Attitude Switching Control of Spacecraft Based on Hamilton System
详细信息 查看官网全文
- 英文论文题名：Attitude Switching Control of Spacecraft Based on Hamilton System
- 论文作者：Shen Zhang ; Qing Wang ; Chaoyang Dong ; Yanze Hou
- 英文论文作者：Shen Zhang ; Qing Wang ; Chaoyang Dong ; Yanze Hou ; School of Automation Science and Electrical Engineering ; Beijing University of Aeronautics and Astronautics ; School of Aeronautic Science and Engineering ; Beijing University of Aeronautics and Astronautics ; Institute of Manned Space System Engineering ; China Academy of Space Technology
- 年：2017
- 作者机构：School of Automation Science and Electrical Engineering,Beijing University of Aeronautics and Astronautics;School of Aeronautic Science and Engineering,Beijing University of Aeronautics and Astronautics;Institute of Manned Space System Engineering,China Academy of Space Technology;
- 英文论文关键词：attitude control ; Hamilton system ; passivity ; switched control ; dynamic inversion
- 会议召开时间：2017-07-26
- 会议录名称：第36届中国控制会议论文集（A）
- 英文会议录名称：Proceedings of the 36th Chinese Control Conference（A）
- 语种：英文
- 分类号：V448.2
- 学会代码：KZLL
- 会议名称：第36届中国控制会议
- 会议地点：中国辽宁大连
- 主办单位：中国自动化学会控制理论专业委员会
- 学会名称：中国自动化学会控制理论专业委员会
- 页数：7
- 文件大小：194k
- 原文格式：D
- 会议级别：全国
摘要
In modern space missions, such as space rendezvous and docking, actuator switching, booster stage separation for carrier rockets, the instantaneous mass or structure variations are exist. A Hamilton system based spacecraft attitude switching control scheme is proposed. The passivity control law is designed based on the Hamilton system model of spacecraft. A dynamic inversion method is used to compensate the nonlinear dynamic and establish the linear switched system approach. Asymptotic stability condition with instantaneous mass or structure variation existence is given. The energy based control law ensures the robustness and anti-disturbance ability of each switched subsystem. On the other hand, the proposed scheme can guarantee the stability with the presence of the instantaneous mass or structure changes. The results of numerical simulation validate the proposed scheme has strong robustness and can achieve accurate command tracking.
In modern space missions, such as space rendezvous and docking, actuator switching, booster stage separation for carrier rockets, the instantaneous mass or structure variations are exist. A Hamilton system based spacecraft attitude switching control scheme is proposed. The passivity control law is designed based on the Hamilton system model of spacecraft. A dynamic inversion method is used to compensate the nonlinear dynamic and establish the linear switched system approach. Asymptotic stability condition with instantaneous mass or structure variation existence is given. The energy based control law ensures the robustness and anti-disturbance ability of each switched subsystem. On the other hand, the proposed scheme can guarantee the stability with the presence of the instantaneous mass or structure changes. The results of numerical simulation validate the proposed scheme has strong robustness and can achieve accurate command tracking.
In modern space missions, such as space rendezvous and docking, actuator switching, booster stage separation for carrier rockets, the instantaneous mass or structure variations are exist. A Hamilton system based spacecraft attitude switching control scheme is proposed. The passivity control law is designed based on the Hamilton system model of spacecraft. A dynamic inversion method is used to compensate the nonlinear dynamic and establish the linear switched system approach. Asymptotic stability condition with instantaneous mass or structure variation existence is given. The energy based control law ensures the robustness and anti-disturbance ability of each switched subsystem. On the other hand, the proposed scheme can guarantee the stability with the presence of the instantaneous mass or structure changes. The results of numerical simulation validate the proposed scheme has strong robustness and can achieve accurate command tracking.
引文
[1]Y.C.Liu,Y.Z.Wang.New development of energy-based control on generalized controlled Hamiltonian systems,Journal of Shandong University(Engineering Science),39(3):47-55,2009.(in Chinese)
[2]J.J.E.Slotine,M.D.Benedetto,Hamilton adaptive control of spacecraft,IEEE Transaction on Automatic Control,35(7):848-852,1990.
[3]H.Yoon,B.H.Agrawal.Adaptive control of uncertain Hamilton multi-input multi-output systems:With application to spacecraft control,IEEE Transactions on Control Systems Technology,17(4):900-906,2009.
[4]X.P.Shi,G.P.Yuan,Robust adaptive control of Hamilton system and its application in spacecraft,Journal of Sichuan university(Engineering Science Edition),45(5):130-144,2013.(in Chinese)
[5]Y.D.Zhang,Q.F.Chen,J.H.Dai,Study on Hamiltonian dynamic model and solving method of distributed satellite system relative motion,Journal of National University of Defense Technology,32(2):12-16,2010.(in Chinese)
[6]B.T.Gao,Y.Q.Bao,J.H.Xie,et al,Passivity-based control of two-dimensional translational oscillator with rotational actuator,Transactions of the Institute of Measurement and Control,36(1):111-118,2014.
[7]V.D.Anton,M.K.Mikhail,Attitude dynamic of a spacecraft with variable structure at presence of harmonic perturbations,Applied Mathematical Modelling,38(7):2073-2089,2014.
[8]F.Kenji,N.Taishi,On trajectory tracking control of port-Hamiltonian systems with quaternions,in Proceeding of IEEE Conference on Decision and Control,Los Angeles,California,USA,2014:4820-4825.
[9]Y.C.Xie,H.Zhang,J.Hu,et al,Automatic control system design of Shenzhou spacecraft for rendezvous and docking,Science Sinica Technology,44(1):12-19,2014.(in Chinese)
[10]H.Leeghim,D.Lee,H.Bang,et al,Spacecraft attitude control by combination of various torquers,International Journal of Systems Science,40(10):995-1008,2009.
[11]H.R.Zhang,J.J.Fan,W.H.Zhang,Numerical simulation of separation of central stage and booster stage for a carrier rocket,Journal of National University of Defense Technology,36(2):7-12,2014.(in Chinese)
[12]P.Riedinger,M.Sigalotti,J.Daafouz.On the algebratic characterization of invariant sets of switched linear systems,Automatica,46(6):1047-1052,2010.
[13]Y.Z.Hou,C.Y.Dong,Q.Wang.Gain scheduled control:switched polytopic system approach,Journal of Guidance,Control and Dynamics,34(2):623-629,2011.
[14]M.S.Branicky.Analyzing continuous switching systems:theory and example,in Proceedings of the American Control Conference,Maryland,USA,1994:3100-3114.
[15]Q.L.Hu,G.F.Ma,Y.Jiang.Variable structure attitude control with time-varying sliding surface for flexible spacecraft under control input constraint,Journal of Harbin Institute of Technology,40(9):1358-1362,2008.(in Chinese)
[16]P.K.C.Wang,F.Y.Hadaegh.Stability analysis of switched dynamical system with state-space dilation and contraction,Journal of Guidance,Control and Dynamics,31(2):395-401,2008.
[17]D.Zheng.Linear system theory.2nd ed.Beijing:Tsinghua University Press,2002:244-248.
[2]J.J.E.Slotine,M.D.Benedetto,Hamilton adaptive control of spacecraft,IEEE Transaction on Automatic Control,35(7):848-852,1990.
[3]H.Yoon,B.H.Agrawal.Adaptive control of uncertain Hamilton multi-input multi-output systems:With application to spacecraft control,IEEE Transactions on Control Systems Technology,17(4):900-906,2009.
[4]X.P.Shi,G.P.Yuan,Robust adaptive control of Hamilton system and its application in spacecraft,Journal of Sichuan university(Engineering Science Edition),45(5):130-144,2013.(in Chinese)
[5]Y.D.Zhang,Q.F.Chen,J.H.Dai,Study on Hamiltonian dynamic model and solving method of distributed satellite system relative motion,Journal of National University of Defense Technology,32(2):12-16,2010.(in Chinese)
[6]B.T.Gao,Y.Q.Bao,J.H.Xie,et al,Passivity-based control of two-dimensional translational oscillator with rotational actuator,Transactions of the Institute of Measurement and Control,36(1):111-118,2014.
[7]V.D.Anton,M.K.Mikhail,Attitude dynamic of a spacecraft with variable structure at presence of harmonic perturbations,Applied Mathematical Modelling,38(7):2073-2089,2014.
[8]F.Kenji,N.Taishi,On trajectory tracking control of port-Hamiltonian systems with quaternions,in Proceeding of IEEE Conference on Decision and Control,Los Angeles,California,USA,2014:4820-4825.
[9]Y.C.Xie,H.Zhang,J.Hu,et al,Automatic control system design of Shenzhou spacecraft for rendezvous and docking,Science Sinica Technology,44(1):12-19,2014.(in Chinese)
[10]H.Leeghim,D.Lee,H.Bang,et al,Spacecraft attitude control by combination of various torquers,International Journal of Systems Science,40(10):995-1008,2009.
[11]H.R.Zhang,J.J.Fan,W.H.Zhang,Numerical simulation of separation of central stage and booster stage for a carrier rocket,Journal of National University of Defense Technology,36(2):7-12,2014.(in Chinese)
[12]P.Riedinger,M.Sigalotti,J.Daafouz.On the algebratic characterization of invariant sets of switched linear systems,Automatica,46(6):1047-1052,2010.
[13]Y.Z.Hou,C.Y.Dong,Q.Wang.Gain scheduled control:switched polytopic system approach,Journal of Guidance,Control and Dynamics,34(2):623-629,2011.
[14]M.S.Branicky.Analyzing continuous switching systems:theory and example,in Proceedings of the American Control Conference,Maryland,USA,1994:3100-3114.
[15]Q.L.Hu,G.F.Ma,Y.Jiang.Variable structure attitude control with time-varying sliding surface for flexible spacecraft under control input constraint,Journal of Harbin Institute of Technology,40(9):1358-1362,2008.(in Chinese)
[16]P.K.C.Wang,F.Y.Hadaegh.Stability analysis of switched dynamical system with state-space dilation and contraction,Journal of Guidance,Control and Dynamics,31(2):395-401,2008.
[17]D.Zheng.Linear system theory.2nd ed.Beijing:Tsinghua University Press,2002:244-248.