超低干扰力矩微纳卫星姿控半物理仿真平台  

Hardware-in-loop simulation platform with super-low disturbance torque for attitude control system of micro-and nano-satellites

作　　者：刘延芳[1] 刘兴富[2] 齐乃明[1] 

机构地区：[1]哈尔滨工业大学航天学院飞行器机电一体化中心,黑龙江哈尔滨150001 [2]上海微小卫星工程中心,上海201210

出　　处：《系统工程与电子技术》2017年第8期1808-1814,共7页Systems Engineering and Electronics

基　　金：中央高校基本科研业务费专项基金(HIT.NSRIF.201622);黑龙江省博士后特别资助(LBH-TZ1609);微小型航天器技术国防重点学科实验室开放基金(HIT.KLOF.MST.201507);钱学森实验室种子基金资助课题

摘　　要：微纳卫星姿控的反作用飞轮输出力矩小,难以克服普通气浮转台的干扰力矩,为了解决上述问题,实现微纳卫星姿控地面半物理仿真验证,必须对干扰力矩进行有效补偿。为此,对干扰力矩分类并分析了各自的特性,针对性提出了干扰力矩主动补偿方法,研制了主动补偿式超低干扰力矩气浮转台,并基于此开发了微纳卫星姿控半物理仿真平台。研制的气浮转台的干扰力矩达到2×10-5 Nm,小于微纳卫星反作用飞轮的最小输出力矩,利用半物理仿真平台有效地验证了微纳卫星大角度姿态机动控制算法。The output moment of the reaction wheels utilized in the attitude control system of the micro-and nano-satellites is too small to overcome the disturbance torque of the air bearing table. To solve this problem and experimentally verify the attitude control system , the disturbance torque is required to be compensated for. Thus, the disturbance torque is classified and analyzed and the compensation methods are proposed accordingly. An air bearing table with supper-low disturbance torque is constructed,based on which the hardware-in-loop simulation system for attitude control system of micro-and nano-satellites is developed. Experimental results demonstrate that the disturbance torque is 2×10^-5 Nm, and it is smaller than the minimum output of the reac-tion wheels. The verification of the large-angle attitude maneuver control algorithm of the micro-and nano-satel-lites is completed by the simulation platform effectively.

关 键 词：半物理仿真 微纳卫星模拟器 干扰力矩 气浮转台 

分 类 号：V461[航空宇航科学与技术—航空宇航制造工程]