Movement Conversion Nonlinear modeling and Simulation of Precision Line Transmission Products
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- 英文论文题名：Movement Conversion Nonlinear modeling and Simulation of Precision Line Transmission Products
- 论文作者：Jiaolong Zhang ; Jun Zhou
- 英文论文作者：Jiaolong Zhang ; Jun Zhou ; Institute of Precision Guidance and Control ; Northwestern Polytechnical University
- 年：2017
- 作者机构：Institute of Precision Guidance and Control,Northwestern Polytechnical University;
- 英文论文关键词：line transmission ; ball screw ; planetary roller screw ; transmission ratio nonlinear ; electric serve system
- 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（B）
- 英文会议录名称：Proceedings of the 36th Chinese Control Conference（B）
- 语种：英文
- 分类号：TP391.9;V242
- 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：403k
- 原文格式：D
- 会议级别：全国
摘要
Aiming at the nonlinear transmission problem resulting from movement conversion of line transmission products in aircraft electric serve system, in order to define the serve system states all the time, and then improve the precision of the mathematical model. With fork structure and rocker arm structure as the research objects, firstly, applying speed synthesis theory and structure force balance theory, the uniform nonlinear transmission ratio model are obtained respectively. Secondly, By means of modeling and analysis of the nonlinear transmission ratio, and utilizing computer aided model, the quantitative relationship between the transmission ratio nonlinear term and structure size is calculated. Finally, the dynamic model of serve system including transmission ratio is modeled, and the dynamic properties of the two structure forms are simulated by using MATLAB software then the quantitative errors by using constant ratio instead of nonlinear ratio are calculated. The research results summarize the different nonlinear transmission characteristics and the range of application, which provide theoretical basis for the determination of electrical serve system structure form and size.
Aiming at the nonlinear transmission problem resulting from movement conversion of line transmission products in aircraft electric serve system, in order to define the serve system states all the time, and then improve the precision of the mathematical model. With fork structure and rocker arm structure as the research objects, firstly, applying speed synthesis theory and structure force balance theory, the uniform nonlinear transmission ratio model are obtained respectively. Secondly, By means of modeling and analysis of the nonlinear transmission ratio, and utilizing computer aided model, the quantitative relationship between the transmission ratio nonlinear term and structure size is calculated. Finally, the dynamic model of serve system including transmission ratio is modeled, and the dynamic properties of the two structure forms are simulated by using MATLAB software then the quantitative errors by using constant ratio instead of nonlinear ratio are calculated. The research results summarize the different nonlinear transmission characteristics and the range of application, which provide theoretical basis for the determination of electrical serve system structure form and size.
Aiming at the nonlinear transmission problem resulting from movement conversion of line transmission products in aircraft electric serve system, in order to define the serve system states all the time, and then improve the precision of the mathematical model. With fork structure and rocker arm structure as the research objects, firstly, applying speed synthesis theory and structure force balance theory, the uniform nonlinear transmission ratio model are obtained respectively. Secondly, By means of modeling and analysis of the nonlinear transmission ratio, and utilizing computer aided model, the quantitative relationship between the transmission ratio nonlinear term and structure size is calculated. Finally, the dynamic model of serve system including transmission ratio is modeled, and the dynamic properties of the two structure forms are simulated by using MATLAB software then the quantitative errors by using constant ratio instead of nonlinear ratio are calculated. The research results summarize the different nonlinear transmission characteristics and the range of application, which provide theoretical basis for the determination of electrical serve system structure form and size.
引文
[1]Sha Nansheng,Li Jun.Research on airborne power-by-wire integrated electrical actuation and control systems,Journal of Beijing University of Aeronautics and Astronautics,2004,30(9):909-912.
[2]Ren Xiaojun,Tang Miao,Zhang Xinhua,Xie Jinsong.Status of new integrated direct-drive electromechanical actuation systems,Control Technology of Tactical Missile,2010,27(2):31-39.
[3]Liu Geng,Ma Shangjun,Tong Ruiting,Guan Dong.New Development and Key Technology of Planetary Roller Screw,Mechanical Transmission,2012,36(05):103-108.
[4]ABDELHAFEZA,FORSYTAJ.A review of more-electric aircraft,13th International Conference on Aerospace Sciences Aviation Technology,Cairo,Egypt,2009:1-13
[5]CLAEYSSENF,JANKERP,LELETTYR.New actuators for aircraft,space and military applications,12th International Conference on New Actuators,Bremen,Germany,2010:324-330.
[6]Zhang Wenjie,Liu Geng,Ma Shangjun,Tong Ruiting.Load Distribution of Planetary Roller Screw Mechanism with Different Installations,Journal of Northwestern Polytechnical University,2015,33(2):229-236.
[7]Velinsky S A,Chu B,Lasky T A.Kinematics and Efficiency Analysis of the planetary Roller Screw Mechanism,Mechanical Design,2009,131(1):1-8.
[8]Ma Shangjun,Liu Geng,Tong Ruiting,et al.A Frictional Heat Model of Planetary Roller Screw Mechanism Considering Load Distribution,Mechanics Based Design of Structures and machines,2015,43:164-182.
[9]Yohan Lin,Ethan Baumann,David M.Bose,Roger Beck,Gavin Jenney.Tests and techniques for characterizing and modeling X-43A electromechanical actuators,NASA/TM,2008-214637.
[10]John D.Albright and Landon A.Moore.Development and Implementation of Electromechanical Actuators for the X-38Atmospheric Test Vehicles,AIAA,Atmospheric Flight Mechanics Conference and Exhibit,18-21 August 2008,Honolulu,Hawaii.
[11]Stephen C,Gavin D.Jenney,David Dawson.Flight Test Experience with an Electromechanical Actuator on the F-18Systems Research Aircraft,AIAA,the 19th Digital Avionics Systems Conference,October 7-123,2000,Philadelphia.
[12]J.R.Cowan,W.N.Myers.Design and Test of a High Power Electromechanical Actuator for Trust Vector Control,AIAA,1992.
[13]Mary Ellen Roth,Cleveland,Ohio.Electromechanical Actuation for Thrust Vector Control Applications,NASATechnical Memorandum 102548,1990.
[14]Wissam Karam,Jean-Charles Mare.Modelling and simulation of mechanical transmission in roller-screw electromechanical actuators.Aircraft Engineering and Aerospace Technology,2009,81:288-298
[15]Zhang Jiaolong,Zhou Jun,Zhou Fengqi.Application study on ball screw actuator,Machinery&Electronics,2011(10):15-19.
[16]Li Qiang,Zhang Jiaolong,Zhou Jun,Gao Zhigang.Nonlinear Modeling and Simulation of a Planetary Roller Screw Based Transmission,Journal of Northwestern Polytechnical University,2015,33(5):739-743.
[2]Ren Xiaojun,Tang Miao,Zhang Xinhua,Xie Jinsong.Status of new integrated direct-drive electromechanical actuation systems,Control Technology of Tactical Missile,2010,27(2):31-39.
[3]Liu Geng,Ma Shangjun,Tong Ruiting,Guan Dong.New Development and Key Technology of Planetary Roller Screw,Mechanical Transmission,2012,36(05):103-108.
[4]ABDELHAFEZA,FORSYTAJ.A review of more-electric aircraft,13th International Conference on Aerospace Sciences Aviation Technology,Cairo,Egypt,2009:1-13
[5]CLAEYSSENF,JANKERP,LELETTYR.New actuators for aircraft,space and military applications,12th International Conference on New Actuators,Bremen,Germany,2010:324-330.
[6]Zhang Wenjie,Liu Geng,Ma Shangjun,Tong Ruiting.Load Distribution of Planetary Roller Screw Mechanism with Different Installations,Journal of Northwestern Polytechnical University,2015,33(2):229-236.
[7]Velinsky S A,Chu B,Lasky T A.Kinematics and Efficiency Analysis of the planetary Roller Screw Mechanism,Mechanical Design,2009,131(1):1-8.
[8]Ma Shangjun,Liu Geng,Tong Ruiting,et al.A Frictional Heat Model of Planetary Roller Screw Mechanism Considering Load Distribution,Mechanics Based Design of Structures and machines,2015,43:164-182.
[9]Yohan Lin,Ethan Baumann,David M.Bose,Roger Beck,Gavin Jenney.Tests and techniques for characterizing and modeling X-43A electromechanical actuators,NASA/TM,2008-214637.
[10]John D.Albright and Landon A.Moore.Development and Implementation of Electromechanical Actuators for the X-38Atmospheric Test Vehicles,AIAA,Atmospheric Flight Mechanics Conference and Exhibit,18-21 August 2008,Honolulu,Hawaii.
[11]Stephen C,Gavin D.Jenney,David Dawson.Flight Test Experience with an Electromechanical Actuator on the F-18Systems Research Aircraft,AIAA,the 19th Digital Avionics Systems Conference,October 7-123,2000,Philadelphia.
[12]J.R.Cowan,W.N.Myers.Design and Test of a High Power Electromechanical Actuator for Trust Vector Control,AIAA,1992.
[13]Mary Ellen Roth,Cleveland,Ohio.Electromechanical Actuation for Thrust Vector Control Applications,NASATechnical Memorandum 102548,1990.
[14]Wissam Karam,Jean-Charles Mare.Modelling and simulation of mechanical transmission in roller-screw electromechanical actuators.Aircraft Engineering and Aerospace Technology,2009,81:288-298
[15]Zhang Jiaolong,Zhou Jun,Zhou Fengqi.Application study on ball screw actuator,Machinery&Electronics,2011(10):15-19.
[16]Li Qiang,Zhang Jiaolong,Zhou Jun,Gao Zhigang.Nonlinear Modeling and Simulation of a Planetary Roller Screw Based Transmission,Journal of Northwestern Polytechnical University,2015,33(5):739-743.