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针对离轨段轨道设计中飞行器需周期性满足离轨点要求的问题,提出了一种具有一定回归周期的回归轨道设计方法。与以往的给定星下点轨迹和回归周期来求解回归轨道的轨道高度和轨道倾角的设计方法不同的是,该回归轨道设计可以在不改变原有轨道倾角的情况下,在一定范围的轨道高度内寻找满足回归周期要求的回归轨道;并且能保证设计的回归轨道星下点轨迹经过离轨点星下点。通过分析半长轴在回归轨道设计中的影响,得到了求解回归周期和推算升交点赤经的方法。最后针对离轨实例进行MATLAB仿真,同时对比卫星仿真软件的仿真结果,验证了所提方法的有效性。
Aiming at the problem that the spacecraft needs to meet the requirements of derailment periodically in orbit design, a method of regression orbit design with a certain regression period is proposed. Different from the previous design method of solving the orbital height and orbit inclination of a given orbit and the regression period, the regression orbit design can be used in a certain range of orbit without changing the original orbit inclination, Looking for the return path to meet the requirements of the regression period; and can ensure that the design of the orbit point under the orbit of the return orbit passes the point under the orbit. By analyzing the influence of the semi-major axis in the design of orbit, we obtain the method of solving the regression period and calculating the ascension point. At last, MATLAB simulation is carried out for the derailment case, and the simulation results of satellite simulation software are compared to verify the effectiveness of the proposed method.