| 引用本文: | 万雨君,陈克俊,刘鲁华,等.高超声速飞行器巡航段多约束制导方法.[J].国防科技大学学报,2014,36(1):11-16.[点击复制] |
| WAN Yujun,CHEN Kejun,LIU Luhua,et al.Research on guidance law with multiple constraints of hypersonic vehicle for cruise phase[J].Journal of National University of Defense Technology,2014,36(1):11-16[点击复制] |
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| 高超声速飞行器巡航段多约束制导方法 |
| 万雨君, 陈克俊, 刘鲁华, 吴杰 |
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(国防科技大学 航天科学与工程学院，湖南 长沙 410073)
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| 摘要: |
| 针对高超声速飞行器巡航段飞行，建立了等高等速飞行的平衡条件，并对飞行器能否满足平衡条件开展分析。基于平衡条件提出了一种能够满足飞行过程中多约束条件以及终端航向角约束的制导方法，推导得到了满足多约束条件的最优制导律。该方法所有制导指令均采用解析公式实时获得，具有较强适应性。在各种偏差条件下对方法进行了仿真，仿真结果验证了方法的有效性。 |
| 关键词: 高超声速飞行器 平衡条件 巡航段 多约束条件 制导方法 |
| DOI：10.11887/j.cn.201401003 |
| 投稿日期：2013-05-08 |
| 基金项目:国家自然科学基金资助项目（61104200） |
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| Research on guidance law with multiple constraints of hypersonic vehicle for cruise phase |
| WAN Yujun, CHEN Kejun, LIU Luhua, WU Jie |
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(College of Aerospace Science and Engineering,National University of Defense Technology, Changsha 410073, China)
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| Abstract: |
| The equilibrium condition of hypersonic vehicle during cruise phase is modeled, under which the vehicle can maintain constant speed and altitude. It analyzed the equilibrium conditions that the vehicle can satisfy. Based on the conditions, a guidance law with multiple constraints and terminal course angular constraint is proposed, and the analytic solution is concluded. The method is adaptive since the guidance command is obtained through the analytic expressions in real time. In the end, simulations under different deviations have proved the method is effective. |
| Keywords: hypersonic vehicle equilibrium condition cruise phase multiple constraints guidance law |
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