考虑舵机动力学的舵系统颤振特性分析

张新榃; 吴志刚; 杨超

考虑舵机动力学的舵系统颤振特性分析

北京航空航天大学航空科学与工程学院, 北京 100191

详细信息

作者简介:
张新榃(1984-),男,陕西西安人,博士生,xintanzhang@yahoo.com.cn.

中图分类号: V 215.3
计量
- 文章访问数: 2974
- HTML全文浏览量: 100
- PDF下载量: 943
- 被引次数: 0
出版历程
- 收稿日期: 2010-04-19
- 网络出版日期: 2011-08-30

Flutter analysis for rudder considering actuator’s dynamics

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 飞行器舵面的颤振特性与舵机动态特性有很大关系.提出了2种考虑舵机复刚度颤振分析的工程分析方法,第1种方法思想是对舵面和舵机的耦合系统(下文称舵系统)模型在各种来流速度下进行状态矩阵的稳定性判断,称为时域方法;第2种方法是将舵机复刚度特性包含在频域颤振方程中,使用改进的V-g法求解该方程得到舵系统颤振特性,称为频域方法.通过对舵系统模型算例的数值计算验证了方法的可行性;发现传统的按扭转频率进行舵机刚度等效的舵面颤振工程计算方法的结果相对于该方法有较大差别.说明当舵机动力学特性较差时,在舵面颤振分析中考虑舵机复刚度特性是很有必要的.
- 颤振 /
- 舵面 /
- 舵机 /
- 复刚度
Abstract: Missile rudder-s flutter characteristics are influenced by the actuator-s impedance. Two new methods which can analyze the rudder-s flutter stabilities were used respectively in time domain and frequency domain. Stability judgement of the state matrix was required in the time domain method. Actuator-s impedance characteristics had to be included by the flutter equation which can only be solved by the improved k method when the frequency domain method was used. The two methods- validity was checked by numerical calculation of a rudder model with an actuator. Traditional way of predicting flutter boundary was also used to analyze the rudder, and the flutter velocity/frequency were different from the new methods- results. It indicates that considering actuator-s dynamic characteristics while doing a rudder-s flutter analysis is very important.
- flutter /
- rudder /
- actuator /
- impedance

HTML全文

参考文献(1)

[1] 吴志刚,杨超.细长体弹箭的气动弹性问题与研究方法 //第九届全国空气弹性学术交流会.成都,中国空气动力学学会,2005:102-110 Wu Zhigang,Yang Chao.Aeroelastic problems and methodology of slender missiles //The 9th National Aeroelasticity Conference.Chengdu:Chinese Aerodynamics Research Society,2005:102-110(in Chinese) [2] Laurenson R M,Trn R M.Flutter analysis of missile control surfaces containing structural nonlinearities[J].AIAA Journal,1980,18(10):1245-1251 [3] 高新绪.电动、气动和液压三类伺服机构快速性的比较[J].航空兵器,1995(1):17-20 Gao Xinxu.Comparison of the rapidity of electric,pneumatic and hydraulic actuators[J].Aero Weaponry,1995(1):17-20(in Chinese) [4] 吴娟,张家盛,康光会.舵机系统动刚度的分析研究[J].科学技术与工程,2008,8(4):1124-1128 Wu Juan,Zhang Jiasheng,Kang Guanghui.Analysis and research of the impedance of hydraulic booster location system[J].Science Technology and Engineering,2008,8(4):1124-1128(in Chinese) [5] 吴娟,张家盛,康光会.舵机动刚度试验台的建模与仿真[J].机床与液压,2008,36(7):134-136 Wu Juan,Zhang Jiasheng,Kang Guanghui.Simulation and modeling of the tester applied to test the impedance of hydraulic booster location system[J].Machine Tool & Hydraulics,2008,36(7):134-136(in Chinese) [6] Shin W H,Lee I,Shin Y S,et al.Nonlinear aeroelastic analysis for a control fin with an actuator[J].Journal of Aircraft,2007,44(2):597-605 [7] 陈桂彬,邹丛青,杨超.气动弹性设计基础[M].北京:北京航空航天大学出版社,2004:103-106,179-183,201-208 Chen Guibin,Zou Congqing,Yang Chao.Elements of aeroelastic design[M].Beijing:Beijing University of Aeronautics and Astronautics Press,2004:103-106,179-183,201-208(in Chinese) [8] 刘金琨.先进PID控制及其MATLAB仿真[M].北京:电子工业出版社,2003:271-282 Liu Jinkun.Advanced PID control and simulation[M].Beijing:Publishing House of Electronics Industry,2003:271-282(in Chinese) [9] 王文亮.结构振动与动态子结构方法[M].上海:复旦大学出版社,1985:229-233 Wang Wenliang.Vibration and substructure methodology[M].ShangHai:Fudan University Press,1985:229-233(in Chinese) [10] 管德.飞机气动弹性力学手册[M].北京:航空工业出版社,1994:126-128 Guan De.Aeroelastic handbook of aircraft[M].Beijing:Aeronautic Industry Press,1994:126-128(in Chinese) [11] Kapel M.Time-domain aeroservoelastic modeling using weighted unsteady aerodynamic forces[J].Journal of Guidance,Control and Dynamics,1990,13(1):30-37 [12] 张新榃.舵面的颤振机理与试验研究 .北京:北京航空航天大学航空科学与工程学院,2009 Zhang Xintan.Studies on flutter mechanism and test of rudder .Beijing:School of Aeronautic Science and Engineering,Beijing University of Aeronautics and Astronautics,2009(in Chinese)

施引文献

资源附件(0)

访问统计