多级助推-入轨飞行器上升段高效高精度弹道优化设计  

High Efficiency and High Precision Ascent Trajectory Optimization of Multistage Boost-to-Orbit Flight Vehicle

作　　者：杜文豪 齐欢 DU Wenhao;QI Huan(Beijing Institute of Astronautical Systems Engineering,Beijing 100076,China)

机构地区：[1]北京宇航系统工程研究所,北京100076

出　　处：《宇航总体技术》2024年第6期10-14,共5页Astronautical Systems Engineering Technology

摘　　要：研究了采用多级固体火箭发动机的助推入轨式飞行器的上升段弹道优化问题。为了创造有利的轨道段初始条件,助推段的终端状态被严格约束;多级助推会导致总飞行时间可变,以及质量的突变。针对这一类具有强终端约束的,且截止时间未知的,多段非线性不连续最优控制问题,使用hp自适应的Radau伪谱法获得了合适的结果,并通过与参数优化的对比分析,验证了伪谱法在计算效率以及最优性方面的优势。The ascent trajectory optimization of multistage boost-to-orbit flight vehicle is studied in this article.There are two major difficulties in this problem,first,to get a better initial condition for the orbital segment,the terminal conditions of boost stage must be achieved in a very narrow band;and second,because of the multistage boost,the terminal time is uncertain and the mass changes suddenly.To solve the nonlinear multistage optimal control problem with discontinuous states,uncertain terminal time and strong terminal constraints,the hp-adaptive Radau pseudospectral method is applied and suitable results are obtained.Furthermore,the computational efficiency and the optimality of pseudospectral method are validated,by the comparison with method of parameter optimization.

关 键 词：助推段 弹道优化 最优控制 Radau伪谱法 

分 类 号：V475.1[航空宇航科学与技术—飞行器设计]