改进滤波的再入飞行器风干扰补偿鲁棒制导律  

Wind disturbance compensation robust guidance law for re-entry vehicles based on an improved filtering method

作　　者：唐明明 都延丽 成巍 刘燕斌 TANG Mingming;DU Yanli;CHENG Wei;LIU Yanbin(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;Beijing Institute of Applied Meteorology,Beijing 100029,China)

机构地区：[1]南京航空航天大学航天学院,江苏南京211106 [2]北京应用气象研究所,北京100029

出　　处：《哈尔滨工程大学学报》2024年第9期1687-1694,共8页Journal of Harbin Engineering University

基　　金：中央高校基本科研业务费专项资金(NS2021061).

摘　　要：为了解决滑翔式再入飞行器受临近空间风干扰影响的问题,本文基于预测校正制导方法,对风场引起的落点误差进行了分析。通过自适应滤波方法在线预估误差,并进行末端点位置调整来补偿风场对飞行器再入路径的影响。同时,滚动优化倾侧角幅值参数,使参数随待飞航程的变化而更新,从而提高末端制导精度。使用蒙特卡罗法对不同风场影响下的飞行路径进行仿真,对比该制导律的优化效果。仿真结果表明:风速预测值标准差在0.3以内,设计的制导律能够将末端速度控制在15 m/s以内,落点误差在800 m以内,更接近于无风状态的落点。To solve the problem of gliding re-entry vehicles being affected by wind interference from near space,the impact point error caused by the wind field is analyzed using the predictor-corrector guidance method.The error is estimated online by the adaptive filtering method,and the position of the terminal point is adjusted to compensate for the impact of the wind field on the re-entry path of the vehicle.At the same time,the amplitude parameter of the bank angle is determined by receding horizon optimization so that the parameter is updated with the change in the range to go,thereby improving the terminal guidance accuracy.Finally,the Monte Carlo method is employed to simulate the flight path under the influence of different wind fields,and the optimization effects of the guidance law are compared.The simulation results show that the standard deviation of the predicted wind speed is within 0.3,and the designed guidance law can control the end velocity within 15 m/s,with an impact error of less than 800 m,which is close to the landing point in a calm state.

关 键 词：自适应滤波 风场 制导律 倾侧角 再入飞行器 预测校正法 蒙特卡罗仿真 鲁棒制导率 

分 类 号：V448.235[航空宇航科学与技术—飞行器设计]