航空学报 > 2021, Vol. 42 Issue (11): 524912-524912   doi: 10.7527/S1000-6893.2020.24912

大气层内模型预测静态规划拦截中制导

周聪1,2, 闫晓东1,2, 唐硕1,2, 吕石1,2   

  1. 1. 西北工业大学 航天学院, 西安 710072;
    2. 陕西省空天飞行器设计重点实验室, 西安 710068
  • 收稿日期:2020-10-21 修回日期:2020-11-30 发布日期:2021-01-14
  • 通讯作者: 闫晓东 E-mail:yan804@nwpu.edu.cn

Midcourse guidance for endo-atmospheric interception based on model predictive static programming

ZHOU Cong1,2, YAN Xiaodong1,2, TANG Shuo1,2, LYU Shi1,2   

  1. 1. School of Astronautics, Northwestern Ploytechnical University, Xi'an 710072, China;
    2. Shaanxi Aerospace Flight Vehicle Design Key Laboratory, Xi'an 710068, China
  • Received:2020-10-21 Revised:2020-11-30 Published:2021-01-14

摘要: 在临近空间机动目标拦截中,拦截器的初始动力段对中制导段乃至末端拦截性能具有重要影响。在模型预测静态规划(MPSP)理论基础上提出了一种初、中制导联合规划制导方法,旨在解决多阶段、快速、最优拦截轨迹规划和制导问题。首先,提出了一种改进的模型预测静态规划方法,该方法不仅可以满足终端约束,还可以生成最优初始状态,并在性能指标中考虑状态变量相关函数。其次,基于等效阻力模型建立了包含动力段与非动力段的两段规划模型,通过采用分段离散以及构建关机点变分关系的方法,避免了内点约束的引入,使MPSP算法可直接求解该两段规划问题。最后,结合提出的MPSP算法以及两段规划模型,实现了终端速度最优的拦截轨迹规划,结合目标预测方法,实现了对机动目标的预测拦截。仿真结果表明,本文方法可提高制导精度和终端速度,且能更好满足对机动目标的拦截需求。

关键词: 临近空间目标, 拦截中制导, 模型预测静态规划, 多阶段规划, 初始状态规划, 预测制导

Abstract: In the scenario of intercepting a near space maneuvering target, the powered ascent phase of the interceptor has a significant impact on the midcourse guidance performance as well as the final interception precision. In this paper, an integrated guidance method is designed based on the model predictive static programming (MPSP) theory, which is able to efficiently generate the optimal trajectory as well as guidance commands for the powered ascent phase and the midcourse phase. First, an improved model predictive static programming method is proposed, which has merits of obtaining the optimal initial state, considering the terminal constraints, and solving the performance index with the states. Second, an equivalent drag model is established, then a two-phase programming model involving the powered and unpowered flight phases is developed. By using the piecewise discretization method and formulating the state variation relationship at the shutdown point, the interior point constraint is avoided, which ensures that the proposed MPSP algorithm can directly solve the two-phase programming problem. Finally, applying the proposed MPSP algorithm and two-phase programming model, the optimal trajectory is achieved to maximum the final speed. With the prediction of the target motion, predictive interception for the maneuvering target is accomplished. Simulation results show that the proposed method can improve the guidance accuracy and the final speed, even for highly maneuvering target.

Key words: near space target, midcourse intercept guidance, model predictive static programming, multi-phase programming, initial state programming, predictive guidance

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