摘要
针对滑翔段到巡航段的过渡段控制问题,在考虑地球自转和冲压约束及巡航段初始状态约束条件下,建立了导弹控制律设计模型.运用Gauss伪谱法将最优控制问题转换为非线性规划问题,利用SNOPT对非线性规划问题进行求解.仿真结果表明Gauss伪谱法对导弹滑翔段到巡航段的过渡段最优控制律求解是有效的。
Aiming at the control problem of glide stage to cruise stage, considering rotation of the Earth and stamping constraint and ini- tial state constraint of the cruise stage, control law design model has been build. Optimal control problem have been translated to nonlin- ear programming problem Using Gauss pseudospeetral methods. Nonlinear programming problem has been solved by SNOPT. The simu- lation results show that Gauss pseudospectral methods can salve optimal control law problems of glide stage to cruise stage.
出处
《控制工程》
CSCD
北大核心
2013年第5期906-909,共4页
Control Engineering of China
基金
装备技术基础项目(EP114054)
关键词
导弹过渡段
GAUSS伪谱法
最优控制
SNOPT软件包
transitional section of missile
Gauss pseudospectral methods
optimal control
SNOPT software＇ package
