基于间接伴随法的大气层内高超声速飞行器最优上升轨迹研究  

Indirect Adjoint Method-Based Endoatmospheric Ascent Trajectory Optimization for Hypersonic Vehicle

作　　者：佘智勇[1] 马广富[1] 沈作军[2] 

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150001 [2]北京航空航天大学,北京100191

出　　处：《宇航学报》2010年第8期1951-1957,共7页Journal of Astronautics

基　　金：国家自然科学基金(60774062)

摘　　要：利用修正的无量纲因子,建立了适用于大气层内高速飞行器数值优化的数学模型。创新地采用欧氏空间中超立方体顶点坐标作为协状态初始值的方法解决了伴随方法的初始值估计难题,实现了间接伴随法在最优轨迹优化中的应用。完成并给出了该方法在真空状态和有空气动力存在的情况下轨迹优化结果,并在控制约束存在的前提下,对上升段轨线进行重规划,仿真结果表明,该方法快速、有效,且具有在线制导的应用潜力。Modified non-dimensional factors are used to derive a dynamic model of endoatmospheric hypersonic vehicles suitable for numerical optimization.Indirect adjoint method is applied for solving the two point boundary value problem of endoatmospheric ascent trajectory optimization.A method for initial value estimation is proposed and a vacuum solution is obtained first.Then the aerodynamic effects are introduced gradually and a convergence solution with control constraints is reached..Simulation results are presented to demonstrate the effectiveness of this proposed method and its potential for onboard closed-loop guidance.

关 键 词：伴随法 初值估计 轨迹线性化 大气层内 上升段轨迹优化 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]