宇航学报

宇航学报 ›› 2019, Vol. 40 ›› Issue (6): 655-665.doi: 10.3873/j.issn.1000-1328.2019.06.006

• 制导、导航、控制与电子 • 上一篇    下一篇

高超声速滑翔再入定向定速打击末制导算法

王荣刚, 许志, 唐硕, 贾生伟   

  1. 1. 西北工业大学 航天学院, 西安 710072； 2. 南京航空航天大学 飞行器先进设计技术国防重点学科实验室，南京 210016； 3. 中国运载火箭技术研究院，北京 100076
  • 收稿日期:2018-03-20 修回日期:2018-08-31 出版日期:2019-06-15 发布日期:2019-06-25
  • 基金资助:

    国防基础科研项目（A042013102）；国家自然科学基金项目（11672235）

Terminal Guidance with Impact Angle Constraint and Deceleration Control for a Hypersonic Glide Reentry Vehicle

WANG Rong gang, XU Zhi, TANG Shuo, JIA Sheng wei   

  1. 1. Northwestern Polytechnical University， School of Astronautics， Xi’an 710072, China; 2. Key Laboratory of Fundamental Science for National Defense Advanced Design Technology of Flight Vehicle，Nanjing University of Aeronautics and Astronautics，Nanjing 210016, China; 3. China Academy of Launch Vehicle Technology, Beijing 100076, China
  • Received:2018-03-20 Revised:2018-08-31 Online:2019-06-15 Published:2019-06-25

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摘要：

以具有终端落角和落速约束的小升阻比短距滑翔高超声速再入打击飞行器为研究对象，通过引入弹道调整段来实现对飞行器的初步大幅度减速，并使其满足中末制导交班条件，以解决飞行器捕获目标后难以直接对其进行定向定速打击的问题。首先设计了一种变角偏差反馈系数的偏置比例制导律，解决了末端攻击段弹道下压困难以及导引头视场稳定跟踪等问题。在此基础上，建立了一种基于攻角和弹道倾角估计的末端减速指令生成方法，有效解决了基于理想速度曲线减速控制方法精度不足的问题。因此，数值仿真结果表明该制导方案能够有效控制飞行器终端落角和落速，并具有较高的制导精度。

关键词: 高超声速滑翔飞行器, 末制导；减速控制；落角约束

Abstract:

 A short-range low-lift-to-drag ratio hypersonic glide-reentry vehicle with impact angle constraint and deceleration control is selected as the object of study. By introducing a trajectory adjustment phase to make the vehicle satisfy the capturability condition of the terminal guidance phase, the problem of the hypersonic glide-reentry vehicle which is difficult to attack the target directly with impact angle constraint and deceleration control is solved. In order to push down the trajectory and maintain the field of view, a biased proportional guidance law is proposed by adjusting the coefficient of the error feedback. On this foundation, a velocity control order generation method is established based on the estimation of the angle of attack and flight-path angle, to solve the problem of the ideal velocity control order generation method which has a low accuracy. Extensive simulations are conducted to verify the design features of the algorithm.

Key words: Hypersonic glide-reentry vehicle, Terminal guidance, Impact angle control, Deceleration control

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