非太阳同步重访干涉轨道设计与摄动影响分析  

Non-Sun-Synchronous InSAR Repeat-Groundtrack Orbit Design and Perturbation Analysis

作　　者：陈奇 寇义民 任维佳 杨峰 熊淑杰 CHEN Qi;KOU Yi-min;REN Wei-jia;YANG Feng;XIONG Shu-jie(Changsha Tianyi Space Science and Technology Research Institute Co.,Ltd.,Changsha 410221,China)

机构地区：[1]长沙天仪空间科技研究院有限公司,湖南长沙410221

出　　处：《测控技术》2023年第3期143-148,共6页Measurement & Control Technology

摘　　要：为了满足合成孔径雷达(SAR)卫星大型星座任意轨道面都可保持长期重访干涉的需求,提出了一种通用的非太阳同步重访干涉参考轨道设计方法,将重访周期作为修正变量之一,采用迭代修正方法得到了高精度动力学模型下的任意轨道倾角的参考轨道。仿真分析给出了一定轨道高度范围内所有候选的参考轨道,并指出了不同轨道倾角、相同重访圈数的参考轨道高度的明显变化,为实际任务的轨道筛选提供了参考。此外,针对日、月引力摄动对轨道倾角的影响进行了详细分析,指出了中低轨道倾角的非太阳同步轨道所需轨道保持控制的代价非常小,完全可以保持长期重访干涉。In order to meet the requirement of maintaining long-term interferometric synthetic aperture rader(InSAR) on any orbital plane of a large constellation of synthetic aperture rader(SAR) satellites,a general method for designing a non-sun-synchronous InSAR repeat-groundtrack orbit is proposed.The revisit period is chosen as one of the variables,and an iterative correction method is adopted to determining the reference orbits for arbitrary orbital inclinations under the high-precision dynamic model.The simulation analysis gives all the candidate reference orbits within a certain orbit height range,and points out the obvious changes of the orbit heights with different orbit inclinations and the same number of revisit revolutions,which provides a reference for the orbit selection of practical missions.In addition,the influence of lunisolar gravitational perturbation on orbit inclination is analyzed in detail,and it is pointed out that very little orbital control cost is required for maintaining a non-sun-synchronous orbit with medium or low orbital inclination,and long-term InSAR can be maintained completely.

关 键 词：非太阳同步轨道 SAR卫星 重访干涉 摄动分析 

分 类 号：V448[航空宇航科学与技术—飞行器设计]