The invention discloses a multi-satellite leveraging burnup optimal orbit optimization method in a planetary system, and belongs to the technical field of aerospace. The implementation method comprises the following steps: selecting a leveraging satellite sequence meeting detection requirements, taking each transfer orbit period as a variable, adding maneuver only when the satellite leaves an initial orbit and is captured by a target satellite or enters a target orbit, and constructing an orbit optimization problem under a planet centroid inertial system according to an optimization target that the total speed increment is minimum. According to the parameters of the transfer orbit of the spacecraft between the leveraging satellites, the state of the next satellite leveraging is solved, the state can be matched with the parameters of the transfer orbit after leveraging, and then continuous solving is achieved till the state of the spacecraft arriving at the target satellite is obtained. And solving the optimization problem by adopting a global optimization algorithm to obtain the relative speed of arriving at each leveraging satellite and transfer orbit parameters before and after leveraging, and realizing transfer of each section of transfer orbit under the ephemeris according to the transfer orbit parameters.
本发明公开的一种行星系统内多卫星借力燃耗最优轨道优化方法,属于航空航天技术领域。本发明实现方法为:选择满足探测需求的借力卫星序列,以各转移轨道周期为变量,只在离开初始轨道以及被目标卫星捕获或进入目标轨道时添加机动,优化目标为总速度增量最小,在行星质心惯性系下构建轨道优化问题。根据航天器在借力卫星间转移轨道的参数求解下一次卫星借力时的状态,由该状态能够匹配借力后转移轨道的参数进而实现连续求解,直到得到到达目标卫星时的状态。采用全局优化算法对该优化问题进行求解,得到抵达各借力卫星的相对速度以及借力前后的转移轨道参数,根据转移轨道参数实现参考在星历下各段转移轨道转移。
Multi-satellite leveraging burnup optimal orbit optimization method in planetary system
一种行星系统内多卫星借力燃耗最优轨道优化方法
2024-11-15
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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