For the entry guidance problem of hypersonic gliding vehicles, an analytical predictor-corrector guidance method based on feedback control of bank angle is proposed. First, the relative functions between the velocity, bank angle and rangeto-go are deduced, and then, the analytical relation is introduced into the predictorcorrector algorithm, which is used to replace the traditional method to predict the range-to-go via numerical integration. To eliminate the phugoid trajectory oscillation, a method for adding the aerodynamic load feedback into the control loop of the bank angle is proposed. According to the quasi-equilibrium gliding condition, the function of the quasi-equilibrium glide load along with the velocity variation is derived. For each guidance period, the deviation between the real time load and the quasi-equilibrium gliding load is revised to obtain a smooth reentry trajectory. The simulation results indicate that the guidance algorithm can adapt to the mission requirements of different downranges, and it also has the ability to guide the vehicle to carry out a large range of lateral maneuvers. The feedback control law of the bank angle effectively eliminates the phugoid trajectory oscillation and guides the vehicle to complete a smooth reentry flight. The Monte Carlo test indicated that the guidance precision and robustness are good.

中文翻译：

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高超音速滑翔飞行器的分析预测器-校正器输入指南

针对高超声速滑翔飞行器的进入制导问题，提出了一种基于坡度角反馈控制的解析预测校正制导方法。首先推导出速度、坡度角和剩余航程之间的相关函数，然后将解析关系引入到预测校正算法中，用于替代传统的通过数值积分预测剩余航程的方法. 为了消除phugoid轨迹振荡，提出了一种在坡度角控制回路中加入气动载荷反馈的方法。根据准平衡滑行条件，推导出准平衡滑行载荷随速度变化的函数。对于每个指导期，修正实时载荷与准平衡滑翔载荷之间的偏差，以获得平滑的再入轨迹。仿真结果表明，该制导算法能够适应不同下行范围的任务要求，并具有引导车辆进行大范围横向机动的能力。坡度角反馈控制规律有效地消除了phugoid轨迹振荡，引导飞行器顺利完成再入飞行。蒙特卡罗测试表明制导精度和鲁棒性良好。坡度角反馈控制规律有效地消除了phugoid轨迹振荡，引导飞行器顺利完成再入飞行。蒙特卡罗测试表明制导精度和鲁棒性良好。坡度角反馈控制规律有效地消除了phugoid轨迹振荡，引导飞行器顺利完成再入飞行。蒙特卡罗测试表明制导精度和鲁棒性良好。