建立了大气层内高超声速飞行器轨迹优化无因次数学模型,提出了一种求解最优两点边值问题的改进型伴随方法,并证明其算法收敛性,将其用于以固体火箭发动机为动力的高超声速飞行器稠密大气层内上升段轨迹优化问题中,在有弯曲力矩约束的前提下,间接得到一组平滑控制量。仿真结果表明,该方法快速、有效、可靠。 A non-dimensional mathematical model of trajectory optimization of hypersonic vehicles in the atmosphere was established. An improved concomitant method to solve the optimal two-point boundary value problem was proposed and its convergence was proved. The algorithm was applied to the solid rocket motor In the hypersonic vehicle hypersonic trajectory optimization problem, a set of smoothing control variables are indirectly obtained under the constraint of bending moment. Simulation results show that the method is fast, effective and reliable.