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研究了针对航天器解体事件所生成的空间碎片的寿命计算方法.给出了基于NASA标准航天器解体模型的航天器解体算法.该算法生成的一系列碎片参数,将作为寿命计算的初始条件.总结了现有求解碎片寿命的算法,并提出了一种半分析算法.该算法运用平均根数法的思路,计算了在J2摄动项的影响下,碎片的半长轴和偏心率的变化率;并采用微分积分法预报半长轴和偏心率随时间的变化.为了适应时变大气模型,该算法限制了计算步长.通过与数值法的比较分析了算法的计算速度和精度.选用了3种大气模型:SA76、GOST和MSIS-00,分析了不同大气模型在计算碎片寿命之间的差异.通过与P-78卫星解体事件的实测数据对比验证了整个算法的正确性.
The method for calculating the life of space debris generated by spacecraft disintegration events is studied.The spacecraft disintegration algorithm based on the NASA standard spacecraft disintegration model is given.The series of debris parameters generated by this algorithm will be used as the initial conditions for life calculation. The existing algorithms for solving the problem of debris life are summarized and a semi-analytical algorithm is proposed.The algorithm uses the idea of average root number method to calculate the change of the semi-major axis and eccentricity of debris under the influence of J2 perturbation term And the differential integral method is used to predict the variation of the semi-major axis and eccentricity over time. In order to adapt to the time-varying atmospheric model, the algorithm limits the calculation step. The speed and accuracy of the algorithm are analyzed by comparison with the numerical method. Three atmospheric models, SA76, GOST and MSIS-00, were used to analyze the differences in the calculated lifetimes of different atmospheric models, and the correctness of the whole algorithm was verified by comparison with the measured data of the P-78 satellite disintegration event.