高超声速再入飞行器可达横程分析  

Reachable cross range analysis of hypersonic reentry aerocraft

作　　者：赵国荣[1] 宋超[1] 陈洁[1] 洪海斌[1] 

机构地区：[1]海军航空工程学院控制工程系,烟台264001

出　　处：《战术导弹控制技术》2013年第1期16-21,共6页

基　　金：国家自然科学基金资助项目（61004002）;航空科学基金（211018400）

摘　　要：为使飞行器再入大气层后获得最大可达横程，采用高斯伪谱法（GPM）求解飞行器最优再入轨迹。首先给出了高超声速飞行器再入轨迹优化问题模型，在不考虑过程约束的条件下，选取横程最大为最优性能指标，攻角和倾斜角作为控制量，终端状态受到位置和速度的约束。然后采用GPM将再入轨迹优化问题离散化为非线性规划问题，选取各高斯点上的状态量和控制量作为优化参数。最后利用适合求解大型非线性规划问题的SNOPT软件包对参数最优化问题进行求解，得到再入的最优轨迹。仿真结果表明，该方法对状态初始值并不敏感，容易得到最优解，且不需要对协状态变量初值进行猜测，非常适用于轨迹优化问题的求解。The application of Gauss pseudospectral method （GPM） to hypersonic aerocraft reentry trajectory optimization problem with maximum cross range was introduced. The Gauss pseudospectral method was used to solve the reentry trajecto-ry of the hypersonic vehicle with the maximum cross range. Firstly, the model of hypersonic aircraft entry trajectory optimi- zation control problem was established. Taking no account of course constraint, the maximum cross range was chosen as op- timal performance index, and angle of attack and bank was chosen as control variable. Terminal state variable constraints were position and velocity constraints. Then GPM was applied to change trajectory optimization problem into nonlinear pro- gramming problem （NLP） , and the state variables and control variables were selected as optimal parameters at all Gauss nodes. At last, optimal reentry trajectory was solved by solving the NLP with the help of SNOPT. The simulation results in-dicate that GPM is not sensitive to the initial states and useless to estimate the initial costate variable, and effective to solve trajectory optimization problem.

关 键 词：高超声速 轨迹优化 最大横程 再入 高斯伪谱法 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]