Dynamics and Autopilot Design for BTT Aircraft with Flaps Control System
详细信息 查看官网全文
- 英文论文题名：Dynamics and Autopilot Design for BTT Aircraft with Flaps Control System
- 论文作者：Jinlu Dong ; Di Zhou
- 英文论文作者：Jinlu Dong ; Di Zhou ; Harbin Institute of Technology
- 年：2017
- 作者机构：Harbin Institute of Technology;
- 英文论文关键词：flap control ; zero dynamics ; autopilot design ; feedback linearization
- 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：TJ765.2
- 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：6
- 文件大小：404k
- 原文格式：D
- 会议级别：全国
摘要
A tail-controlled BTT missile with flaps control is presented. First, we derive the nonlinear system model of the six-degree-of-freedom with two inputs. Based on choosing the angle-of-attack and roll angle as output variables, the internal dynamics of the system are analyzed by using differential geometry method, and are proved to be stabilized. An autopilot is designed by using the feedback linearization technique. Results of a numerical simulation of an autopilot design example show the effectiveness of the autopilot design.
A tail-controlled BTT missile with flaps control is presented. First, we derive the nonlinear system model of the six-degree-of-freedom with two inputs. Based on choosing the angle-of-attack and roll angle as output variables, the internal dynamics of the system are analyzed by using differential geometry method, and are proved to be stabilized. An autopilot is designed by using the feedback linearization technique. Results of a numerical simulation of an autopilot design example show the effectiveness of the autopilot design.
A tail-controlled BTT missile with flaps control is presented. First, we derive the nonlinear system model of the six-degree-of-freedom with two inputs. Based on choosing the angle-of-attack and roll angle as output variables, the internal dynamics of the system are analyzed by using differential geometry method, and are proved to be stabilized. An autopilot is designed by using the feedback linearization technique. Results of a numerical simulation of an autopilot design example show the effectiveness of the autopilot design.
引文
[1]H.Jin,S.Chang,J.Min.Plant inversion control of tail-controlled missiles[J].Journal of Guidance,Control,and Dynamics,1691-1696,1997.
[2]S.Gennaro.Output attitude tracking for flexible spacecraft[J].Automatica,38:1719-1726,2002.
[3]Y.Huang,T.Wang,L.Lin.Slip ratiocontrol of locomotion system based on sliding mode variable structue control[J].Acta Armamentarii,35(10):1707-1715,2014.
[4]J.R.Cloutier,D.Souza,C.P.Mracek.Nonlinear regulation and nonlinear H control via the state-dependent Riccati equation technique[C].Proceeding of the First International Conference on Nonlinear Problems in Aviation and Aerospace,Daytona Beach,FL,117-141,1996.
[5]I.Ha.Design of a CLOS guidance law via feedback linearization[J].Transaction on Aerospace and Electronic Systems,28:51-62,1992.
[6]R.Sira,H.The differential algebraic approach in nonlinear dynamical feedback controlled landing maneuvers[J].IEEE Transaction on Automatic control,37(4):518-524,1992.
[7]M.W.Elmar,H.W.Klaus.Attitude control of a reentry vehicle with internal dynamics[J].Journal of Guidance,Control,and Dynamics,26(6):846-854,2003.
[8]A.Isidori.Nonlinear control systems[M].London:Springer,1995.
[9]D.Zhou,C.T.Shao.Dynamics and autopilot design for endoatmospheric interceptors with dual control systems[J].Aerospace Science and Technology,13:291-300,2009.
[10]J.I.Lee,J.H.Oh,I.J.Ha,E.G.Kim,and H.J.Cho.A new approach to autopilot design for highly nonlinear missiles[J].Proc.of AIAA,Guidance Navigation and Control Conference,96-3915,1996.
[11]J.H.Oh,I.J.Ha.Missile autopilot design via functional inversion and time-scaled transformation[J]IEEE Trans.on Aerospace and Electronic Systems,33(1):64-76,1997.
[12]D.Chwa,J.Y.Choi.New parametric affine modeling and control for skid-to-turn missiles[J].IEEE Trans.on Control Systems Technology,9(2):335-347,2001.
[13]J.Hauser,S.Sastry,G.Meyer.Nonlinear controller design for slightly non minimum phase system:Application to V/STOL aircraft[J].Automatica,28(4),665–679,1992.
[14]P.K.Menon,M.Yousefpor,Design of nonlinear autopilot for high angle of attack missiles[J].In Proceedings of AIAA Guidance,navigation and control conference,San Diego,California,29–31,1996.
[15]J.H.Ryu,M.J.Tahk.Plant inversion control of tail-controlled missiles[J].In Proceedings of AIAA Guidance,navigation,and control conference,New Orleans,Louisiana,1691-1696,1997.
[16]S.H Kim,M.J Tahk.Missile acceleration controller design using proportional integral and non-linear dynamic control design method[J].Part G:J.Aerospace Engineering,1-16,2011.
[17]S.Houria,D.Emmanuel.Nonlinear missile autopilot design based on angle of attack normal form[J].European Journal of Control,154-164,2000.
[18]M.Tahk.Robustness Characteristics of Missile Autopilot Systems Based on Feedback Linearization[J].Japan Aircraft Symposium,Tokyo,1990.
[19]W.Tang,Y.Zhang,Q.Ma.Aerodynamics configuration design for elliptical cross section vehicle with flaps[J].Acta Aerodynamica Sinica,24(2):223-226,2006.
[20]F.Deng,H.Y.Ren,X.G.Li.Rudder effect of near space hypersonic gliding vehicle with different control surfaces[J].Acta Aerodynamica Sinica,32(2):240-245,2014.
[21]Y.Zhou.Research on control technology of reentry for reusable launch aircraft[D].Nanjing University of Aeronautics and Astronautics,Nanjing,2012.
[22]W.J.Hu,J.Zhou.Design of variable structure attitude control system for RLV[J].Journal of Northwestern Polytechnical University,(1):92-96,2007.
[23]K.K.Hassan.Nonlinear systems,third eidtion[M].Michigan,2007.
[2]S.Gennaro.Output attitude tracking for flexible spacecraft[J].Automatica,38:1719-1726,2002.
[3]Y.Huang,T.Wang,L.Lin.Slip ratiocontrol of locomotion system based on sliding mode variable structue control[J].Acta Armamentarii,35(10):1707-1715,2014.
[4]J.R.Cloutier,D.Souza,C.P.Mracek.Nonlinear regulation and nonlinear H control via the state-dependent Riccati equation technique[C].Proceeding of the First International Conference on Nonlinear Problems in Aviation and Aerospace,Daytona Beach,FL,117-141,1996.
[5]I.Ha.Design of a CLOS guidance law via feedback linearization[J].Transaction on Aerospace and Electronic Systems,28:51-62,1992.
[6]R.Sira,H.The differential algebraic approach in nonlinear dynamical feedback controlled landing maneuvers[J].IEEE Transaction on Automatic control,37(4):518-524,1992.
[7]M.W.Elmar,H.W.Klaus.Attitude control of a reentry vehicle with internal dynamics[J].Journal of Guidance,Control,and Dynamics,26(6):846-854,2003.
[8]A.Isidori.Nonlinear control systems[M].London:Springer,1995.
[9]D.Zhou,C.T.Shao.Dynamics and autopilot design for endoatmospheric interceptors with dual control systems[J].Aerospace Science and Technology,13:291-300,2009.
[10]J.I.Lee,J.H.Oh,I.J.Ha,E.G.Kim,and H.J.Cho.A new approach to autopilot design for highly nonlinear missiles[J].Proc.of AIAA,Guidance Navigation and Control Conference,96-3915,1996.
[11]J.H.Oh,I.J.Ha.Missile autopilot design via functional inversion and time-scaled transformation[J]IEEE Trans.on Aerospace and Electronic Systems,33(1):64-76,1997.
[12]D.Chwa,J.Y.Choi.New parametric affine modeling and control for skid-to-turn missiles[J].IEEE Trans.on Control Systems Technology,9(2):335-347,2001.
[13]J.Hauser,S.Sastry,G.Meyer.Nonlinear controller design for slightly non minimum phase system:Application to V/STOL aircraft[J].Automatica,28(4),665–679,1992.
[14]P.K.Menon,M.Yousefpor,Design of nonlinear autopilot for high angle of attack missiles[J].In Proceedings of AIAA Guidance,navigation and control conference,San Diego,California,29–31,1996.
[15]J.H.Ryu,M.J.Tahk.Plant inversion control of tail-controlled missiles[J].In Proceedings of AIAA Guidance,navigation,and control conference,New Orleans,Louisiana,1691-1696,1997.
[16]S.H Kim,M.J Tahk.Missile acceleration controller design using proportional integral and non-linear dynamic control design method[J].Part G:J.Aerospace Engineering,1-16,2011.
[17]S.Houria,D.Emmanuel.Nonlinear missile autopilot design based on angle of attack normal form[J].European Journal of Control,154-164,2000.
[18]M.Tahk.Robustness Characteristics of Missile Autopilot Systems Based on Feedback Linearization[J].Japan Aircraft Symposium,Tokyo,1990.
[19]W.Tang,Y.Zhang,Q.Ma.Aerodynamics configuration design for elliptical cross section vehicle with flaps[J].Acta Aerodynamica Sinica,24(2):223-226,2006.
[20]F.Deng,H.Y.Ren,X.G.Li.Rudder effect of near space hypersonic gliding vehicle with different control surfaces[J].Acta Aerodynamica Sinica,32(2):240-245,2014.
[21]Y.Zhou.Research on control technology of reentry for reusable launch aircraft[D].Nanjing University of Aeronautics and Astronautics,Nanjing,2012.
[22]W.J.Hu,J.Zhou.Design of variable structure attitude control system for RLV[J].Journal of Northwestern Polytechnical University,(1):92-96,2007.
[23]K.K.Hassan.Nonlinear systems,third eidtion[M].Michigan,2007.