国家自然科学基金资助项目(61374116)和航空科学基金资助项目(2011ZA52009)
考虑一类带液体燃料的航天器,由于航天器控制自身姿态的同时,还需要抑制液体燃料的晃动,使得系统整体表现为一个欠驱动系统.针对给出的物理模型,将其转化为一定形式的标准型,并对模型的特性进行了分析验证,最后采用一种适用于一类欠驱动系统的滑模控制方法来进行控制器的设计.由系统的稳定性分析可以看出,设计的控制器可以使系统的一些状态量达到平衡点,而剩下的状态量在系统自身特性的作用下,也能够达到平衡点,进而使整个航天器系统渐近稳定.仿真结果证明了控制器的有效性和可行性.
A class of spacecrafts with fuel slosh would behave like a kind of underactuated system for they have to suppress the sloshing modes while controlling the spacecraft attitude. A sliding mode control approach wasproposed to stabilize the spacecraft which is transformed into certain normalized form. The designed controller can stabilize some states of the system, while other states can achieve the equilibriumdue to the system’s own characteristic. Finally, simulation results were presented to demonstrate the effectiveness and feasibility of the proposed controller.
顾黄兴,齐瑞云.基于滑模控制的充液航天器燃料晃动抑制研究[J].动力学与控制学报,2015,13(2):138~143; Gu Huangxing, Qi Ruiyun. Attitude control of spacecraft with fuel slosh based on sliding mode control[J]. Journal of Dynamics and Control,2015,13(2):138-143.
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