一种考虑视场角约束的自适应偏置比例末制导律设计  

Biased Proportional Terminal Guidance with Line of Sight Angle Constraint

作　　者：程云鹏 周昌伟 严东升[1] 贾平会 颜楚雄 CHENG Yunpeng;ZHOU Changwei;YAN Dongsheng;JIA Pinghui;YAN Chuxiong(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）》2023年第4期142-146,共5页Missiles and Space Vehicles

摘　　要：以具有终端落角和侧窗探测范围约束的机动再入飞行器为研究对象,通过设计末制导律来实现飞行器捕获目标后定向打击的目标。针对机动再入飞行器侧窗探测带来的部分探测域缺失问题,首先建立目标的相对运动关系模型,然后建立一种广义偏置比例导引律,解决了末攻击段导引头视场稳定跟踪问题,在此基础上,设计一种自适应比例系数优化方法,有效提高了飞行器末攻击段的制导精度。最后,通过数值仿真研究表明,该制导方案能够有效解决有限视场约束问题并控制飞行器终端落角范围,具有较高的制导精度。The maneuvering reentry vehicles with terminal landing and side window detection range constraints is taken as the research object,and a novel terminal guidance law is designed to achieve the problem of directional strike after the vehicle captures the target.In order to solve the problem of partial missing detection caused by wave impermeability,firstly,the relative motion relationship model of the target in established.Secondly,a generalized biased proportional navigation law is established to solve the problem of field of view stable tracking of the seeker in terminal phase.And then,an adaptive proportional coefficient optimization method is designed to effectively improve the guidance accuracy of the terminal phase.Finally,extensive simulations are conducted to verify the design features of the algorithm.

关 键 词：机动再入飞行器 末制导 视场约束 落角约束 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]