摘要
针对变质心高超声速再入飞行器,设计了一种以扩展比例制导为基础的预测制导律,通过制导律参数调整,实现弹道抬升,满足终端速度约束的要求。同时,采用数值预测-校正的方法,实现了对制导参数同步计算以满足制导系统性能指标,解决了在多种偏差环境下制导参数的选取难度较大的问题,为变质心高超声速再入飞行器工程实践中的制导律设计提供参考。
Aiming at the hypersonic reentry vehicle with degenerated centroid,this paper designs a predictive guidance law based on extended proportional guidance,which can adjust the guidance law parameters to achieve ballistic elevation and meet the requirements of terminal speed constraints.At the same time,the numerical prediction-correction method is adopted to realize the synchronous calculation of the guidance parameters to meet the performance indicators of the guidance system.The design solves the difficult problem of selecting the guidance parameters in a variety of deviation environments,and provides reference for guidance law design in reentry aircraft engineering practice.
作者
樊博璇
陈桂明
李乔扬
高琛
Fan Boxuan;Chen Guiming;Li Qiaoyang;Gao Chen(Rocket Force Engineering University,Xi'an 710025;The First Military Representative Office of the Rocket Force Equipment Department in Xi'an Area,Xi'an 710025)
出处
《航天制造技术》
2021年第2期15-22,共8页
Aerospace Manufacturing Technology
关键词
变质心控制
机动突防
制导律
degeneration of center of mass control
maneuver penetration
guidance law
