[1]屈高敏,李继广.基于微分几何方法的飞翼无人飞行器解耦飞行控制[J].弹箭与制导学报,2018,38(02):116-122.[doi:10.15892/j.cnki.djzdxb.2018.02.026]
 QU Gaomin,LI Jiguang.The Attitude Decoupling Control of the Flying Wing UAV Based on the Differential Geometry Method[J].,2018,38(02):116-122.[doi:10.15892/j.cnki.djzdxb.2018.02.026]
点击复制

基于微分几何方法的飞翼无人飞行器解耦飞行控制

参考文献/References:

[1] 洪都集团. 无人机与有人机协同作战发展研究 [R]. 南昌:洪都集团, 2014, 6.
[2] SU B W. Study of advanced flight control techniques of uninhabited aerial vehicles [D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2001.
[3] HUANG Y M. Study of flight control techniques of helicopters [D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 1999.
[4] WANG J. Nonlinear dynamic inversion flight control for ASTOVL aircrafts [D]. Nanjing: Nanjing University of Aeronautics and As tron au tics, 2000.
[5] ZHU E. Technique study for high-angle-of-attack supermaneu verable flight control [D]. Nanjing: Nan Jing University of Aeronautics and Astronautics, 1995.
[6] ZHU J Q. Neural network and nonlinear dynamic inversion based supermaneu verable flight control [D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2004.
[7] KRENER A J. On the equivalence of control systems and the linear systems and the linearization of nonlinear systems [J]. SIAM Journal of Control, 1973, 11: 670-676.
[8] CHENG D, TARN T J, ISIDORI A. Global external linearization of nonlinear system via feedback [J]. IEEE Transactions on Automatic Control, 1985, 30(8): 808-811.
[9] MENON P K. Differential geometric estimators for nonlinear dynamic systems [J]. AIAA Guidance, Navigation and Control Conference and Exhibit, 2008, 18(21): 1-18.
[10] BAKKER C, PARKS G. JARRETT J. On the application of differential geometry to MDO:AIAA 2012-5556[R].[S.l.]:AIAA,2012.
[11] BAKKER C, PARKS G, JARRETT J. Differential geometry and design coupling in MDO: AIAA 2013-1535[R]. [S.l.]:AIAA, 2013.
[12] BROCKETT R W. Feedback invariants for nonlinear systems [J]. IFAC Proceedings Volumes, 1978, 11(1): 1115-1120.
[13] CHARLET B, LEVINE J, MARINO R. Sufficient conditions for dynamic state feedback linearzation [J]. SIAMJJ. Control Optim, 1991, 29(1): 38-57.
[14] CHARLET B, LEVINE J, MARINOR. On dynamic feedback linearization [J]. System and Control Lettets, 1989, 13(2): 143-151.
[15] TOMLIN C,LYGEROS J,BENVENUTI L,et al. Output tracking for a non-minimum phase dynamic CTOL aircraft model[C]//IEEE. Proceedings of 1995 34th IEEE Conference on Decision and Control. New York:IEEE Publications,1995:1867-1872.
[16] NAIDU D S,CALISE A J. Singular perturbations and time scales in guidance and control of aerospace systems: a survey [J].Journal of Guidance Control and Dynamics,2001,24(6):1057-1078.
[17] TOMLIN C J, SASTRY S S. Bounded tracking for non-minimum phase nonlinear systems with fast zero dynamics [J].International Journal of Control, 1998,68(4):819-848.
[18] BORTOFF S A. Approximate state-feedback linearization using spline functions[J].Auto Matica, 1997, 33(8): 1449-1458.
[19] BAUMANN W,RUGH W. Feedback control of nonlinear systems by extended linearization[J].IEEE Transactions on Automatic Control, 1986, 31(1):40-46.
[20] DOYLE F J, ALGOWER F,MORARI M. A normal form approach to approximate input-output linearization for maximum phase nonlinear SISO systems[J].IEEE Transactions on Automatic Control,1996,41(2):305-309.
[21] HAUSER J,SASTRY S,MEYER G. Nonlinear control design for slightly non-minimum phase systems: Application to V/STOL aircraft[J].Automatica,1992,28(4):665-679.
[22] MEYER G,SU Rand,HUNT L R. Application of nonlinear transformations to automatic flight control[J].Automatica,1984,20(1):103-107.

相似文献/References:

[1]郝永平,郭煜洋,张嘉易,等.轴承摩擦力矩对智能引信控制效率的影响[J].弹箭与制导学报,2014,34(4):69.
 HAO Yongping,GUO Yuyang,ZHANG Jiayi,et al.Influence of Bearing Friction Torque on Control Efficiency of Smart Fuse[J].,2014,34(02):69.
[2]苗昊春,马清华,陈 韵,等.基于滑模趋近律的潜空导弹垂直出水姿态控制律设计[J].弹箭与制导学报,2015,35(2):45.[doi:10.15892/j.cnki.djzdxb.2015.02.012]
 MIAO Haochun,MA Qinghua,CHEN Yun,et al.Attitude Control Law Design of Vertical Water-exit of Submarine-to-air Missile Based on Sliding Mode Control[J].,2015,35(02):45.[doi:10.15892/j.cnki.djzdxb.2015.02.012]
[3]王 晔,程昊宇.运载火箭姿态的自抗扰控制器设计[J].弹箭与制导学报,2015,35(4):11.[doi:10.15892/j.cnki.djzdxb.2015.04.003]
 WANG Ye,CHENG Haoyu.Active Disturbance Rejection Control of Attitude for Launch Vehicle[J].,2015,35(02):11.[doi:10.15892/j.cnki.djzdxb.2015.04.003]

备注/Memo

收稿日期:2017-07-30 基金项目:陕西省自然科学基金(2016JM1014); 陕西省教育厅自然科学基金(16JK1396); 通用航空工程技术中心建设基金(XHY-2016084); 校级科研基金(2017KY1229)资助 第一作者简介:屈高敏(1990-),女,陕西渭南人,助教,博士研究生,研究方向:飞行器总体设计与飞行器控制技术。

更新日期/Last Update:

2018-02-11