摘要
小卫星在实际运行中受到多种摄动力的作用,这会对其轨道造成不同程度的影响,因此在小卫星的轨道设计与控制中,摄动是必须考虑的重要因素。本文以500km高的小卫星太阳同步轨道为研究对象,运用轨道摄动的基本理论,估计了地球非球形引力、大气阻力、太阳光压及第三体引力的量级并进行比较;建立小卫星轨道摄动分析模型,并在此模型的基础上,利用计算机仿真技术,对小卫星轨道摄动问题展开仿真研究,验证了几种主要摄动力的量级估计的结果,分析比较了几种主要摄动力对小卫星运行轨道的影响程度及规律,本文结果对小卫星轨道设计与控制具有很好的参考价值。
Micro satellite is under the influence of perturbative forces which would affect its orbit, so it is important to consider these perturbations in micro satellite orbit design and control. This paper studies on the sun-synchronous micro satellite with an altitude of 500km, uses basic orbit perturbation theory to estimate and compare the quantity of perturbation forces caused by the non-spherical gravitational potential, the atmospherics drag, the sunlight pressure and the third body gravitation ; and establishes orbit perturbation analysis model of micro satellite, then carries out research on micro satellite orbit perturbation based on this model. The result of perturbations estimate is verified through simulation, and the effect of different pertur- bations and their rules are also analyzed. At the end, this paper presents some references for small satellite orbit design and control.
出处
《航天控制》
CSCD
北大核心
2007年第3期66-70,共5页
Aerospace Control
基金
863基金(2006AA704312)资助
关键词
轨道摄动
小卫星
仿真
Orbit perturbation
Micro satellite
Simulation
