可用于轨道重构的舵面控制配平特性分析方法  

Analysis of Control Trimming Characteristics for Trajectory Reshaping

作　　者：解永锋 李森[2] 张群 陈佳晔 XIE Yong-feng;LI Sen;ZHANG Qun;CHEN Jia-ye(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China;China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]北京宇航系统工程研究所,北京100076 [2]中国运载火箭技术研究院,北京100076

出　　处：《计算机仿真》2023年第6期26-31,共6页Computer Simulation

摘　　要：针对重复使用火箭助推级无动力升力式返回任务,为提高飞行器对操纵舵面故障的适应性,提出了一种操纵舵面控制配平特性量化的快速计算方法。将多操纵舵面的控制分配问题转化为混合整型线性规划问题,并通过分析操纵舵面故障下的配平特性,建立反映控制配平特性的迎角-马赫数约束条件。将属于六自由度模型的配平效应引入到三自由度动力学模型中,与其它路径约束一起用于故障下返回可达域计算和应急返回轨道重构。仿真结果表明,上述方法可以快速量化评估舵面故障对控制配平特性造成的影响,提高轨道重构算法计算效率和适应性。Aiming at unpowered lifting entry missions of the reusable rocket booster,a rapid calculation method of control surface trimming characteristics is proposed to improve the adaptability of the vehicle to control surface fail-ures.The control allocation problem of multiple control surfaces is transformed into a mixed-integer linear program-ming problem,and the angle of attack-Mach number constraints can be established through trimming characteristics analysis of control surface failures.Trim effects that are components of six-degree-of-freedom models are included in the three-degree-of-freedom dynamical models through control-induced attack-Mach constraints that can be used for footprint calculation and emergency trajectory generation under failure conditions together with other path con-straints.Numerical simulations have demonstrated the effectiveness of the approach proposed.Numerical simulations show that the proposed method can rapidly quantify and evaluate the effect of control surface failures,and improve the calculation efficiency and adaptability of trajectory reshaping algorithms.

关 键 词：重复使用火箭助推级 无动力返回 控制分配 配平特性 轨道重构 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]