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限制性三体问题下共线平动点附近的拟周期轨道在深空探测中具有重要的实际应用价值,得到了各航天大国的广泛重视。通过将动力学中心流形结构引入轨道控制方法的设计之中,得到了基于投影到中心流形的共线平动点拟周期轨道稳定保持策略。首先推导了会合坐标到中心流形坐标的正则变换方法,在此基础上设法通过引入轨道机动,将偏差状态点投影到中心流形上,从而达到消除不稳定分量的目的。该方法充分整合了平动点的动力学特性,并且也适用于周期轨道的稳定保持。通过对Lissajous轨道和晕轨道的数值仿真表明,该方法较以往方法具有更强的稳定性,能在显著降低轨控燃料消耗的基础上达到较好的稳定保持效果。
Quasi-periodic orbits near collinear translational points under restricted three-body problem have important practical application value in deep space exploration and have gained widespread attention of various spacefaring nations. By introducing the dynamic center manifold structure into the design of orbit control method, the quasi-periodic orbitally stable holding strategy of collinear translational points based on the projection to the central manifold is obtained. Firstly, the regular transformation of the coordinates from the meeting point to the central manifold is deduced. Based on this, we try to project the deviation state point onto the central manifold by introducing orbit maneuver, so as to eliminate the unstable component. The method fully integrates the dynamic characteristics of translational points and also applies to the stable holding of periodic orbits. The numerical simulation of Lissajous orbit and halo orbit shows that this method is more stable than the previous method, and can achieve a good steady retention based on the significant reduction of orbit control fuel consumption.