高精度航天器太阳能电池阵减扰驱动方法  

Disturbance-mitigation drive methods for solar array of a high-precision spacecraft

作　　者：朱仕尧 雷勇军[1] 谢燕[1] 李家文[1] 

机构地区：[1]国防科学技术大学航天科学与工程学院,长沙410073

出　　处：《振动与冲击》2014年第21期26-30,37,共6页Journal of Vibration and Shock

基　　金：国家自然科学基金面上项目(11272348);国家自然科学基金青年基金项目(11202233)

摘　　要：为减小太阳能电池阵对日跟踪驱动过程所产生的扰动,基于电池阵及其驱动装置机电一体化模型分析了激起电池阵驱动扰动的主要因素,并从稳态力矩平衡方程出发提出了适用于电池阵闭环和开环输入补偿的减扰驱动控制方法。结果表明:步进电机谐波电磁力矩可近似为电池阵转动规律的比例控制环节,其齿槽效应是激起电池阵驱动过程扰动的主要因素之一;两种减扰驱动策略都能有效改善跟踪驱动过程中的速度和力矩稳定度,且不会降低电池阵对日跟踪指向精度,但其减扰效果会随齿槽力矩峰值误差增大而逐渐降低;综合考虑多种因素条件下开环减扰驱动方法较优,在±11%参数误差范围内该驱动方法可以将转速稳定度控制在1%以下,且力矩稳定度优于1.15%。With the aim to investigate and mitigate the disturbance induced by sun-track drive of solar array,the main factor inducing this disturbance was analyzed based on a mechatronic model of a solar array with drive assembly. Starting with steady-state moment equilibrium equation,disturbance-mitigation drive control methods for close-loop compensation and open-loop one by updating input signal to compensate speed fluctuation of the drive assembly were presented.The results indicate that the harmonic electromagnetic torque can be approximately taken as the proportional control link for rotation angle,and its cogging effect is one of important factors causing the disturbance in the drive process;two disturbance-mitigation drive strategies are clearly capable of improving the speed stability and the disturbing torque stability without degrading the sun-pointing accuracy of the solar array,but the disturbance-mitigation effectiveness gradually degrades with increase in the error of the cogging torque amplitude;taking various factors combined into consideration,the disturbance-mitigation open-loop drive control is preferable,it can achieve the speed stability and the disturbing torque stability less than 1% and 1.15%,respectively,while the error of cogging torque amplitude is below the upper limit of 11%.

关 键 词：太阳能电池阵 跟踪驱动 齿槽效应 减扰驱动 输入补偿 

分 类 号：V414.1[航空宇航科学与技术—航空宇航推进理论与工程] TM383.6[电气工程—电机]