一种共轴式直升机操纵机构的运动学建模与分析

袁夏明; 朱纪洪; 陈志刚; 鲁兴举

doi:10.7527/S1000-6893.2013.0188

航空学报 >

2013 , Vol. 34 >Issue 5: 988 - 1000

DOI: https://doi.org/10.7527/S1000-6893.2013.0188

流体力学与飞行力学

一种共轴式直升机操纵机构的运动学建模与分析

袁夏明 ,
朱纪洪 ,
陈志刚 ,
鲁兴举

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1. 清华大学计算机科学与技术系, 北京 100084;
2. 兰州交通大学机电工程学院, 甘肃兰州 730070;
3. 国防科学技术大学机电工程与自动化学院, 湖南长沙 410073

袁夏明男, 博士研究生。主要研究方向: 无人直升机建模与飞行控制。 Tel: 010-62796711-8063 E-mail: summersbright@yahoo.com.cn;朱纪洪男, 博士, 教授, 博士生导师。主要研究方向: 飞行控制与导航、鲁棒控制与非线性控制。 Tel: 010-62796706 E-mail: jhzhu@tsinghua.edu.cn;陈志刚男, 硕士研究生。主要研究方向: 仿生机器人、空中机器人。 Tel: 010-62796711-8045 E-mail: chenzgbs@126.com;鲁兴举男, 博士研究生, 讲师。主要研究方向: 飞行器制导与控制。 Tel: 0731-84576381 E-mail: luxingju@163.com

收稿日期: 2012-06-07

修回日期: 2012-11-05

网络出版日期: 2012-12-18

基金资助

国家自然科学基金(60974142)

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Kinematic Modeling and Analysis of a Coaxial Helicopter’s Actuating Mechanism

YUAN Xiaming ,
ZHU Jihong ,
CHEN Zhigang ,
LU Xingju

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1. Department of Computer Science and Technology, Tsinghua University, Beijing 100084, China;
2. School of Mechatronic Engineering, Lanzhou Jiaotong University, Lanzhou 730070, China;
3. College of Mechatronic Engineering and Automation, National University of Defense Technology, Changsha 410073, China

Received date: 2012-06-07

Revised date: 2012-11-05

Online published: 2012-12-18

Supported by

National Natural Science Foundation of China (60974142)

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摘要

共轴式直升机操纵机构的输入/输出运动学关系复杂、非线性严重,不同通道间控制耦合大,其中航向采用全差动的操纵机构最为复杂。为了分析用比例关系简化建模所引起的误差及利用逆运动学进行操纵系统线性化,必须对操纵机构运动学进行精确建模。针对一种航向全差动操纵机构,首先,运用机构学原理,通过去除过约束、局部自由度对机构进行简化,计算得到操纵机构自由度;然后,将操纵机构分为3个子模块,通过对每个模块应用空间机构位置分析方法进行正向、逆向运动学推导,建立系统完整的运动学模型;利用光学测量原理设计了测试系统,并通过实验验证了所建模型的正确性;最后给出了所建模型在共轴式直升机建模、操纵解耦及线性化方面的应用方法。

关键词： 直升机; 操纵机构; 运动学; 建模; 自由度

本文引用格式

袁夏明 , 朱纪洪 , 陈志刚 , 鲁兴举 . 一种共轴式直升机操纵机构的运动学建模与分析[J]. 航空学报, 2013 , 34(5) : 988 -1000 . DOI: 10.7527/S1000-6893.2013.0188

Abstract

The kinematic relationship between the input and output of a coaxial helicopter's actuating mechanism is complicated and seriously nonlinear, and coupled among different channels as well, especially for the mechanism in yaw control which is fully-differential. For the purpose of error analysis on simplified modeling using proportional relationships, and linearization on the actuating system by inverse kinematics, it is necessary to model the actuating mechanism precisely. With regard to a fully-differential actuating mechanism, the over-constraint and local degrees of freedom are firstly eliminated based on the theory of mechanism, to calculate the total degrees of freedom of the actuating mechanism. Next, after dividing the mechanism into three sub-modules, the method of position analysis of spatial mechanisms is applied to derive the forward and inverse kinematic model of each sub-module to establish the complete kinematic model. Then a measurement system is designed based on the principle of optical measurement, and the established model is verified to be correct through experiment. Finally, the method of application with the established model to the modeling, actuating decoupling and linearization of coaxial helicopters is provided.

Key words： helicopter; actuating mechanism; kinematics; modeling; degree of freedom

参考文献

[1] Cai G W, Chen B M, Lee T H. Unmanned rotorcraft systems. London, UK: Springer, 2011: 14-16.
[2] Tischler M B, Remple R K. Aircraft and rotorcraft system identification, engineering methods with flight-test examples. Virginia, USA: AIAA, 2006: 8-9.
[3] Chen M. Technology characteristic and development of coaxial rotor helicopter. Aeronautical Manufacturing Technology, 2009(17): 26-31. (in Chinese) 陈铭. 共轴双旋翼直升机的技术特点及发展. 航空制造技术, 2009(17): 26-31.
[4] Yang Y L, Fan S S, Du X, et al. Analysis on size optimization of equivalent parallel mechanism of stationary ring of swashplate. Journal of Mechanical Engineering, 2010, 46(7): 48-56. (in Chinese) 杨育林, 樊少帅, 杜雄, 等. 自动倾斜器不旋转环操纵机构等效并联机构尺寸优化分析. 机械工程学报, 2010, 46(7): 48-56.
[5] Civita M L. Integrated modeling and robust control for full-envelope flight of robotic helicopters. Pennsylvania, USA: Carnegie Mellon University, 2002: 11-26.
[6] Raptis I A, Valavanis K P. Linear and nonlinear control of small-scale unmanned helicopters. New York, USA: Springer, 2010: 103-135.
[7] Lange C, Ranjbaran F, Angeles J, et al. The kinematics of the swashplate mechanism of VTOL unmanned aerial vehicle. Multibody System Dynamics, 1999, 3(4): 333-365.
[8] Lange C, Angeles J, Ranjbaran F, et al. The dynamics of the swashplate mechanism of VTOL unmanned aerial vehicle. Multibody System Dynamics, 2001, 5(2): 105-131.
[9] Saffarian M, Fahimi F. A comprehensive kinematic analysis of a model helicopter's actuating mechanism. Proceedings of 44th AIAA Aerospace Sciences Meeting and Exi-bit, 2008: 1-25.
[10] Sabaapour M R, Zohoor H. Analysis of a swashplate mechanism of a hingeless rotor hub with the flybar in a model helicopter, part I: kinematics. Journal of System Design and Dynamics, 2010, 4(4): 616-631.
[11] Feng Y C, Du H F. Control system of semi-differential yawing for coaxial helicopters. Acta Aeronautica et Astronautica Sinica, 1997, 18(1): 117-119. (in Chinese) 冯亚昌, 杜慧芳. 共轴式直升机半差动航向操纵系统. 航空学报, 1997, 18(1): 117-119.
[12] Feng Y C, Li S J. Analysis and study dynamical characteristics of control system of small coaxial helicopter. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(5): 410-414. (in Chinese) 冯亚昌, 李胜军. 共轴式小型直升机操纵系统动态特性分析研究. 北京航空航天大学学报, 2003, 29(5): 410-414.
[13] Lv J G, Wang J D, Chen D R. A new prototype rotor manipulation mechanism for unmanned micro-helicopter. Mechanical Science and Technology, 2001, 20(6): 855-883. (in Chinese) 吕俊刚, 汪家道, 陈大融. 一种微型无人直升机旋翼操纵机构. 机械科学与技术, 2001, 20(6):855-883.
[14] Dou S C, Liu L. The analysis of control mechanism of a kind of unmanned helicopter. Mechanical and Electrical Engineering Magazine, 2005, 22(2): 43-46. (in Chinese) 窦尚成, 刘亮. 一类无人直升机的旋翼操纵机构的分析. 机电工程, 2005, 22(2): 43-46.
[15] Merlet J P. Parallel robots. 2nd ed. Dordrecht, Netherland: Springer, 2006: 12-17.
[16] Vinod K L. Computational investigation of micro-scale coaxial rotor aerodynamics in hover. Maryland, USA: University of Maryland at College Park, 2009.
[17] Deng Y M, Hu J Z, Tao R. Effect of aerodynamic interactions between dual rotors of coaxial helicopter on course control. Flight Dynamics, 2003, 21(3): 21-24. (in Chinese) 邓彦敏, 胡继忠, 陶然. 共轴式直升机旋翼气动干扰对航向操纵的影响. 飞行力学, 2003, 21(3): 21-24.
[18] Chen M, Hu J Z. Analysis of dynamic response of direction control for a full-differential coaxial helicopter. Flight Dynamics, 2001, 19(4): 26-30. (in Chinese) 陈铭, 胡继忠. 共轴式直升机全差动航向操纵的动态响应分析. 飞行力学, 2001, 19(4): 26-30.
[19] Xu G F, Chen M. Decoupling analysis between yaw and collective pitch controls of coaxial helicopter using free wake arithmatic. Journal of Beijing University of Aeronautics and Astronautics, 2011, 37(2): 249-252. (in Chinese) 徐冠峰, 陈铭. 基于自由尾迹的共轴直升机航向/总距解耦分析. 北京航空航天大学学报, 2011, 37(2): 249-252.

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