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针对重复使用运载器原场返回这一发展思路存在的诸多问题,提出一种在发动机二次点火方案下结合逆向积分的原场返回轨迹设计方法。该方法将原场返回分为轨迹回转段与再入返回段两部分进行设计。前者通过姿态调整、速度调整实现飞行方向朝向发射场;后者通过逆向积分设计再入返回轨迹,并进一步确定轨迹回转段的终端需求。仿真结果表明,该设计方法能够在满足约束条件下获得原场返回的完整飞行轨迹。
Aiming at many problems existing in the field of reusable carrier field return, this paper presents a design method of the original field return trajectory combined with reverse integral under the engine secondary ignition scheme. This method divides the original field return into the trajectory revolving segment and the reentry return segment. The former through the attitude adjustment, speed adjustment to achieve the direction of flight toward the launch site; the latter by reverse integration design reentry trajectory, and further determine the trajectory of the terminal segment needs. The simulation results show that this design method can obtain the complete flight path of the original field under the constraint conditions.