基于电磁干风洞的大柔性结构准模态试验研究
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摘要
结构的频率是结构的重要动力学特性,对于飞行器来说,当机翼等大型结构在非定常气动力作用下发生变形时,其频率也会发生变化。本文介绍了一种地面电磁干风洞试验方法,利用电磁场和安培力实现气动力的模拟,在不接触模型的情况下对模型进行静动态加载。基于这种新的试验技术,建立了一种地面电磁干风洞实验方法,利用电磁场和安培力实现气动力的模拟,可有效实现对模型结构的非接触式静态和动态气动力跟随加载。利用该实验系统,研究了静动态条件下,结构质量、刚度分布对飞机内载荷的影响;结构变形对结构动力学特征的影响。结果表明,结构的弯曲变形会影响结构的弯曲和扭转频率,结构的质量和刚度分布会对结构内载荷产生较大影响。这种新的试验方法有利于研究大柔性结构的气动弹性特性,对新型飞机的设计和研制具有重要意义。
The frequency of structures is an important dynamic characteristic.For aircrafts,when the wing and other large scale structures deform under the action of unsteady aerodynamic forces,its frequency correspondingly changes.For large structural flexible aircraft represented by high altitude long endurance UAVs,it is very important to explore the variation rules of the structural dynamic characteristics of the aircraft to develop the design technology and improve the design method.This paper introduces a test method of a ground electromagnetic dry wind tunnel.A principle experiment method of the ground electromagnetic dry wind tunnel is established.The electromagnetic field and Ampere force are used to realize the simulation of aerodynamics force,and the model is statically and dynamically loaded without touching the model.Based on this new test technique,a series of experiments were carried out by using the experimental system,and the influence of the structural quality and stiffness distribution was analyzed on the internal load of the aircraft under static and dynamic conditions.The results show that the bending deformation affects the bending and torsion frequencies of the structure,and the dynamic characteristics of the structure.This new test method is conducive to the study of aeroelastic characteristics of large flexible structures,and is of great significance for the design and development of new aircraft.
The frequency of structures is an important dynamic characteristic.For aircrafts,when the wing and other large scale structures deform under the action of unsteady aerodynamic forces,its frequency correspondingly changes.For large structural flexible aircraft represented by high altitude long endurance UAVs,it is very important to explore the variation rules of the structural dynamic characteristics of the aircraft to develop the design technology and improve the design method.This paper introduces a test method of a ground electromagnetic dry wind tunnel.A principle experiment method of the ground electromagnetic dry wind tunnel is established.The electromagnetic field and Ampere force are used to realize the simulation of aerodynamics force,and the model is statically and dynamically loaded without touching the model.Based on this new test technique,a series of experiments were carried out by using the experimental system,and the influence of the structural quality and stiffness distribution was analyzed on the internal load of the aircraft under static and dynamic conditions.The results show that the bending deformation affects the bending and torsion frequencies of the structure,and the dynamic characteristics of the structure.This new test method is conducive to the study of aeroelastic characteristics of large flexible structures,and is of great significance for the design and development of new aircraft.
引文
[1]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.CHEN G B,ZOU C Q,YANG C.Aeroelastic design basis[M].Beijing:Beijing University of Aeronautics and Astronautics Press,2004.(in Chinese)
[2]管德.气动弹性试验[M].北京:北京航空学院出版社,1986.GUAN D.Aeroelastic test[M].Beijing:Beijing Institute of Aeronautics Press,1986.(in Chinese)
[3]KEARNS J P.Flutter simulation[R].AD650981,1967.
[4]NARYZHNY A G,PEDORA A P,SMYSLOV V I.Vibration tests with airflow simulation in the aeroelastic investigations on dynamically scaled models[R].Uchenye Zapiski TsAGI,2001(XXXII):1-2.
[5]ZENG J,KINGSBURY D W,RITZ E,et al.GVT-based ground flutter test without wind tunnel[R].AIAA-2011-1942.
[6]WU Z G,CHU L F,YUAN R Z,et al.Studies on aeroservoelasticity semi-physical simulation test missiles[J].Science China Technological Sciences,2012,55(1):1-7.
[7]许云涛,吴志刚,杨超.地面颤振模拟试验中的非定常气动力模拟[J].航空学报,2012,33(11):1947-1957.XU Y T,WU Z G,YANG C.Unsteady aerodynamic simulation in ground flutter simulation test[J].Journal of Aeronautics,2012,33(11):1947-1957.(in Chinese)
[8]刘伯伟,王世斌.电磁脉冲撞击加载装置的研制及其应用[J].中国机械工程,1999,(12):1328-1329.LIU B W,WANG S B.Development and application of electromagnetic pulse impact loading device[J].China Mechanical Engineering,1999,(12):1328-1329.(in Chinese)
[9]周晓,刘军.电磁冲击加载平板线圈的有限元分析[J].机械科学与技术,2013,2:209-212.ZHOU X,LIU J.Finite element analysis of plate coil loaded by electromagnetic impulse[J].Mechanical Science and Technology,2013,2:209-212.(in Chinese)
[10]江春茂,陈雪原,潘金柱.磁阻尼器的研制及其在动导数实验中的应用[J].江汉大学学报(自然科学版),2010,38(1):40-42.JIANG C M,CHEN X Y,PAN J Z.Development of magnetic damper and its application in dynamic derivative experiment[J].Journal of Jianghan University(Natural Science Edition),2010,38(1):40-42.(in Chinese)
[11]侯英昱,刘子强,吕计男,等.一套气动力的电磁模拟试验装置[P].201410770623.7.2014.7.HOU Y Y,LIU Z Q,LU J M,et al.A set of aerodynamic electromagnetic simulation test device[P].201410770623.7.2014.7.(in Chinese)
[12]刘子强,侯英昱,付志超,等.一种干风洞气动弹性试验方法[P].201410770709.X.2014.7.LIU Z Q,HOU Y Y,FU Z C,et al.A dry wind tunnel aeroelastic test method[P].201410770709.X.2014.7.(in Chinese)
[13]侯英昱,付志超,等.气动力模拟非接触式加载方法研究[J].空气动力学学报,2018,36(2):357-361.HOU Y Y,FU Z C,et al.Research on aerodynamic simulation non-contact loading method[J].Acta Aerodynamic Sinica,2018,36(2):357-361.(in Chinese)
[14]陈帅,杨智春,李斌.结构试验中均布载荷的气囊加载系统设计方法[J].工程力学,2012,29(6):146-450.CHEN S,YANG Z C,LI B.Design method of balloon loading system with uniform load in structural test[J].Engineering Mechanics,2012,29(6):146-450.(in Chinese)
[15]张新蠺,吴志刚,杨超.大变形状态机翼振动试验与气动弹性分析[J].航空工程进展,2010,1(1):76-79.ZHANG X H,WU Z G,YANG C.Vibration test and aeroelastic analysis of wing under large deformation[J].Aviation Engineering Progress,2010,1(1):76-79.(in Chinese)
[2]管德.气动弹性试验[M].北京:北京航空学院出版社,1986.GUAN D.Aeroelastic test[M].Beijing:Beijing Institute of Aeronautics Press,1986.(in Chinese)
[3]KEARNS J P.Flutter simulation[R].AD650981,1967.
[4]NARYZHNY A G,PEDORA A P,SMYSLOV V I.Vibration tests with airflow simulation in the aeroelastic investigations on dynamically scaled models[R].Uchenye Zapiski TsAGI,2001(XXXII):1-2.
[5]ZENG J,KINGSBURY D W,RITZ E,et al.GVT-based ground flutter test without wind tunnel[R].AIAA-2011-1942.
[6]WU Z G,CHU L F,YUAN R Z,et al.Studies on aeroservoelasticity semi-physical simulation test missiles[J].Science China Technological Sciences,2012,55(1):1-7.
[7]许云涛,吴志刚,杨超.地面颤振模拟试验中的非定常气动力模拟[J].航空学报,2012,33(11):1947-1957.XU Y T,WU Z G,YANG C.Unsteady aerodynamic simulation in ground flutter simulation test[J].Journal of Aeronautics,2012,33(11):1947-1957.(in Chinese)
[8]刘伯伟,王世斌.电磁脉冲撞击加载装置的研制及其应用[J].中国机械工程,1999,(12):1328-1329.LIU B W,WANG S B.Development and application of electromagnetic pulse impact loading device[J].China Mechanical Engineering,1999,(12):1328-1329.(in Chinese)
[9]周晓,刘军.电磁冲击加载平板线圈的有限元分析[J].机械科学与技术,2013,2:209-212.ZHOU X,LIU J.Finite element analysis of plate coil loaded by electromagnetic impulse[J].Mechanical Science and Technology,2013,2:209-212.(in Chinese)
[10]江春茂,陈雪原,潘金柱.磁阻尼器的研制及其在动导数实验中的应用[J].江汉大学学报(自然科学版),2010,38(1):40-42.JIANG C M,CHEN X Y,PAN J Z.Development of magnetic damper and its application in dynamic derivative experiment[J].Journal of Jianghan University(Natural Science Edition),2010,38(1):40-42.(in Chinese)
[11]侯英昱,刘子强,吕计男,等.一套气动力的电磁模拟试验装置[P].201410770623.7.2014.7.HOU Y Y,LIU Z Q,LU J M,et al.A set of aerodynamic electromagnetic simulation test device[P].201410770623.7.2014.7.(in Chinese)
[12]刘子强,侯英昱,付志超,等.一种干风洞气动弹性试验方法[P].201410770709.X.2014.7.LIU Z Q,HOU Y Y,FU Z C,et al.A dry wind tunnel aeroelastic test method[P].201410770709.X.2014.7.(in Chinese)
[13]侯英昱,付志超,等.气动力模拟非接触式加载方法研究[J].空气动力学学报,2018,36(2):357-361.HOU Y Y,FU Z C,et al.Research on aerodynamic simulation non-contact loading method[J].Acta Aerodynamic Sinica,2018,36(2):357-361.(in Chinese)
[14]陈帅,杨智春,李斌.结构试验中均布载荷的气囊加载系统设计方法[J].工程力学,2012,29(6):146-450.CHEN S,YANG Z C,LI B.Design method of balloon loading system with uniform load in structural test[J].Engineering Mechanics,2012,29(6):146-450.(in Chinese)
[15]张新蠺,吴志刚,杨超.大变形状态机翼振动试验与气动弹性分析[J].航空工程进展,2010,1(1):76-79.ZHANG X H,WU Z G,YANG C.Vibration test and aeroelastic analysis of wing under large deformation[J].Aviation Engineering Progress,2010,1(1):76-79.(in Chinese)