考虑视场角的飞行时间和末端倾角控制导引律  

Impact Time and Angle Control Guidance Law with Look-angle Constraint

作　　者：康珅 赵洪[1] 卜奎晨[1] 高峰[1] 钟婧佳 Kang Shen;Zhao Hong;Bu Kui-chen;Gao Feng;Zhong Jing-jia(China Academy of Launch Vehicle Technology,Beijing,100076)

机构地区：[1]中国运载火箭技术研究院,北京100076

出　　处：《导弹与航天运载技术》2020年第5期58-61,66,共5页Missiles and Space Vehicles

摘　　要：针对飞行器飞行时间和末端倾角控制问题,采用时间多项式设计前置角变化规律,提出了一种带有飞行时间和末端倾角约束的导引律,同时给出了一种基于指令限幅的视场角约束方法。首先设计前置角边界条件,保留多项式中两个自由系数,之后采用线性化模型推导了满足飞行时间和末端倾角约束的系数解析解,并设计了在线更新方法提高系数在非线性模型中的适应性,并设计了指令限幅机制用于满足制导过程中的视场角约束。最后通过数值仿真验证了所提出的导引和视场角约束方法的有效性。A guidance law to control impact time and angle under look-angle constraint is proposed.The proposed guidance law is originated from look-angle shaping using time-polynomial and the look-angle constraint is also considered.The time polynomial of look angle is shaped with respect to the boundary conditions which allows two adjustable coefficients,namely the guidance gain,for the desired impact time and angle,followed by the analytical solutions in linear domain.The guidance gain is further updated continuously based on frame convention to adapt to nonlinear model and a method to ensure look-angle constraint during the flight is provided.Numerical simulations are provided to demonstrate the effectiveness of the proposed guidance law.

关 键 词：飞行时间约束 末端倾角约束 视场角约束 导引律 

分 类 号：V421.1[航空宇航科学与技术—飞行器设计]