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分析了快速进入近地轨道特点及其星下点轨迹特性,并通过星下点轨迹特性反算快速进入近地轨道根参数。提出了J2摄动影响下快速进入近地轨道回归轨道设计方法。STK仿真验证了该设计方法的正确性。
The characteristics of fast-entering near-Earth orbit and the trajectory of the satellite under it are analyzed. The root parameters of the near-earth orbit The design method of fast orbit regression trajectory under the influence of J2 perturbation is proposed. STK simulation verifies the correctness of the design method.