GEO卫星在轨横向质心快速估算方法  

Method of In-orbit Lateral Centroid Fast Estimation of GEO Satellite

作　　者：刘伟[1] 俞洁[2] 杨立峰[1] 洪振强[1] 

机构地区：[1]上海卫星工程研究所,上海200240 [2]上海航天技术研究院,上海201109

出　　处：《航天器工程》2016年第5期39-44,共6页Spacecraft Engineering

基　　金：基金项目:国家重大航天工程

摘　　要：针对地球静止轨道(GEO)卫星转移轨道段推进剂消耗量大,卫星横向质心偏移,导致变轨过程中发动机产生较大干扰力矩等情况,提出在轨使用推力器进行卫星横向质心估算的方法。为保证卫星姿态稳定控制,采用推力方向相同、力矩方向相反的成组推力器同时喷气激励,再用陀螺进行角速度测量,避免因力矩过大、控制系统暂停闭环控制时卫星产生较大的角速度。利用实例对横向质心估算方法进行仿真验证,结果表明:估算方法仅需10s的连续喷气激励,避免了卫星姿态的波动,估算误差可控,可用于GEO卫星转移轨道段的质心估算。For GEO satellites, the propellant consuming in large quantities during geostationary transfer orbit results in satellite lateral centroid deviation and consequently causes relatively large perturbed moment. In this background, a method to estimate the lateral centroid of a satellite based on thrusters firing is proposed. This centroid estimation method uses thrusters in the same direction but in the opposite direction of torque to jet simultaneously to avoid the torque to be too large, and uses a gyro to measure the angular velocity. By these considerations, this method can ensure the stability of satellite attitude when the closed-loop control is turned off during measu- ring. Simulation results with a validation example show that this method is effective with only 10 seconds continuous thrust, and the turbulance of satellite attitude and estimated error are control- lable so that it is feasible and available to GEO satellite centroid estimation during geostationary transfer orbit.

关 键 词：地球静止轨道卫星 在轨横向质心估算 推力器 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]