特种风洞试验中气动伺服弹性失稳故障分析

唐波; 吴志刚; 杨超; 马成骥

doi:10.13700/j.bh.1001-5965.2015.0339

特种风洞试验中气动伺服弹性失稳故障分析

doi: 10.13700/j.bh.1001-5965.2015.0339

北京航空航天大学航空科学与工程学院, 北京 100083

基金项目: 国家自然科学基金(11372023,11402013)

详细信息

作者简介:
唐波男,硕士研究生。主要研究方向:气动弹性。Tel.:010-82338406 E-mail:tangbo23@126.com;吴志刚男,博士,副教授,硕士生导师。主要研究方向:气动弹性与主动控制,结构动力学。Tel.:010-82338723 E-mail:wuzhigang@buaa.edu.cn;杨超男,博士,教授,博士生导师。主要研究方向:气动弹性与主动控制,飞行器设计。Tel.:010-82338723 E-mail:yangchao@buaa.edu.cn;马成骥男,博士研究生。主要研究方向:气动弹性与主动控制。Tel.:010-82327539 E-mail:machengji@buaa.edu.cn

通讯作者:
吴志刚,Tel.:010-82338723 E-mail:wuzhigang@buaa.edu.cn

中图分类号: V211.47
计量
- 文章访问数: 835
- HTML全文浏览量: 60
- PDF下载量: 530
- 被引次数: 0
出版历程
- 收稿日期: 2015-05-26
- 网络出版日期: 2016-05-20

Aeroservoelastic unstability failure analysis in special wind tunnel test

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 在某带飞行控制系统的特种风洞试验中,试验模型在闭环大增益情况下出现了振动发散现象。为分析故障原因,对试验数据进行了频谱分析并检验了无风情况下伺服稳定性;同时,将风洞试验动力学系统简化为数学模型,并建立相应的运动微分方程进行分析,得到以下结论:加入支持结构后整个系统的弹性影响较大,并与控制及气动力发生耦合出现气动伺服弹性失稳。进一步针对以上简化模型,进行数值仿真,其结果验证了以上机理。为解决此失稳问题,对控制系统提出了2种改进方案:增加结构陷波器或更改操纵面偏转比例参数,2种方案亦得到仿真验证。最后,将增加结构陷波器的改进方案应用到试验中,达到了预期的效果。
- 风洞试验 /
- 控制系统 /
- 气动伺服弹性 /
- 振动发散 /
- 试验改进
Abstract: In an already completed wind tunnel test where a flight control system was applied, the vibration divergence of the test model under big closed-loop gain has drawn our attention. To find the mechanism of this failure, the frequency analysis of the test data has been done and the servo stabilization under no wind condition has been examined. Also, we built a simplified structural mechanic model according to the real situation and investigated the problem by analyzing the related differential equation of motion. The main cause for this failure has been found:the unexpected elastic effect after the involving of support system is significant and thus the coupling of elastic structure, control system and aerodynamic force gives rise to the aeroservoelastic instability. In addition, a numerical simulation has been done and verified the above mechanism. To solve this divergence problem, two improvements/solutions for the control system have been brought up:adding a structure filter in the feedback loop or changing the gain parameters of different control surfaces. Also, both the solutions have been verified by numerical simulation. The solution of adding a structure filter has been applied in the real wind tunnel test and expected effect has been achieved.
- wind tunnel test /
- control systems /
- aeroservoelastic /
- vibration divergence /
- test improvement

HTML全文

参考文献(15)

[1]	杨超,吴志刚,万志强,等.飞行器气动弹性原理[M].北京:北京航空航天大学出版社,2011:148-167. YANG C,WU Z G,WAN Z Q,et al.Principle of aircraft aeroelasticity[M].Beijing:Beihang University Press,2011:148-167(in Chinese).
[2]	杨超,吴志刚.导弹气动伺服弹性稳定性分析[J].飞行力学,2000,18(4):1-5. YANG C,WU Z G.Aeroservoelastic stability of missile[J].Flight Dynamics,2000,18(4):1-5(in Chinese).
[3]	FELT L R,HUTTSELL L J,NOLL T E,et al.Aeroservoelastic encounters[J].Journal of Aircraft,1979,16(7):477-483.
[4]	KARPEL M.Procedures and models for aeroservoelastic analysis and design[J].Journal of Applied Mathematic and Mechanics,2001,40(6):579-592.
[5]	KARPEL M,MOULIN B,IDAN M.Robust aeroservoelastic design with structural variations and modeling uncertainties[J].Journal of Aircraft,2003,40(5):946-954.
[6]	GUPTA T K,MEEK J L.Finite element multidisciplinary analysis[M].Reston:AIAA,2003:295-310.
[7]	REICHENBACH E,CASTELLUCCIO M,SEXTON B.Joined wing sensorcraft aeroservoelastic wind tunnel test program:AIAA-2011-1956[R].Reston:AIAA,2011.
[8]	PITT D M,HAYES W B,GOODMAN C E.F/A-18E/F aeroservoelastic design,analysis and test:AIAA-2003-1880[R].Reston:AIAA,2003.
[9]	REICHENBACH E,DAVIDSON R.Aeroservoelastic design and test of the X-45A unmanned combat air vehicle:AIAA-2003-1883[R].Reston:AIAA,2003.
[10]	章俊杰.飞机的气动伺服弹性横侧向风洞试验研究[J].北京航空航天大学学报,2003,29(2):120-123. ZHANG J J.Wind tunnel test for roll/lateral aeroservoelasticity of aircraft[J].Journal of Beijing University of Aeronautics and Astronautics,2003,29(2):120-123(in Chinese).
[11]	孟庆明.自动控制原理[M].北京:高等教育出版社,2008:67-68. MENG Q M.Principle of automatic control[M].Beijing:Higher Education Press,2008:67-68(in Chinese).
[12]	邢誉峰,李敏.工程振动基础[M].北京:北京航空航天大学出版社,2011:38-39. XING Y F,LI M.Basics of vibration engineering[M].Beijing:Beihang University Press,2011:38-39(in Chinese).
[13]	YAMASHIRO H,STIRLING R.Reduction of flight control system/structure mode interaction:AIAA-2007-6381[R].Reston:AIAA,2007.
[14]	楚龙飞,吴志刚,杨超,等.导弹自适应结构滤波器的设计与仿真[J].航空学报,2011,32(2):195-201. CHU L F,WU Z G,YANG C,et al.Dsign and simulation of adaptive structure filter for missiles[J].Acta Aeronautica et Astronautica Sinica,2011,32(2):195-201(in Chinese).
[15]	吴志刚,杨超.弹性导弹的连续与离散阵风响应[J].北京航空航天大学学报,2007,33(2):136-140. WU Z G,YANG C.Discrete and continuous gust response of elastic missile[J].Journal of Beijing University of Aeronautics and Astronautics,2007,33(2):136-140(in Chinese).