2014, 0(1): 15-21 |
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| 作者姓名： | 徐星光 李树盛 魏清新 等 |
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| 作者单位： | 北京机电工程研究所,北京100074 |
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| 摘 要： | 针对临近空间飞行器飞行环境、动力特性复杂的特点,提出了临近空间飞行器的一种简化建模思路,并在此基础上设计控制方法。用小扰动线性化模型简化临近空间飞行器,并分析其气动特性。设计气动力和气动力/直接力两套控制系统,重点分析确定了点火时间和喷气量。用Matlab/Simulink进行仿真,仿真结果表明,采用气动力/直接力组合控制系统达到控制指标,满足被控对象的过载要求。
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| 关 键 词： | 临近空间飞行器 气动力/直接力 小扰动线性化模型 |
Aerodynamic Modeling and Pneumatic Force/Reaction Combination Control System for Near |
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| Xu Xingguang,Li Shusheng,Wei Qingxin,Yang Guang,Huang Daoqing. Aerodynamic Modeling and Pneumatic Force/Reaction Combination Control System for Near[J]. Tactical Missile Technology, 2014, 0(1): 15-21 |
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| Authors: | Xu Xingguang Li Shusheng Wei Qingxin Yang Guang Huang Daoqing |
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| Affiliation: | (Beijing Electro-mechanical Engineeing Institute, Beijing 100074, China) |
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| Abstract: | Aimed at variations of circumstances and aerodynamic characteristics for near space vehicle, a modeling idea of near space vehicle is discussed and control method is designed. Near space vehicle is simplified by the small perturbation linear model and the aerodynamic characteristics of the missile are analyzed. Two sets of control systems are designed. The ignition time and the jet flow are determined, and the aircraft are simulated by Matlab/Simulink. The results show that the controlled object has good dynamic and static characteristics. |
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| Keywords: | near space vehicle pneumatic force/reaction small perturbation linear model |
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