The invention discloses a space orbit finite thrust optimal orbital transfer method based on a bilinear tangent law. Comprising the steps of defining a thrust direction; establishing a kinetic equation containing thrust under a two-body orbit; carrying out integral solution by utilizing a kinetic equation containing thrust and a thrust direction under a two-body orbit to obtain a virtual terminal state position and speed; according to the terminal state constraint, obtaining the flight time before a given distance pulse application point and the flight time after the fixed distance pulse application point; determining an engine starting point corresponding to the pulse orbital transfer time and an engine shutdown point corresponding to the pulse orbital transfer time; and determining a motion trail corresponding to orbital transfer and a corresponding position and speed at each moment. According to the method, the optimal orbital transfer strategy corresponding to the spacecraft on-orbit maneuver and orbital transfer based on pulse orbital transfer and meeting the optimal control viewpoint can be calculated.
一种双线性正切律的空间轨道有限推力最优变轨方法。包括:定义推力方向;建立二体轨道下含推力的动力学方程;利用二体轨道下含推力的动力学方程和推力方向进行积分求解,获得虚拟的终端状态位置、速度;根据终端状态约束,获得给定距离脉冲施加点前的飞行时间和定距离脉冲施加点后的飞行时间;确定脉冲变轨时刻对应的发动机开机点和脉冲变轨时刻对应的发动机关机点;确定变轨对应的运动轨迹以及每时每刻对应的位置和速度。本发明可以计算出航天器在轨机动和变轨时基于脉冲变轨对应的符合最优控制观点下的最优变轨策略。
Limited thrust optimal orbital transfer method for space orbit based on bilinear tangent law
一种双线性正切律的空间轨道有限推力最优变轨方法
2024-01-23
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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