固体火箭技术2012，Vol.35Issue(4)：427-433,7.
助推-滑翔导弹再入弹道快速优化
Rapid re-entry trajectory optimization for boost-glide missile
摘要
Abstract
Rapid re-entry trajectory optimization of near space boost-glide missile was studied via the Legendre-Gauss-Lobatto ( LGL) pseudospectral method. Firstly,an accurate mathematics model in re-entry phase was established based on an improved aerodynamic model. Aiming at the difficulties of the optimization problem in processing of aerodynamic data as well as optimization solving, the steps based on LGL pseudospectral method were listed systemically for solving the optimal re-entry flight trajectory. Then a serial strategy based on LGL pseudospectral method was presented to deal with the difficulties in optimization using the LGL pseudospectral method directly. Finally, the feasibility and the optimality of optimal result were validated by integral propagation method and covector mapping principle,respectively. Simulation results show that computational time required for optimizing one reentry trajectory is 3 -4 s,and thus the computational efficiency is high. Path constrains and boundary constrains are well satisfied, and the precision of this trajectory optimization method is high. The rapid re-entry trajectory optimization with characteristics of multiple constraints, multiple variables and large sparsity is achieved.关键词
临近空间/助推-滑翔导弹/再入弹道优化/伪谱方法/优化控制Key words
near space/ boost-glide missile/ re-entry trajectory optimization/ pseudospectral method/ optimal control分类
航空航天引用本文复制引用
赵欣,闫循良,张金生,王仕成,何安荣..助推-滑翔导弹再入弹道快速优化[J].固体火箭技术,2012,35(4):427-433,7.基金项目
国家自然科学基金项目(60874093) （60874093）
863项目(2011AA7053016). （2011AA7053016）
