固体助推飞行器大气层内闭环制导方法  

Endo-atmospheric Closed-loop Guidance Method for Solid-boosted Vehicle

作　　者：郭杰[1] 宋满金 柳青 唐胜景[1] GUO Jie;SONG Manjin;LIU Qing;TANG Shengjing(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;Beijing Institute of Aerospace Technology,Beijing 100074,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]北京空天技术研究所,北京100074

出　　处：《宇航学报》2023年第6期863-873,共11页Journal of Astronautics

基　　金：航天科技联合基金项目(20190014)。

摘　　要：针对固体火箭助推飞行器大气层内制导问题,提出一种能够严格约束终端攻角的在线闭环制导方法。根据控制量对轨迹的不同影响能力,选择合适的飞行剖面,提高轨迹调整能力。设计具有解析多项式形式的飞行剖面,通过实时更新剖面约束条件实现对终端姿态的精确控制,解决终端姿态约束问题。设计剖面参数在线更新策略,在每个制导周期内,采用数值算法在线搜索剖面参数完成剖面更新,可以直接求得实际控制量,并满足终端高度和终端弹道倾角约束,为载荷后续飞行创造初始条件。仿真结果表明,在气动参数和发动机参数不确定情况下,终端攻角均在约束范围内,且波动不超过0.3°,高度误差小于10 m,具有较强的鲁棒性。Aiming at the endo-atmospheric guidance for solid-boosted vehicle,an online closed-loop guidance method which can strictly constrain the terminal angle of attack is proposed.To improve the trajectory adjustment ability,a suitable flight profile is selected according to the different effects of control variables to the trajectory.The flight profile with analytic polynomial form is designed,and the terminal attitude constraint is controlled precisely by updating the profile constraint conditions in real time.Within each guidance cycle,the numerical algorithm is used to search profile parameters online to complete profile updating.The actual control variables can be obtained directly,and the constraints of terminal altitude and terminal trajectory inclination can be satisfied,thus creating initial conditions for the subsequent flight of loads.The simulation results show that when the aerodynamic parameters and engine parameters are uncertain,the terminal angle of attack is within the constraint range,the fluctuation is less than 0.3°,and the height error is less than 10 m,which has strong robustness.

关 键 词：固体火箭 大气层内 闭环制导 俯仰角剖面 攻角约束 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]