基于预置动压的高超声速飞行器上升段轨迹设计

Ascent trajectory design of hypersonic vehicle based on preset dynamic pressure

针对高超声速飞行器燃料最省上升轨迹的研究问题,为实现高超声速飞行器的燃料最省上升轨迹快速求解,对定动压情况下高超声速飞行器上升段轨迹特性进行了研究分析,给出了定动压情况下高超声速飞行器燃料最省上升轨迹的快速反解方法,总结分析了不同定动压下的上升轨迹特性,并在此研究的基础上提出了基于预置动压的高超声速飞行器上升段轨迹设计方法。该方法可以通过设计燃料最省的动压曲线,反解出该预置动压下的上升轨迹参数,得到一条近似燃料最省最优解的轨迹。仿真结果表明,经过解算得到的上升轨迹结果与高斯伪谱法得到的最优上升轨迹结果基本相似。

According to the problem of minimum fuel ascent trajectory of hypersonic vehicle （ HSV ）, in order to obtain the optimal trajectory quickly, a rapid inverse method for generating a HSV minimum-fuel ascent trajectory was proposed firstly, and the characteristics of the trajectory under different fixed ic pressure was analyzed. Then, the trajectory dynam design method based on the preset dynamic pressure was proposed. By designing the dynamic pressure curve, it is easy to obtain the trajectory parameters. Simu- lation results demonstrate that the results drawn from the proposed method is almost similar to the results obtained from the Gauss pseudo-spectral method （GPM）.