超低轨道卫星摄动特性分析及轨道维持方法

摘要

针对超低轨道卫星长时间在轨飞行的轨道维持问题，分析了超低轨道平均偏心率矢量变化特性，提出了一种超低轨道维持的控制方法。分析了 J2、J3摄动以及大气阻力摄动作用下超低轨道卫星偏心率矢量的变化特性；基于能量守恒原理设计了超低轨道高度维持的控制策略；通过仿真算例验证了控制策略的有效性。结果表明：在地球非球形引力摄动、大气阻力摄动和速度脉冲作用下超低轨道平均偏心率的变化是稳定的，所设计的轨道维持方法不仅能够实现超低轨道高度维持，确保平均偏心率矢量收敛至平衡位置，且用于轨道维持的燃料消耗合理，能够满足长时间的超低轨道飞行要求。%Aiming at the orbital maintenance problem of super low altitude satellite for the long duration of the flight,the variation characteristics of the average eccentricity vector were analyzed and an orbital maintenance method was presented.Firstly,the change of average eccentricity vector characteristic of super low altitude satellite under the J2 ,J3 zonal terms and the atmospheric drag was analyzed.Then an orbital maintenance strategy based on energy conservation principle was proposed.Finally,the effectiveness of orbital maintenance strategy was validated by simulation examples.Simulation results show that the changes of average eccentricity is stable under the perturbation of the earth non-spherical gravity,the atmospheric drag and the impulsive maneuver,and the proposed orbital maintenance method can effectively achieve super low altitude maintenance and make the average eccentricity vector converge to equilibrium point.Besides,the fuel consumption for orbital maintenance is reasonable and the long duration flight in super low orbit can be achieved.