基于InSAR任务性能要求的编队轨道构型设计

Orbit Configuration Design and Perturbation Analysis Based on Formation Flying InSAR Satellites Mission and Performance Requirements

为使卫星在飞过特定经纬度地面上空时对应特定的空间基线形式,系统的其他参数常受制于诸多限制,只有编队构型可以进行更为自由的设计。以双星编队为例,研究了基于轨道摄动理论的编队飞行模型;分析了编队飞行InSAR卫星的轨道设计约束条件与设计目标;提出了四种轨道构型方案并对其测高性能进行比较;并分析了地球扁率摄动因素对编队构型及InSAR测高性能的影响。

Configuration design is of great importance to the formation flying InSAR satellites system. To achieve specific spatial baseline Earth surface, the formation configuration is form when the satellites are flying over the specific the only variable which can be designed freely, while other parameters are restricted by many limiting factors. The formation flying model based on orbit perturbation solution was studied. The orbit design constraint conditions and objective of formation flying InSAR satellites were analyzed. Four two-satellite formation proposals and comparisons of their elevation generation performances were presented. The influence of the earth flattening perturbation to the formation configuration and the InSAR measurement performance were also described.