机动发射条件下空间飞行器上升段弹道设计

为提高空间飞行器机动发射能力，在飞行中段轨迹确定情况下，以入轨点位置、高度、速度、速度方位角、弹道倾角等作为终端约束，设计上升段弹道，实现以基准发射点为中心，一定范围内任意发射点上升段与飞行中段高精度交班。考虑到上升段终端入轨点约束条件多、精度要求高，且上升段弹道具有非线性、强耦合的特点，研究设计了二级、三级能量管理模型和变射面横向机动模型，并采用加入混合扰动算子的梯度粒子群算法对上升段弹道进行求解。仿真结果表明:优化设计的变射面横向机动弹道能够实现与飞行中段的高精度交班，上升段终端入轨点位置、高度、速度、速度方位角和弹道倾角平均偏差分别为27.506 2 m、2.125 4 m、1.652 2 m/s、0.072 8°和0.029 0°。 

Design of ascent trajectory of space vehicle in mobile launch condition

In order to improve the mobile launch capability of space vehicle, the position, height, velocity magnitude, velocity azimuth and trajectory inclination of the injection point were used as terminal constraints to design the ascent trajectory under the condition that the mid-flight trajectory was determined. The space vehicle could be launched at any position in a certain range centered on the original launch point, and the high-precision shift with the mid-flight trajectory was completed. Considering many constraints and high-precision requirements of the injection point, and the nonlinear and strong coupling characteristics of the ascent trajectory, the two-stage and three-stage energy management model and the changeable-launching-plane transverse maneuvering model were designed, and then the gradient particle swarm algorithm with the blended disturbance operator was used to solve the ascent trajectory. The simulation results show that the high-precision shift with the mid-flight trajectory can be realized smoothly by optimized transverse maneuvering trajectory, and the average deviation of the position, height, velocity, velocity azimuth and trajectory inclination of the terminal injection point for ascent trajectory are 27.506 2 m, 2.125 4 m, 1.652 2 m/s, 0.072 8° and 0.029 0° respectively.