一种火箭动力助飞高超声速飞行器轨迹优化设计方法

A METHOD OF TRAJECTORY OPTIMIZATION DESIGN FOR ROCKET-POWERED HYPERSONIC VEHICLE

  • 摘要: 为提升高超声速飞行器的射程和飞行性能,提出一种基于气动力与火箭发动机推力混合控制的轨迹优化设计方法。针对高超声速飞行器再入阶段的混合控制轨迹优化问题,提出求解多段不同特征轨迹的分段高斯伪谱法,将多段最优控制问题转化为非线性规划问题。采用SQP算法对其进行求解,获取以最大射程为性能指标的飞行器轨迹优化方法,并以此研究火箭发动机在有限燃料、适当启动条件下单次和多次启动对飞行轨迹的影响。数值仿真结果表明,分段高斯伪谱法可较快速求解出火箭动力助飞高超声速飞行器最优轨迹,发动机单次启动和多次启动方案能够在不同方面改善飞行器性能。

     

    Abstract: A method of trajectory optimization design based on hybrid control of aerodynamics force and rocket engine thrust is proposed, in order to improve the range and flight performance of hypersonic vehicle. For the trajectory optimization problem of the hybrid control during the gliding phase of the hypersonic vehicle, a piecewise Gauss pseudo-spectral method for solving multi-segment trajectories with different characteristics is presented, which transforms the multi-segment optimal control problem into a nonlinear programming problem. The vehicle trajectory optimization method with the maximum range as the performance index is obtained by solving the nonlinear programming problem with sequential quadratic programming (SQP) algorithm, and the influence of single and multiple ignition of rocket engine on flight trajectory is studied under limited fuel and appropriate ignition conditions. The numerical simulation results illustrate that the piecewise Gauss pseudo-spectral method can quickly solve the optimal trajectory of the rocket-powered hypersonic vehicle, and the rocket engine single ignition and multiple ignition schemes can also improve the performance of the vehicle in different aspects.

     

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