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Suboptimal Midcourse Guidance with Terminal-Angle Constraint for Hypersonic Target Interception

机译：具有终端角约束的次优中途制导，用于高超声速目标拦截

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摘要

For the problem of hypersonic target interception, a novel midcourse guidance method with terminal-angle constraint is proposed. Referring to the air-breathing and the boost-gliding hypersonic targets, flight characteristics and difficulties of interception are analyzed, respectively. The requirements of midcourse guidance for interceptors are provided additionally. The kinematics model of adversaries is established concerning line-of-sight coupling in longitudinal and lateral planes. Suboptimal guidance law with terminal-angle constraint, specifically the final line-of-sight angle or impact angle, is presented by means of model predictive static programming. The trajectory is optimized and the load factor would finally converge after penalizing control sequence and output deviations. The realization of terminal angle is firstly verified with a constant speed target. A full interception scenario is further simulated focusing on a typical boost-gliding target, which flies along a skipping trajectory. Results show the success of providing handover conditions for intercepting hypersonic targets.
机译：针对高超声速目标的拦截问题，提出了一种具有终端角约束的中途制导方法。分别参照呼吸呼吸和助推滑行高超声速目标，分别分析了飞行特性和拦截困难。另外提供了拦截器的中途制导要求。建立了关于纵向和横向平面上视线耦合的对手运动学模型。通过模型预测静态规划，给出了具有终端角约束的次优制导律，特别是最终的视线角或撞击角。优化了轨迹，并且在惩罚了控制序列和输出偏差之后，负载因子最终会收敛。首先以恒定速度目标来验证端角的实现。以典型的助推滑行目标为目标，进一步模拟了完全拦截场景，该目标沿着跳跃轨迹飞行。结果表明成功提供了用于拦截高超声速目标的切换条件。

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  • 来源
    《International journal of aerospace engineering》 |2019年第2期|6161032.1-6161032.13|共13页
  • 作者

    Wan Shizheng; Chang Xiaofei; Li Quancheng; Yan Jie;

  • 作者单位

    Northwestern Polytech Univ, Sch Astronaut, Xian 710072, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sch Astronaut, Xian 710072, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sch Astronaut, Xian 710072, Shaanxi, Peoples R China;

    Northwestern Polytech Univ, Sch Astronaut, Xian 710072, Shaanxi, Peoples R China;

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