论文部分内容阅读
本文求得了空间飞行器在地球扁率摄动作用下简单形式的一阶解。首先引入了一组由轨道根数与坐标组成的新的正则变量,求出了中间轨道,建立起中间轨道的正则摄动方程,进而求出了一阶解。作为应用举例,将Lambert定理推广到包含扁率一阶摄动的情形。最后就弹道飞行器轨道,将本文结果与数值积分和二体轨道计算结果进行了比较,表明本文结果有较高精度。 本文结果无轨道倾角限制,包含了全部一阶摄动作用。可直接用于制导,实时轨道计算,卫星轨道短期预报等。
In this paper, we obtain the simple form first order solution of the spacecraft under the action of the oblate earth obliquity. Firstly, we introduce a new set of regular variables consisting of the number of orbits and coordinates of the track, find the middle orbit, establish the normal perturbation equation of the middle orbit, and then find the first order solution. As an example of application, the Lambert theorem is generalized to include the first-order perturbation of flattening. Finally, trajectory of the ballistic vehicle is compared with the result of numerical integration and two-body orbit calculation, which shows that the result of this paper has higher accuracy. The results of this paper have no orbital obliquity and contain all first-order perturbations. Can be used directly for guidance, real-time orbit calculations, short-term satellite orbit forecast.