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月地转移轨道设计一般分为初步轨道设计和精确轨道设计.其中,初步轨道设计的准确性是确保后续精确轨道设计收敛的关键.提出了一种基于Lambert算法的月地转移轨道快速设计方法.以出月球影响球的时刻、位置和速度为中间变量,将轨道分为地心段和月心段分别进行计算.将探测器飞出月球影响球至指定再入点的地心段轨道简化为一个Lambert问题进行求解,提出了通过牛顿迭代法求解月地转移轨道Lambert问题的方法,避免了Lambert问题求解时大量的超几何函数和级数计算,提高了计算效率.在月心段轨道的快速计算中,提出了根据探测器出影响球速度矢量、月球停泊轨道倾角和近月点高度计算月心双曲线轨道根数的新方法.通过迭代计算,使得两段轨道在月球影响球处的位置和速度连续,从而获得一条完整的满足两端约束的双二体月地转移轨道.该方法计算速度快,精度相对较高.计算结果可以作为后续精确轨道设计的初值.
The design of lunar orbit transfer orbit is generally divided into preliminary orbit design and precise orbit design, in which the accuracy of initial orbit design is the key to ensure the follow-up of precise orbit design convergence.A fast Lambertian algorithm based lunar transfer orbit design method is proposed. Taking the time, position and velocity of the lunar sphere as the intermediate variable, the orbit is divided into the geocentric segment and the lunar segment, respectively, and the trajectory of the lunar sphere to the specified reentry point is simplified to A Lambert problem is solved and a Newton iterative method is proposed to solve the Lambert problem of lunar transfer orbit. A large number of hypergeometric functions and series computations are avoided and the computational efficiency is improved. In the calculation, a new method of calculating the number of lunar hyperbolic orbitals based on the velocities of the velocities of the detectors, the inclination of the mooring orbit and the height of the lunar moons is proposed. By iterative calculation, the position of two orbits in the lunar sphere And the velocity is continuous, so as to obtain a complete double doubly momentary transfer orbit which satisfies both ends constraints. The method is fast and precise Relatively high calculated results as the initial value can be accurately follow the track design.