液体大幅晃动充液航天器分数阶滑模姿态机动控制  

Fractional-order Sliding Mode Attitude Control for Liquid-filled Spacecraft with Large-amplitude Liquid Sloshing

作　　者：宋晓娟[1,2,3] 范志文 吕书锋 岳宝增 SONG Xiaojuan;FAN Zhiwen;LYU Shufeng;YUE Baozeng(College of Mechanical Engineering,Inner Mongolia University of Technology,Hohhot 010051,China;Inner Mongolia Key Laboratory of Special Service Intelligent Robotics,Hohhot 010051,China;College of science,Inner Mongolia University of Technology,Hohhot 010051,China;School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China)

机构地区：[1]内蒙古工业大学机械工程学院,呼和浩特010051 [2]内蒙古自治区特殊服役智能机器人重点实验室,呼和浩特010051 [3]内蒙古工业大学理学院,呼和浩特010051 [4]北京理工大学宇航学院,北京100081

出　　处：《宇航学报》2024年第7期1146-1154,共9页Journal of Astronautics

基　　金：国家自然科学基金项目(12362004,11962020,12172182,12132002);内蒙古自治区高等学校创新团队发展计划支持(NMGIRT2213);内蒙古自治区高等学校青年科技人才项目(NJYT23029,NJYT23067);内蒙古自治区直属高校基本科研业务费项目(JY20240066,JY20220086,JY20220046)。

摘　　要：研究部分充液航天器存在系统参数不确定、外部未知扰动、液体燃料大幅晃动的姿态机动控制问题。首先,将大幅晃动的液体燃料等效为运动脉动球模型,建立刚-液耦合航天器动力学方程;其次,针对充液航天器姿态稳定问题,提出一种具有固定时间收敛的分数阶非奇异快速终端滑模算法;同时,设计扰动观测器来估计系统的综合扰动,并且利用径向基函数神经网络来估计液体大幅晃动引起的扰动;设计Lyapunov函数分析并证明系统固定时间稳定性;最后,通过对比的仿真结果验证本文提出控制策略的可行性和有效性。The attitude maneuver control problem of liquid-filled spacecraft with system parameter uncertainty,external disturbance and large-amplitude liquid sloshing are studied.Firstly,the liquid fuel with large-amplitude liquid sloshing is equivalent to a moving pulsating ball model,and the dynamic equation of the spacecraft with large liquid sloshing is established.A fractional-order nonsingular fast terminal sliding mode algorithm with fixed time convergence is proposed for the attitude stability of liquid-filled spacecraft.Additionally,a perturbation observer is designed to estimate the combined perturbations including parameter uncertainties and external perturbations,and the perturbations caused by large-amplitude liquid sloshing are estimated using a radial basis function neural network.The Lyapunov function is designed to analyze and prove the fixed-time stability of the system.Finally,the feasibility and effectiveness of the control strategy proposed in this paper are verified by the comparative simulation results.

关 键 词：充液航天器 液体晃动 滑模控制 扰动观测器 神经网络 

分 类 号：V448[航空宇航科学与技术—飞行器设计]