Jeyakodi David Jim Fletcher, Sharma Ram Krishan
Department of Aerospace Engineering, Karunya University, Karunya Nagar, Coimbatore 641114, India.
Int Sch Res Notices. 2014 Oct 29;2014:864953. doi: 10.1155/2014/864953. eCollection 2014.
The combination of atmospheric drag and lunar and solar perturbations in addition to Earth's oblateness influences the orbital lifetime of an upper stage in geostationary transfer orbit (GTO). These high eccentric orbits undergo fluctuations in both perturbations and velocity and are very sensitive to the initial conditions. The main objective of this paper is to predict the reentry time of the upper stage of the Indian geosynchronous satellite launch vehicle, GSLV-D5, which inserted the satellite GSAT-14 into a GTO on January 05, 2014, with mean perigee and apogee altitudes of 170 km and 35975 km. Four intervals of near linear variation of the mean apogee altitude observed were used in predicting the orbital lifetime. For these four intervals, optimal values of the initial osculating eccentricity and ballistic coefficient for matching the mean apogee altitudes were estimated with the response surface methodology using a genetic algorithm. It was found that the orbital lifetime from these four time spans was between 144 and 148 days.
除了地球扁率外，大气阻力以及月球和太阳的摄动共同作用，会影响地球同步转移轨道（GTO）上上面级的轨道寿命。这些高偏心率轨道的摄动和速度都会发生波动，并且对初始条件非常敏感。本文的主要目的是预测印度地球同步卫星运载火箭GSLV-D5上面级的再入时间，该火箭于2014年1月5日将卫星GSAT-14送入GTO，其近地点和远地点的平均高度分别为170千米和35975千米。在预测轨道寿命时，使用了观测到的平均远地点高度近线性变化的四个区间。对于这四个区间，使用遗传算法通过响应面方法估算了用于匹配平均远地点高度的初始密切轨道偏心率和弹道系数的最佳值。结果发现，这四个时间段的轨道寿命在144天至148天之间。
