CAJ | 학술논문

空间站通常运行在力矩平衡姿态下。空间站上搭载大型天文观测有效载荷时，载荷运动会产生干扰力矩，对空间站平衡姿态会产生影响。针对搭载在空间站平台上的大型观测类有效载荷工作特点，建立了其运动补偿规律和扰动模型，将扰动引入空间站的平衡姿态动力学过程中，并进行了计算机仿真和分析。仿真结果表明，在设计的二次调节器和前馈控制器的作用下，转动有效载荷运动引起的姿态角、姿态角速率变化等控制在一定的范围内，且有效载荷的跟踪观测效果较稳定。
공간참통상운행재력구평형자태하。공간참상탑재대형천문관측유효재하시，재하운동회산생간우력구，대공간참평형자태회산생영향。침대탑재재공간참평태상적대형관측류유효재하공작특점，건립료기운동보상규률화우동모형，장우동인입공간참적평형자태동역학과정중，병진행료계산궤방진화분석。방진결과표명，재설계적이차조절기화전궤공제기적작용하，전동유효재하운동인기적자태각、자태각속솔변화등공제재일정적범위내，차유효재하적근종관측효과교은정。
Space station is usually operated in Torque Equilibrium Attitude ( TEA) mode. When large payloads for astronomical observa-tion mounted on a space station,their movements will lead to disturbed torque,thus influencing the attitude of a space station. The motion compensation laws and corresponding disturbance mathematical models were established according to the moving rule of large payload feature. The disturbance was brought in the system of equilibrium attitude dynamics,then an analysis on impacts of the platform with large payloads for astronomical observation was conducted in the paper. The result shows that after a Linear Quadratic Regulator ( LQR) and feed forward controller were designed,the change of the attitude angle was restrained in a acceptable range,as well as the payload tracking effects are stable.