基于落压式动力装置的挠性航天器姿态控制技术研究  

Research on attitude control technology of flexible spacecraft based on drop pressure power plant

作　　者：胡诗桥 陈宁[1] 刘国生 戴曜泽 时中 Hu Shiqiao;Chen Ning;Liu Guosheng;Dai Yaoze;Shi Zhong(No.8511 Research Institute of CASIC,Nanjing 210007,Jiangsu,China)

机构地区：[1]中国航天科工集团8511研究所,江苏南京210007

出　　处：《航天电子对抗》2024年第1期1-5,17,共6页Aerospace Electronic Warfare

摘　　要：针对充气可展开结构的挠性航天器的姿态控制问题,以线性自抗扰控制理论为基础,开展挠性航天器姿态控制技术研究,通过对落压式动力装置中气体压强变化的实时拟合,提出了一种落压式自抗扰姿态控制算法。仿真结果表明落压式自抗扰姿态控制算法相对于传统恒压式在姿态控制精度不变的条件下,减少了约10%的工质消耗,增加了11%姿态保持时间,进一步实现挠性航天器的小型化、轻量化。Based on linear active disturbance rejection control theory,research on flexible spacecraft attitude control technology is carried out to solve the attitude control problem of flexible spacecraft with inflatable deployable structures.By real-time fitting of pressure changes in a drop pressure power plant,a pressure drop disturbance rejection attitude control algorithm is proposed.The simulation results show that compared to traditional constant pressure attitude control algorithm,the drop pressure attitude control algorithm reduces the consumption of working fluid by about 10%and increases the attitude holding time by 11%,and the miniaturization and lightweighting of flexible spacecraft are further realized.

关 键 词：挠性航天器 落压式动力装置 姿态控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]