面向RBCC模态转换的上升段轨迹优化方法  

Ascent trajectory optimization method for RBCC modal transition

作　　者：郭建国[1] 胡冠杰 郭宗易[1] Guo Jianguo;Hu Guanjie;Guo Zongyi(Institute of Precision Guidance and Control,Northwestern Polytechnical University,Xi'an 710072,China)

机构地区：[1]西北工业大学航天学院精确制导与控制研究所,西安710072

出　　处：《空天技术》2024年第5期71-80,共10页Aerospace Technology

基　　金：国家自然科学基金(5227120749)。

摘　　要：针对采用火箭基组合循环(Rocket-Based Combined Cycle,RBCC)动力系统的空天飞行器上升飞行段轨迹优化问题,面向RBCC多种工作模态建立了空天飞行器上升段数学模型,为降低所构建轨迹优化问题的难度,提出了一种基于多项式方法的攻角-速度上升剖面,将原轨迹优化问题转化为参数/轨迹协同优化问题。考虑到RBCC模态转换下多重约束和多种参数的优化需求,基于改进粒子群算法提出了一种参数/轨迹协同优化方法,全面提升了轨迹优化算法的搜索能力和收敛速度。通过多场景下的仿真验证和对比分析结果表明,所提出的方法可以有效适应RBCC模态转换下的上升段轨迹优化设计。Aiming at the trajectory optimization issue of the aerospace vehicle ascent stage using the rocket-based combined cycle(RBCC)power system,the mathematical model of the aerospace vehicle ascent stage is established for the various operating modes of RBCC.In order to reduce the difficulty of the constructed trajectory optimization issue,an ascent profile of angle-of-attack and velocity based on the polynomial method is proposed.The original trajectory optimization issue is transformed into a parameter/trajectory co-optimization problem.Considering the optimization needs of multiple constraints and multiple parameters under RBCC mode conversion,a parameter/trajectory co-optimization method is proposed based on the improved particle swarm algorithm.The search capability and convergence speed of the trajectory optimization algorithm are comprehensively improved.The simulation verification and comparative analysis results in multiple scenarios show that the proposed method can be effectively adapted to the ascent stage trajectory optimization design under the RBCC mode conversion.

关 键 词：组合动力 空天飞行器 轨迹优化 上升段 粒子群算法 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]