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提出一种基于正弦指数函数的小推力借力飞行转移轨道初始设计方法。建立极坐标形式的正弦指数函数表达式,用于模拟小推力转移轨道,并用绕圈参数和飞行路径角对转移轨道的参数进行表征;在约束条件下对转移轨道参数进行离散化处理,求解转移轨道与目标星投射轨道在参考面内的交点,计算到达目标轨道时刻的极角,进而得出小推力转移轨道的初始设计参数;设计了地球—木星的火星借力小推力转移轨道,仿真结果验证了该方法在小推力转移轨道初始设计中的快速性与准确性。
A new initial design method of small thrust force transfer trajectory based on sinusoidal exponential function is proposed. The expression of the sine exponential function in the form of polar coordinates is established to simulate the small thrust transfer orbit and the parameters of the transfer orbit are characterized by the parameters of the winding and the flight path angle. The transfer orbit parameters are discretized under the constraints to solve the transfer Trajectory and the trajectory of the target star in the reference plane at the intersection of the reference point to calculate the polar moment of the target orbit, and then get the initial design parameters of small thrust transfer orbit; designed Earth Mars - Jupiter lean thrust transfer orbit, the simulation results The fastness and accuracy of this method in the initial design of small thrust transfer trajectory are verified.