远程机动飞行器地心角修正的制导方法  

Research of Guidance Method with Geocentric Angle Correction for Long Range Maneuvering Vehicle

作　　者：王煜东 方岳[1] 郭珂[1] 颜楚雄 李瑾 WANG Yudong;FANG Yue;GUO Ke;YAN Chuxiong;LI Jin(Beijing Institute of Space Long March Vehicle,Beijing,100076)

机构地区：[1]北京航天长征飞行器研究所,北京100076

出　　处：《导弹与航天运载技术（中英文）》2024年第6期42-46,62,共6页Missiles and Space Vehicles

摘　　要：针对远程机动飞行器长时间在大气层内飞行,传统的带落角约束的比例导引法在末制导段的期望落角受飞行航程地心角的影响较大,不能较好地适应远程机动飞行器落角约束的问题,故提出一种地心角修正的落角约束最优制导律。仿真结果表明该制导方法可以使远程机动飞行器的落角满足落角约束,并且具有一定的鲁棒性。The guidance method for long range maneuvering vehicle is focused.The traditional proportional guidance method with falling angle in the terminal guidance phase is greatly affected by the geocentric angle of the flight range and cannot well adapt to the falling angle constraint of long range maneuvering vehicle.An optimal guidance law with falling angle constraint using geocentric angle is proposed.The simulation results show that the guidance method can make the falling angle of long range maneuvering vehicle content the falling angle constraint,and has certain robustness.

关 键 词：飞行器 比例导引 地心角 落角 最优制导律 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]