In this article, a low-order partial integrated guidance and control (PIGC) design method is proposed for diving hypersonic vehicles to impact ground maneuver target. A three-channel analytical model of body rates is deduced based on acceleration components of the hypersonic vehicle. By combining the analytical model of body rates and relative dynamic model between the hypersonic vehicle and target, three-channel commands of body rates are directly generated based on the extended state observer (ESO) technique, sliding mode control approach, and dynamic surface control theory in the guidance subsystem. In the attitude control subsystem, a sliding mode controller is designed to track the commands of body rates and generate commands of control surface fin deflections. By making full use of acceleration information of the hypersonic vehicle measured by the mounted accelerometer, the proposed PIGC design method provides a novel solution to compensate the unknown acceleration of the ground maneuver target. Besides, the order of design model is also reduced, and the design process is simplified. The effectiveness and robustness of the PIGC design method are verified and discussed by 6DOF simulation studies.

中文翻译：

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一种俯冲高超声速飞行器撞击地面机动目标的低阶部分集成制导与控制方案

本文提出了一种用于俯冲高超声速飞行器撞击地面机动目标的低阶部分集成制导与控制（PIGC）设计方法。基于高超声速飞行器的加速度分量推导出了三通道的车身速率分析模型。通过结合体率分析模型和高超声速飞行器与目标之间的相对动力学模型，基于扩展状态观测器（ESO）技术、滑模控制方法和动态表面控制理论直接生成体率三通道命令在制导子系统中。在姿态控制子系统中，设计了一个滑模控制器来跟踪车身速率的命令并生成控制面翅片偏转的命令。通过充分利用安装的加速度计测量的高超音速飞行器的加速度信息，所提出的PIGC设计方法为补偿地面机动目标的未知加速度提供了一种新的解决方案。此外，还减少了设计模型的阶数，简化了设计过程。PIGC 设计方法的有效性和稳健性通过 6DOF 仿真研究得到验证和讨论。