摘要
在传统的弹道分段优化设计基础上,针对国外某临近空间飞行器,提出一种全程弹道一体化设计与优化方法。建立包含助推段、变轨段、滑翔段与下压段的复杂多阶段多约束全程弹道优化模型,采用Guass伪谱法进行参数离散,基于遗传算法与序列二次规划法组成的复合优化算法,实现了全程弹道优化仿真计算。仿真结果验证了多阶段多约束优化模型处理方法的可行性,检验了全程弹道一体化设计与优化算法的有效性,为解决各类弹道优化问题提供了一种新的求解思路。
Based on the traditional trajectory segment optimization strategy, an integrative design and optimization method for near space vehicle is proposed. The whole trajectory optimization model which consists of boost phase, orbit-maneuvering phase, coast phase and diving phase is established. Parameter discretization is taken by Gauss pseudo-spectral method, and the whole trajectory optimization simulation is achieved by hybrid GA and SQP Algorithm. Simulation results testify the feasibility of multi-phase and multi-constraint model and the validity of integrative design and optimization method, and provide a new solving thinking for all kinds of trajectory optimization issues.
出处
《导弹与航天运载技术》
北大核心
2015年第1期61-65,共5页
Missiles and Space Vehicles
关键词
临近空间飞行器
多阶段
多约束
一体化设计
弹道优化
Near space vehicle
Multi-phase
Multi-constraint
Integrative design
Trajectory optimization
