高超声速临近空间飞行器铰链力矩最小俯冲弹道设计

Design of Dive Trajectory of Hypersonic Near-Space Vehicle With Minimum Hinge Moment

为解决高超声速临近空间飞行器俯冲段铰链力矩过大问题,给出了一种降低铰链力矩的俯冲弹道设计方法.在建立俯冲弹道优化模型的基础上,利用Gauss伪谱法将弹道优化问题转化为非线性规划问题,进而将其作为极大极小优化问题采用序列二次规划方法进行求解,其中优化的初值由按照最优导引方式生成的初始弹道获得.在普通台式机上耗时约2min,获得的优化弹道铰链力矩峰值下降达67%,并且各种约束条件均可满足,采用美国GAV-H飞行器总体和气动参数进行了铰链力矩最小俯冲弹道仿真,分析了最优俯冲起点的选取策略,结果表明,该铰链力矩最小俯冲弹道设计方法具有可行性.

To solve the problem that hypersonic near-space vehicle bring a big hinge moment in dive phase,a dive trajectory design method which can depress the hinge moment was proposed.Based on the built dive trajectory optimization model,the trajectory optimization problem was transformed to NLP（Nonlinear Programming） problem by using Gauss pseudospectral method（GPM）,and then the NLP problem was treated as minimax problem to solve by using SQP method.The initial value of optimization parameter was obtained from the initial trajectory created by optimal guidance law.The optimization which consumes about 2 minutes on common PC show that hinge moment peak value falls by 67%,and all the constraints can be satisfied.The dive trajectory with minimum hinge moment was simulated by adopting overall parameters and aerodynamic parameters of American CAV-H vehicle.The selection strategy of optimal dive starting-point was analyzed.The result shows that the design method for dive trajectory with minimum hinge moment is feasible.