CN115266001A - A two-degree-of-freedom aeroelasticity experimental device - Google Patents

A two-degree-of-freedom aeroelasticity experimental device Download PDF

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CN115266001A
CN115266001A CN202210807650.1A CN202210807650A CN115266001A CN 115266001 A CN115266001 A CN 115266001A CN 202210807650 A CN202210807650 A CN 202210807650A CN 115266001 A CN115266001 A CN 115266001A
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linear
wind tunnel
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floating
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高志鹰
赵保仲
汪建文
东雪青
马剑龙
温彩凤
白叶飞
张立茹
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Inner Mongolia University of Technology
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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/02Wind tunnels
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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64FGROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/06Measuring arrangements specially adapted for aerodynamic testing
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00Aerodynamic testing; Arrangements in or on wind tunnels
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Abstract

本发明涉及大型风力机叶片以及航空机翼风洞试验领域,具体涉及一种两自由度的气动弹性实验装置,包括风洞实验模型、两自由度支撑机构,信号采集系统;风洞实验模型包括翼段模型、测压管、端板、中心扭转轴、锁紧机构和质心调节机构;两自由度支撑机构包括风洞固定板、风洞抗扰流罩、支撑板、线性托架、角位移传感器固定法兰、扭转轴固定杆、扭转支杆、光滑线性直杆、沉浮弹性机构、俯仰线性弹簧、俯仰弹簧连接柱、直线滑动轴承、外球面轴承、沉浮限位装置和俯仰限位装置。本发明可用于研究风洞实验模型在俯仰、沉浮两自由度支撑条件下的气动弹性特性,即在进行气动弹性试验时探究翼段表面流动分离以及动态失速、颤振等现象的实验装置。

Figure 202210807650

The invention relates to the field of wind tunnel testing of large-scale wind turbine blades and aviation wings, in particular to a two-degree-of-freedom aeroelasticity experimental device, comprising a wind-tunnel experimental model, a two-degree-of-freedom support mechanism, and a signal acquisition system; the wind tunnel experimental model includes Wing segment model, pressure measuring tube, end plate, central torsion axis, locking mechanism and center of mass adjustment mechanism; two-degree-of-freedom support mechanism includes wind tunnel fixing plate, wind tunnel anti-turbulence cover, support plate, linear bracket, angular displacement Sensor fixing flange, torsion shaft fixing rod, torsion support rod, smooth linear straight rod, ups and downs elastic mechanism, pitching linear spring, pitching spring connecting column, linear sliding bearing, outer spherical bearing, ups and downs limit device and pitch limit device. The invention can be used to study the aeroelastic characteristics of the wind tunnel experimental model under the support conditions of pitch and ups and downs, that is, an experimental device for exploring the surface flow separation, dynamic stall, flutter and other phenomena of the wing section during the aeroelastic test.

Figure 202210807650

Description

一种两自由度的气动弹性实验装置A two-degree-of-freedom aeroelasticity experimental device

技术领域technical field

本发明涉及大型风力机叶片以及航空机翼风洞试验领域,具体涉及一种两自由度的气动弹性实验装置。The invention relates to the field of wind tunnel testing of large wind turbine blades and aviation wings, in particular to a two-degree-of-freedom aeroelasticity experimental device.

背景技术Background technique

目前风力机叶片逐渐向大型化,柔性化的方向发展,高展弦比的叶片随即应用而生,此外飞机机翼也拥有较高的展弦比。这些高展弦比叶片及机翼会面临非线性气动弹性所引发的诸多问题,例如颤振现象。At present, wind turbine blades are gradually developing in the direction of large size and flexibility, and blades with high aspect ratios are applied immediately. In addition, aircraft wings also have high aspect ratios. These high-aspect-ratio blades and wings face many problems caused by nonlinear aeroelasticity, such as flutter phenomena.

以风力机叶片的颤振试验为例,影响叶片颤振的因素有很多,主要包括风轮叶片的结构动力参数、来流特性和风轮叶片所受的气动力。在试验中,往往涉及翼段两个自由度的运动,此外在颤振发生时翼段的表面还会出现流动分离现象。从结构疲劳的角度来看,预测与颤振相关的俯仰和沉浮的振动频率和振动幅值是一项主要的工程任务。所以在风洞试验中利用两自由度的气动弹性实验装置探究叶片的流固耦合力学特性变得十分必要。Taking the flutter test of wind turbine blades as an example, there are many factors that affect the flutter of the blades, mainly including the structural dynamic parameters of the rotor blades, the characteristics of incoming flow and the aerodynamic force on the rotor blades. In the test, the movement of two degrees of freedom of the airfoil is often involved. In addition, when the flutter occurs, the surface of the airfoil will also appear flow separation. From a structural fatigue point of view, predicting the vibration frequencies and amplitudes of pitching and heaving associated with flutter is a major engineering task. Therefore, it is very necessary to use a two-degree-of-freedom aeroelastic experimental device to explore the mechanical characteristics of the fluid-solid interaction of the blade in the wind tunnel test.

目前在试验中使用到的气动弹性模型均为固定质心的翼段模型,并且对翼段表面气动特性的测量是通过在翼型表面布置的若干微型压力传感器来实现的。但这种模型局限于单一质心位置,而且翼段表面的微型压力传感器布置较为复杂,压力传感器在翼段表面的突起部分还会对翼段附近的气动特性造成一定的影响。The aeroelastic models currently used in the test are all airfoil models with a fixed center of mass, and the measurement of the aerodynamic characteristics of the airfoil surface is realized by a number of miniature pressure sensors arranged on the airfoil surface. However, this model is limited to a single centroid position, and the arrangement of micro pressure sensors on the surface of the wing section is relatively complicated, and the protruding part of the pressure sensor on the surface of the wing section will also have a certain impact on the aerodynamic characteristics near the wing section.

此外,目前在试验中所设计的气动弹性模型需要将装置整体放置在风洞内,这样不但会增加风洞的阻塞效应,更重要的是还会由于支撑机构暴露于风洞中进而对翼段的整体气动特性造成影响。In addition, the aeroelastic model currently designed in the test needs to place the device as a whole in the wind tunnel, which will not only increase the blocking effect of the wind tunnel, but more importantly, will cause damage to the airfoil due to the exposure of the support mechanism to the wind tunnel. affect the overall aerodynamic characteristics.

发明内容Contents of the invention

为解决上述问题,本发明提供了一种两自由度的气动弹性实验装置,可用于研究风洞实验模型在俯仰、沉浮两自由度支撑条件下的气动弹性特性,即在进行气动弹性试验时探究翼段表面流动分离以及动态失速、颤振等现象的实验装置。In order to solve the above problems, the present invention provides a two-degree-of-freedom aeroelastic experimental device, which can be used to study the aeroelastic characteristics of the wind tunnel experimental model under the two-degree-of-freedom support conditions of pitch and ups and downs, that is, to explore when performing aeroelasticity tests. Experimental device for flow separation on the surface of wing section and phenomena such as dynamic stall and flutter.

为实现上述目的,本发明采取的技术方案为:In order to achieve the above object, the technical scheme that the present invention takes is:

一种两自由度的气动弹性实验装置,包括风洞实验模型、两自由度支撑机构、信号采集系统;A two-degree-of-freedom aeroelasticity experimental device, including a wind tunnel experimental model, a two-degree-of-freedom support mechanism, and a signal acquisition system;

所述的风洞实验模型包括一个翼段模型,16~28个测压管,两块端板,一套中心扭转轴,一套锁紧机构,一套质心调节机构;The wind tunnel experiment model includes a wing section model, 16-28 piezometric tubes, two end plates, a set of central torsion shafts, a set of locking mechanisms, and a set of center-of-mass adjustment mechanisms;

所述的翼段模型经3D打印制造所得,翼段模型内部设计有放置螺栓的通孔,在翼段模型跨中位置处的上下表面分别设计有直径为1.6mm的8~14个测压孔,8~14个测压孔均沿翼型表面的法线方向,测压孔通过翼段模型内部设计的空气流道与测压管连接,测压管延伸至风洞外,与压力变送器进行连接;The wing section model is manufactured by 3D printing. There are through holes for placing bolts inside the wing section model, and 8 to 14 pressure measuring holes with a diameter of 1.6mm are designed on the upper and lower surfaces of the wing section model at the mid-span position. , 8 to 14 pressure measuring holes are all along the normal direction of the airfoil surface. The pressure measuring holes are connected to the pressure measuring tube through the air channel designed inside the airfoil model, and the pressure measuring tube extends outside the wind tunnel to connect with the pressure transmitter. device to connect;

所述的两块端板经3D打印制造所得,其含有与翼段模型截面镂空形状相同的镂空设计,通过锁紧机构连接在翼段模型两端,以防止翼段的端部效应,确保流动为准二维流动;The two end plates are manufactured by 3D printing, which have the same hollow design as the cross section of the wing section model, and are connected to both ends of the wing section model through a locking mechanism to prevent the end effect of the wing section and ensure the flow is a quasi-two-dimensional flow;

所述的一套中心扭转轴包括一个高强度扭转轴螺栓和一个扭转轴防松螺母以及一个防滑片,高强度扭转轴螺栓穿过防滑片、两块端板以及翼段模型内部预留的放置螺栓的通孔与两自由度支撑机构上的扭转轴固定杆相连接,并用扭转轴防松螺母进行固定,其中防滑片的一部分嵌入到远离支撑机构一侧的端板中,并与高强度扭转轴螺栓的头部固定连接,以防止中心扭转轴与翼段模型之间发生相对滑动;The set of central torsion shaft includes a high-strength torsion shaft bolt, a torsion shaft locknut and an anti-slip sheet, and the high-strength torsion shaft bolt passes through the anti-slip sheet, two end plates and the reserved space inside the wing model The through hole of the bolt is connected with the torsion shaft fixing rod on the two-degree-of-freedom support mechanism, and is fixed with the torsion shaft locknut, wherein a part of the anti-slip sheet is embedded in the end plate on the side away from the support mechanism, and is connected with the high-strength torsion The head of the shaft bolt is fixedly connected to prevent relative sliding between the central torsion shaft and the wing model;

所述的一套锁紧机构位于翼段模型靠近后缘的位置,包括固定螺栓以及防松螺母,固定螺栓通过端板以及翼段模型内部预留的放置螺栓的通孔将翼段模型和两个端板连接在一起,并用防松螺母进行固定;The set of locking mechanisms is located near the trailing edge of the wing section model, and includes fixing bolts and locknuts. The fixing bolts connect the wing section model and the two bolts through the end plate and the through holes reserved inside the wing section model for placing bolts. The two end plates are connected together and fixed with locknuts;

所述的一套质心调节机构包括两个常规质量块、两个偏心质量块和一套质量块固定机构;两个常规质量块为黄铜材质,中心打孔,两个偏心质量块为黄铜材质,偏心打孔,偏心质量块与常规质量块的重量相同;两个常规质量块组合使用,用于调节翼段模型质心位置,使其更靠近扭转轴中心,使翼段模型从前缘到后缘形成气动力心-扭转轴中心(重心)的三心相对位置关系;两个偏心质量块组合使用,用于调节翼段模型质心位置,使其更靠近翼段模型前缘,使翼段模型从前缘到后缘形成气动力心-重心-扭转轴中心的三心相对位置关系;一个常规质量块与一个偏心质量块组合使用,用于调节翼段模型质心位置,使其更靠近翼段模型后缘,使翼段模型从前缘到后缘形成气动力心-扭转轴中心-重心的三心相对位置关系;一套质量块固定机构由质量块固定螺栓和质量块防松螺母构成,通过根据试验中对不同质心位置的需求,利用质量块固定螺栓和质量块防松螺母将两个质量块分别固定在翼段模型两侧的端板上,从而实现翼段模型质心位置的改变;The set of center-of-mass adjustment mechanism includes two conventional mass blocks, two eccentric mass blocks and a set of mass block fixing mechanism; the two conventional mass blocks are made of brass, with a hole in the center, and the two eccentric mass blocks are made of brass Material, eccentric drilling, the weight of the eccentric mass is the same as that of the conventional mass; the combination of two conventional masses is used to adjust the position of the center of mass of the wing section model, making it closer to the center of the torsion axis, so that the wing section model is from the leading edge to the rear The three-center relative position relationship between the aerodynamic center and the torsion axis center (center of gravity) is formed by the edge; two eccentric mass blocks are used in combination to adjust the position of the center of mass of the wing section model, making it closer to the leading edge of the wing section model, so that the wing section model From the leading edge to the trailing edge, a three-center relative position relationship of aerodynamic center-center of gravity-torsion axis center is formed; a conventional mass block and an eccentric mass block are used in combination to adjust the position of the center of mass of the wing section model to make it closer to the wing section model trailing edge, so that the airfoil model forms a three-center relative position relationship of aerodynamic center-torsion axis center-center of gravity from the leading edge to the trailing edge; a set of mass block fixing mechanism is composed of mass block fixing bolts and mass block locknuts. To meet the requirements of different centroid positions in the test, use the mass block fixing bolts and mass block locknuts to fix the two mass blocks on the end plates on both sides of the wing section model, so as to realize the change of the position of the wing section model's center of mass;

所述的两自由度支撑机构包括风洞固定板、风洞抗扰流罩、两块支撑板、两个线性托架、一个角位移传感器固定法兰、一根扭转轴固定杆、两根扭转支杆、四根光滑线性直杆、四组沉浮弹性机构、四组俯仰线性弹簧、八个俯仰弹簧连接柱、八个直线滑动轴承、两个外球面轴承、四套沉浮限位装置和八套俯仰限位装置;The two-degree-of-freedom support mechanism includes a wind tunnel fixing plate, a wind tunnel anti-turbulence cover, two supporting plates, two linear brackets, a fixing flange for an angular displacement sensor, a torsion shaft fixing rod, two torsion Support rods, four smooth linear straight rods, four sets of sinking and floating elastic mechanisms, four sets of pitching linear springs, eight pitching spring connecting columns, eight linear sliding bearings, two outer spherical bearings, four sets of sinking and floating limit devices and eight sets of Pitch limit device;

所述信号采集系统包括16~28个压力变送器、一个角位移传感器,一个非接触式磁滞伸缩位移传感器和一套多通道数据采集分析系统,16~28个压力变送器的压力测量端分别与从风洞中引出的测压管连接,另一端通过应变信号输入线分别连接在多通道数据采集仪的信号采集通道上,角位移传感器固定在角位移传感器固定法兰上,进而与扭转轴固定杆的配套轴孔进行连接,角位移传感器的信号输出端通过应变信号输入线连接在多通道数据采集仪的信号采集通道上,用于采集风洞实验模型的瞬时俯仰角信号,非接触式磁滞伸缩位移传感器连接在风洞固定板上,其与固定在线性托架上浮动磁铁的距离为2mm;通过风洞实验模型的上下运动带动线性托架的线性运动进而带动浮动磁铁的线性运动,通过浮动磁铁在非接触式磁滞伸缩位移传感器的测杆上滑动的距离进而测量出风洞实验模型的瞬时沉浮位移。非接触式磁滞伸缩位移传感器的信号输出端通过应变信号输入线连接在多通道数据采集仪的信号采集通道上,用于采集风洞实验模型的瞬时沉浮位移信号。The signal acquisition system includes 16 to 28 pressure transmitters, an angular displacement sensor, a non-contact magnetic hysteresis displacement sensor and a set of multi-channel data acquisition and analysis system, the pressure measurement of 16 to 28 pressure transmitters One end is respectively connected with the pressure measuring tube drawn from the wind tunnel, and the other end is respectively connected to the signal acquisition channel of the multi-channel data acquisition instrument through the strain signal input line, and the angular displacement sensor is fixed on the fixed flange of the angular displacement sensor, and then connected with the The supporting shaft hole of the torsion shaft fixed rod is connected, and the signal output end of the angular displacement sensor is connected to the signal acquisition channel of the multi-channel data acquisition instrument through the strain signal input line, which is used to acquire the instantaneous pitch angle signal of the wind tunnel experimental model, which is not The contact type hysteresis stretching displacement sensor is connected to the fixed plate of the wind tunnel, and the distance between it and the floating magnet fixed on the linear bracket is 2mm; the up and down movement of the wind tunnel test model drives the linear movement of the linear bracket and then drives the floating magnet. Linear movement, through the sliding distance of the floating magnet on the measuring rod of the non-contact magneto-hysteretic displacement sensor, and then measure the instantaneous ups and downs displacement of the wind tunnel experimental model. The signal output end of the non-contact hysteresis stretching displacement sensor is connected to the signal acquisition channel of the multi-channel data acquisition instrument through the strain signal input line, and is used to acquire the instantaneous ups and downs displacement signals of the wind tunnel experimental model.

作为本方案的进一步地设计,八套俯仰限位装置用于限定风洞实验模型在俯仰运动过程中出现的大位移现象,以防止过大的俯仰位移对两自由度支撑机构以及传感器系统的损坏;每套俯仰限位装置均由一个俯仰限位装置金属固定片、四个俯仰限位装置金属固定片连接螺栓、一个俯仰限位装置橡胶制动块以及两个俯仰限位装置沉头连接螺栓和两个俯仰限位装置沉头连接螺栓配套螺母所构成,其中,八个俯仰限位装置金属固定片分别通过三十二个俯仰限位装置金属固定片连接螺栓固定在两个线性托架上,然后十六个俯仰限位装置沉头连接螺栓分别穿过八个俯仰限位装置橡胶制动块,通过十六个俯仰限位装置沉头连接螺栓配套螺母固定在八个俯仰限位装置金属固定片上As a further design of this scheme, eight sets of pitch limit devices are used to limit the large displacement of the wind tunnel experimental model during the pitch movement, so as to prevent excessive pitch displacement from damage to the two-degree-of-freedom support mechanism and sensor system ;Each set of pitch limit device consists of a pitch limit device metal fixing plate, four pitch limit device metal fixing plate connecting bolts, a pitch limit device rubber brake block and two pitch limit device countersunk connecting bolts It is composed of two pitch limit device countersunk head connecting bolts and matching nuts, among which, the eight pitch limit device metal fixing pieces are respectively fixed on two linear brackets through thirty-two pitch limit device metal fixing piece connecting bolts , and then the sixteen countersunk head connecting bolts of the pitch limit device pass through the rubber brake blocks of the eight pitch limit devices respectively, and are fixed on the eight pitch limit device metal On the fixed piece

作为本方案的进一步地设计,所述的翼段模型内部的空气流道的入口端与测压孔光滑连接,空气流道的出口端位于设有支撑机构一侧的翼段模型的端部,然后通过在翼段模型端部的空气流道出口端穿入测压管,进而将翼段模型表面的压力引出到位于风洞外部的压力变送器上。测压孔及空气流道均利用建模软件进行了高精度的设计,同时,3D打印技术也保证了实体翼段模型的加工精度。As a further design of this scheme, the inlet end of the air channel inside the wing model is smoothly connected to the pressure measuring hole, and the outlet end of the air channel is located at the end of the wing model on the side where the support mechanism is provided. Then, the pressure on the surface of the airfoil model is led out to the pressure transmitter outside the wind tunnel by piercing the pressure measuring tube at the outlet end of the air channel at the end of the wing model. The pressure measuring holes and air flow channels are all designed with high precision using modeling software. At the same time, 3D printing technology also ensures the processing accuracy of the solid wing model.

作为本方案的进一步地设计,所述的测压管通过一端与翼段模型内部的空气流道连接,并在接口处用密封胶进行密封,另一端与风洞外部的压力变送器的测压端进行连接,实现了对翼段模型表面压力的测量。As a further design of this scheme, the pressure measuring tube is connected to the air channel inside the wing section model through one end, and is sealed with a sealant at the interface, and the other end is connected to the measuring tube of the pressure transmitter outside the wind tunnel. The pressure end is connected to realize the measurement of the surface pressure of the airfoil model.

作为本方案的进一步地设计,偏心质量块与端板的接触位置,均设置有防滑凹槽,以防止偏心质量块在翼段模型运动过程中与端板发生相对滑动。As a further design of this solution, the contact position between the eccentric mass and the end plate is provided with anti-slip grooves to prevent the eccentric mass from sliding relative to the end plate during the movement of the wing model.

作为本方案的进一步地设计,所述的风洞固定板用于固定两块支撑板、风洞抗扰流罩以及非接触式磁滞伸缩位移传感器,并通过风洞固定板固定螺栓将风洞固定板固定在风洞闭口段的侧壁上;风洞抗扰流罩通过风洞固定板固定螺栓固定在风洞固定板上,其将风洞外部的两自由度支撑机构罩在风洞抗扰流罩内部,用于防止风洞侧壁开口对风洞内部气流的影响;两块支撑板包括上支撑板和下支撑板,分别通过支撑板固定螺栓固定在风洞固定板上,上支撑板和下支撑板上均设置有固定沉浮限位装置的螺栓孔以及用于固定沉浮弹性机构的凹槽,且上支撑板上还设置有连接光滑线性直杆的螺栓孔,下支撑板的两个面上分别设置有连接光滑线性直杆的沉头螺栓孔和圆柱凹槽。As a further design of this program, the wind tunnel fixing plate is used to fix two support plates, the wind tunnel anti-turbulence cover and the non-contact hysteresis telescopic displacement sensor, and the wind tunnel is fixed by the wind tunnel fixing plate fixing bolts. The fixed plate is fixed on the side wall of the closed section of the wind tunnel; the anti-turbulence cover of the wind tunnel is fixed on the fixed plate of the wind tunnel through the fixing bolts of the fixed plate of the wind tunnel, which covers the two-degree-of-freedom support mechanism outside the wind tunnel Inside the spoiler, it is used to prevent the wind tunnel side wall opening from affecting the air flow inside the wind tunnel; the two support plates include the upper support plate and the lower support plate, which are respectively fixed on the wind tunnel fixing plate by the support plate fixing bolts, and the upper support plate Both the plate and the lower support plate are provided with bolt holes for fixing the ups and downs limit device and grooves for fixing the ups and downs elastic mechanism, and the upper support plate is also provided with bolt holes for connecting smooth linear straight rods, and the two sides of the lower support plate Countersunk bolt holes and cylindrical grooves for connecting smooth linear straight rods are respectively arranged on one surface.

作为本方案的进一步地设计,所述的两个线性托架包括内侧线性托架和外侧线性托架,两个线性托架均设置有用于贯穿光滑线性直杆和扭转轴固定杆的通孔以及用于固定外球面轴承、直线滑动轴承和沉浮弹性机构的凹槽,此外还有用于固定俯仰弹簧连接柱和俯仰限位装置的螺栓孔,且外侧线性托架上还设置有用于固定角位移传感器固定法兰的螺栓孔;八个直线滑动轴承和八个沉浮线性弹簧固定座通过沉浮弹性机构固定螺栓固定在线性托架上设置的凹槽内,两个线性托架分别通过四组沉浮弹性机构悬挂在上支撑板和下支撑板之间;两个线性托架的中部分别设置有一个外球面轴承,扭转轴固定杆通过外球面轴承与线性托架相连接,在两个线性托架上分别通过四组俯仰线性弹簧,将八个俯仰弹簧连接柱与两个扭转支杆相连接,以提供风洞实验模型的俯仰恢复力矩,且内侧线性托架的侧边还安装有与非接触式磁滞伸缩位移传感器配套使用的浮动磁铁,以便实时采集风洞实验模型的沉浮运动数据。As a further design of this solution, the two linear brackets include an inner linear bracket and an outer linear bracket, and the two linear brackets are provided with through holes for passing through the smooth linear straight rod and the torsion shaft fixing rod and Grooves for fixing outer spherical bearings, linear sliding bearings, and ups and downs elastic mechanisms, as well as bolt holes for fixing pitch spring connecting columns and pitch limit devices, and the outer linear bracket is also provided with a fixed angular displacement sensor Bolt holes for fixing the flange; eight linear sliding bearings and eight sinking and floating linear spring fixing seats are fixed in the grooves set on the linear bracket through the fixing bolts of the sinking and floating elastic mechanism, and the two linear brackets are respectively passed through four sets of sinking and floating elastic mechanisms Suspended between the upper support plate and the lower support plate; the middle parts of the two linear brackets are respectively provided with an outer spherical bearing, and the torsion shaft fixing rod is connected with the linear bracket through the outer spherical bearing, and the two linear brackets are respectively Through four sets of pitch linear springs, the eight pitch spring connecting columns are connected with two torsion struts to provide the pitch restoring moment of the wind tunnel experimental model, and the side of the inner linear bracket is also installed with a non-contact magnetic The floating magnet used in conjunction with the hysteresis telescopic displacement sensor is used to collect the ups and downs motion data of the wind tunnel experimental model in real time.

作为本方案的进一步地设计,所述的角位移传感器固定法兰固定在外侧线性托架上,其通过将角位移传感器与线性托架以及扭转轴固定杆固定在一起,进而实现在风洞实验模型做沉浮运动的同时可以测量风洞实验模型的俯仰运动;扭转轴固定杆的一端设置有扭转轴固定夹具,另一端设置有与角位移传感器配套的连接口,其通过两个外球面轴承分别与两个线性托架连接;扭转支杆竖直穿过扭转轴固定杆,并通过扭转支杆固定螺栓将其固定在扭转轴固定杆上,分别通过四组俯仰线性弹簧将两个扭转支杆和八个俯仰弹簧连接柱连接起来。用于将风洞实验模型的俯仰运动转化为俯仰线性弹簧的线性运动;四根光滑线性直杆的一端设置有螺纹另一端设置有螺栓孔,四根光滑线性直杆分别穿过四组沉浮弹性机构、八个直线滑动轴承和内外两个线性托架连接于上下两个支撑板上;四组沉浮弹性机构包括八个沉浮线性弹簧、十六个沉浮线性弹簧固定座,六十四个U型螺栓以及六十四个U型螺栓配套螺母。其中每个沉浮弹性机构均通过八个U型螺栓以及八个U型螺栓配套螺母将一个沉浮线性弹簧的两端分别固定在两个沉浮线性弹簧固定座上。四组沉浮弹性机构中的8个沉浮线性弹簧均采用预加载的拉伸弹簧。沉浮弹性机构的一端通过沉浮弹性机构固定螺栓连接在支撑板上,另一端通过沉浮弹性机构固定螺栓连接在线性托架上,并以上下两个沉浮弹性机构为一组的方式,通过两组沉浮弹性机构悬挂一个线性托架,进而将线性托架以及与线性托架连接的风洞实验模型悬挂在上下两个支撑板之间,从而在风洞实验模型受到风洞中气流的作用力而进行上下方向的沉浮运动时,为风洞实验模型在沉浮运动中提供恢复力。四组俯仰线性弹簧采用预加载的拉伸弹簧,以线性托架一侧位于扭转支杆两边的两个俯仰线性弹簧为一组,通过一端固定在俯仰弹簧连接柱上,另一端固定在穿过扭转轴固定杆的扭转支杆上的方式来为风洞实验模型在俯仰运动中提供扭转恢复力矩,八个俯仰弹簧连接柱通过螺纹连接,固定在两个线性托架上,用来固定四组俯仰线性弹簧;八个直线滑动轴承分别与四组沉浮弹性机构一端的沉浮线性弹簧固定座相连接,通过利用沉浮弹性机构固定螺栓将沉浮弹性机构一端连接有直线滑动轴承的沉浮线性弹簧固定座固定在内外两个线性托架上设置的凹槽内,从而实现了直线滑动轴承与线性托架的固定连接,八个直线滑动轴承分别固定在光滑线性直杆与线性托架连接处的凹槽内,以减小风洞实验模型在沉浮运动过程中的摩擦力;两个外球面轴承分别固定在扭转轴固定杆与线性托架的连接处,以减小风洞实验模型在俯仰运动过程中的摩擦力;四套沉浮限位装置用于限定风洞实验模型在沉浮运动过程中出现的大位移现象,以防止过大的沉浮位移对两自由度支撑机构以及传感器系统的损坏。每套沉浮限位装置均由两个沉浮限位装置金属支撑柱、一个沉浮限位装置金属垫片、一个沉浮限位装置橡胶制动块以及两个沉浮限位装置沉头连接螺栓构成;其中,沉浮限位装置金属支撑柱的一端设置有螺纹,另一端设置有螺栓孔,八个沉浮限位装置金属支撑柱分别连接在上下两块支撑板上,然后八个沉浮限位装置沉头连接螺栓分别穿过四个沉浮限位装置橡胶制动块以及四个沉浮限位装置金属垫片连接在八个沉浮限位装置金属支撑柱一侧的螺栓孔内。As a further design of this scheme, the angular displacement sensor fixing flange is fixed on the outer linear bracket, and it is achieved by fixing the angular displacement sensor, the linear bracket and the torsion shaft fixing rod together to realize the The pitching motion of the wind tunnel experimental model can be measured while the model is doing ups and downs; one end of the torsion shaft fixing rod is provided with a torsion shaft fixing fixture, and the other end is provided with a connection port matched with an angular displacement sensor, which passes through two outer spherical bearings respectively. It is connected with two linear brackets; the torsion strut passes through the torsion shaft fixing rod vertically, and is fixed on the torsion shaft fixing rod by the torsion strut fixing bolt, and the two torsion struts are respectively connected by four sets of pitch linear springs. Connect with eight pitch spring connecting columns. It is used to convert the pitching motion of the wind tunnel experimental model into the linear motion of the pitching linear spring; one end of the four smooth linear straight rods is provided with a thread and the other end is provided with a bolt hole, and the four smooth linear straight rods pass through four sets of ups and downs elastic springs respectively. The mechanism, eight linear sliding bearings and two linear brackets inside and outside are connected to the upper and lower support plates; four sets of ups and downs elastic mechanisms include eight ups and downs linear springs, sixteen ups and downs linear spring fixing seats, and sixty-four U-shaped Bolts and sixty-four U-shaped bolts supporting nuts. Each ups and downs elastic mechanism fixes the two ends of one ups and downs linear spring respectively on two ups and downs linear spring fixing seats through eight U-shaped bolts and eight supporting nuts of U-shaped bolts. The eight ups and downs linear springs in the four sets of ups and downs elastic mechanisms all adopt preloaded tension springs. One end of the up and down elastic mechanism is connected to the support plate through the fixing bolt of the up and down elastic mechanism, and the other end is connected to the linear bracket through the fixing bolt of the up and down elastic mechanism. The elastic mechanism suspends a linear bracket, and then suspends the linear bracket and the wind tunnel test model connected with the linear bracket between the upper and lower support plates, so that the wind tunnel test model is subjected to the force of the airflow in the wind tunnel During the up-and-down movement, it provides the restoring force for the wind tunnel experimental model in the up-and-down movement. The four sets of pitch linear springs are preloaded tension springs, and the two pitch linear springs on one side of the linear bracket are located on both sides of the torsion strut as a group. One end is fixed on the pitch spring connecting column, and the other end is fixed on the through The torsional support of the torsion axis fixed rod is used to provide the torsional restoring moment for the wind tunnel experimental model during the pitching movement. The eight pitching spring connecting columns are connected by threads and fixed on two linear brackets to fix four sets of Pitching linear spring; eight linear sliding bearings are respectively connected with four sets of sinking and floating linear spring fixing seats at one end of the sinking and floating elastic mechanism, and the sinking and floating linear spring fixing seat connected with the linear sliding bearing at one end of the sinking and floating elastic mechanism is fixed by using the fixing bolt of the sinking and floating elastic mechanism In the grooves set on the inner and outer linear brackets, the fixed connection between the linear sliding bearing and the linear bracket is realized, and the eight linear sliding bearings are respectively fixed in the grooves at the connection between the smooth linear straight rod and the linear bracket , to reduce the friction of the wind tunnel test model during the ups and downs; two outer spherical bearings are respectively fixed at the connection between the torsion axis fixed rod and the linear bracket to reduce the friction of the wind tunnel test model during the pitching movement. Friction; four sets of sinking and floating limit devices are used to limit the large displacement of the wind tunnel experimental model during the sinking and floating movement, so as to prevent excessive sinking and floating displacement from damage to the two-degree-of-freedom support mechanism and sensor system. Each set of ups and downs limit device consists of two metal support columns for the ups and downs limit device, a metal gasket for the ups and downs limit device, a rubber brake block for the ups and downs limit device and two countersunk head connecting bolts for the ups and downs limit device; , One end of the metal support column of the sinking and floating limit device is provided with a thread, and the other end is provided with a bolt hole, and the eight metal support columns of the sinking and floating limit device are respectively connected to the upper and lower support plates, and then the eight sinking heads of the sinking and floating limit device are connected The bolts respectively pass through the rubber brake blocks of the four sinking and floating limiting devices and the four metal gaskets of the sinking and floating limiting devices and are connected in the bolt holes on one side of the metal support columns of the eight sinking and floating limiting devices.

作为本方案的进一步地设计,所述的一套多通道数据采集分析系统包括:18~30条应变信号输入线、一个多通道数据采集仪、PC端信号分析系统,18~30条应变信号输入线分别将传感器输出端与多通道数据采集仪的信号输入端连接起来,用于传递传感器采集到的电信号。As a further design of this program, the set of multi-channel data acquisition and analysis system includes: 18-30 strain signal input lines, a multi-channel data acquisition instrument, PC terminal signal analysis system, 18-30 strain signal input lines The wires respectively connect the output terminals of the sensors with the signal input terminals of the multi-channel data acquisition instrument, and are used to transmit the electrical signals collected by the sensors.

作为本方案的进一步地设计,多通道数据采集仪用于采集试验过程中传感器输出的电信号,其通过与PC端信号分析系统相连接,进而将电信号转化为可以识别的待测物理量,PC端信号分析系统用于分析处理由多通道数据采集仪采集到的电信号,进而用户可以实时对采集到的待测物理量进行处理分析。As a further design of this scheme, the multi-channel data acquisition instrument is used to collect the electrical signal output by the sensor during the test, which is connected with the PC signal analysis system to convert the electrical signal into an identifiable physical quantity to be measured. The terminal signal analysis system is used to analyze and process the electrical signals collected by the multi-channel data acquisition instrument, and then the user can process and analyze the collected physical quantities to be measured in real time.

与现有技术相比,本发明具有以下优点:Compared with the prior art, the present invention has the following advantages:

1)本发明通过质心调节机构的设计实现了翼段模型质心位置相对于扭转轴中心的位置变化,从而方便探究翼段的结构特性对其空气动力特性以及振动特性的影响,可以满足风洞实验模型在不同质心位置下的研究需求。1) The present invention realizes the position change of the position of the center of mass of the wing section model relative to the center of the torsion axis through the design of the center of mass adjustment mechanism, so as to facilitate the exploration of the influence of the structural characteristics of the wing section on its aerodynamic characteristics and vibration characteristics, and can meet the requirements of wind tunnel experiments. The research requirements of the model under different centroid positions.

2)本发明采用空气流道式翼段模型表面压力测量系统的设计,实现了在翼段模型表面无突起且对待测区域流场无影响的情况下,对翼段模型表面跨中位置的压力测量。2) The present invention adopts the design of the air channel type airfoil model surface pressure measurement system, which realizes the pressure on the mid-span position of the wing model surface under the condition that there is no protrusion on the surface of the wing model and no influence on the flow field in the area to be measured. Measurement.

3)本发明所设计的一套中心扭转轴中防滑片的设计可以有效防止翼段模型与中心扭转轴之间发生相对滑动,进而减小试验中出现的系统误差。3) The design of the anti-slip sheet in a set of central torsion shafts designed by the present invention can effectively prevent relative sliding between the airfoil model and the central torsion shaft, thereby reducing systematic errors in the test.

4)本发明所设计的一种两自由度的气动弹性实验装置可以将风洞实验模型的支撑机构与运动测量机构放置在风洞外侧,这样可以在降低风洞阻塞比的同时减少翼段以外的物体对试验结果造成的影响。4) A two-degree-of-freedom aeroelasticity experimental device designed by the present invention can place the support mechanism and the motion measurement mechanism of the wind tunnel experimental model outside the wind tunnel, so that the wind tunnel blocking ratio can be reduced while reducing the airfoil. The impact of the object on the test results.

5)本发明所设计的两自由度支撑机构由于在沉浮自由度中加入了直线滑动轴承,在俯仰自由度上加入了外球面轴承,所以可以将风洞实验模型振动时的机械摩擦降到最低,进而减小试验中出现的系统误差。5) The two-degree-of-freedom support mechanism designed by the present invention can reduce the mechanical friction when the wind tunnel experimental model vibrates to a minimum due to the addition of linear sliding bearings in the degree of freedom of ups and downs and the addition of outer spherical bearings in the degree of freedom of pitching , so as to reduce the systematic error in the experiment.

6)本发明所设计的扭转轴固定杆一端的扭转轴固定夹具可以任意调节风洞实验模型在风洞未吹风时的攻角,可以为试验研究提供多种初始工况。6) The torsion shaft fixing fixture at one end of the torsion shaft fixing rod designed by the present invention can arbitrarily adjust the angle of attack of the wind tunnel experimental model when the wind tunnel is not blowing, and can provide a variety of initial working conditions for experimental research.

7)本发明所设计的俯仰、沉浮限位装置可以有效防止风洞实验模型在大振幅振动时对两自由度支撑机构以及传感器系统的损坏。7) The pitching and sinking limit device designed in the present invention can effectively prevent the damage to the two-degree-of-freedom support mechanism and the sensor system when the wind tunnel experimental model vibrates with a large amplitude.

8)本发明所设计的两自由度支撑机构可以有效的把俯仰-沉浮两个自由度进行解耦,同时在风洞实验模型经历大振幅的沉浮振动情况下,由于沉浮线性弹簧被限制在光滑线性直杆上,所以不会出现沉浮线性弹簧明显的侧向倾斜,所以也就保证了沉浮线性弹簧几何刚度的线性变化。8) The two-degree-of-freedom support mechanism designed in the present invention can effectively decouple the two degrees of freedom of pitching and sinking. At the same time, when the wind tunnel experimental model experiences large-amplitude ups and downs, the linear spring is limited to smooth On the linear straight rod, there will be no obvious lateral inclination of the sinking and floating linear spring, so the linear change of the geometric stiffness of the sinking and floating linear spring is guaranteed.

附图说明Description of drawings

通过阅读参照以下附图对非限制性实施例所作的详细描述,本发明的其它特征、目的和优点将会变得更明显:Other characteristics, objects and advantages of the present invention will become more apparent by reading the detailed description of non-limiting embodiments made with reference to the following drawings:

图1为本发明的整体结构示意图;Fig. 1 is the overall structure schematic diagram of the present invention;

图2为本发明的风洞实验模型的结构示意图;Fig. 2 is the structural representation of wind tunnel experiment model of the present invention;

图3为本发明的两自由度支撑机构的结构示意图;Fig. 3 is a structural schematic diagram of a two-degree-of-freedom support mechanism of the present invention;

图4为本发明的风洞实验模型通过质心调节机构调节质心位置,使翼段模型从前缘到后缘形成气动力心-扭转轴中心(重心)的三心相对位置关系的示意图;Fig. 4 is that the wind tunnel experiment model of the present invention adjusts the position of the center of mass by the center of mass adjustment mechanism, so that the wing section model forms a schematic diagram of the relative position relationship of the three centers of the aerodynamic center-torsion axis center (center of gravity) from the leading edge to the trailing edge;

图5为本发明的风洞实验模型通过质心调节机构调节质心位置,使翼段模型从前缘到后缘形成气动力心-重心-扭转轴中心的三心相对位置关系的示意图;Fig. 5 is a schematic diagram of the relative position relationship of the three centers of the aerodynamic center-center of gravity-torsion axis center formed by the airfoil model from the leading edge to the trailing edge by adjusting the center of mass position of the wind tunnel experimental model of the present invention;

图6为本发明的风洞实验模型通过质心调节机构调节质心位置,使翼段模型从前缘到后缘形成气动力心-扭转轴中心-重心的三心相对位置关系的示意图;Fig. 6 is a schematic diagram of the relative position relationship of the three centers of the aerodynamic center-torsion axis center-center of gravity formed by the airfoil model from the leading edge to the trailing edge through the adjustment of the center of mass position of the wind tunnel experimental model of the present invention;

图7为本发明的翼段模型连接测压管示意图;Fig. 7 is the schematic diagram of connecting the piezometric tube of the wing section model of the present invention;

图8为本发明的翼段模型截面空气流道示意图;Fig. 8 is a schematic diagram of the cross-sectional air channel of the wing section model of the present invention;

图9为本发明的常规质量块示意图;Fig. 9 is a schematic diagram of a conventional mass of the present invention;

图10为本发明的偏心质量块示意图;Fig. 10 is a schematic diagram of the eccentric mass of the present invention;

图11为本发明的两自由度支撑机构局部示意图;Fig. 11 is a partial schematic diagram of a two-degree-of-freedom support mechanism of the present invention;

图12为本发明的沉浮弹性机构与支撑板和线性托架的连接示意图;Fig. 12 is a schematic diagram of the connection between the ups and downs elastic mechanism of the present invention, the support plate and the linear bracket;

图13为本发明的风洞实验模型与两自由度支撑机构连接示意图;Fig. 13 is a schematic diagram of the connection between the wind tunnel experimental model of the present invention and the two-degree-of-freedom support mechanism;

图14为本发明的沉浮限位装置示意图;Fig. 14 is a schematic diagram of the sinking and floating limiting device of the present invention;

图15为本发明的俯仰限位装置示意图;Fig. 15 is a schematic diagram of the pitch limiting device of the present invention;

图16为本发明的沉浮弹性机构示意图。Fig. 16 is a schematic diagram of the ups and downs elastic mechanism of the present invention.

图中,1-风洞抗扰流罩,2-多通道数据采集仪,3-PC端信号分析系统,4-压力变送器,5-应变信号输入线,6-测压管,7-多通道数据采集仪专用网线,8-风洞,9-翼段模型,10-端板,11-测压孔,12-放置螺栓的通孔,13-高强度扭转轴螺栓,14-防滑片,15-扭转轴防松螺母,16-固定螺栓,17-防松螺母,18-质量块固定螺栓,19-质量块防松螺母,20-常规质量块,21-偏心质量块,22-空气流道,23-风洞固定板,24-支撑板,25-线性托架,26-沉浮限位装置,27-俯仰限位装置,28-角位移传感器固定法兰,29-角位移传感器,30-非接触式磁滞伸缩位移传感器,31-浮动磁铁,32-沉浮弹性机构,33-沉浮线性弹簧,34-沉浮线性弹簧固定座,35-U型螺栓,36-U型螺栓配套螺母,37-俯仰线性弹簧,38-扭转支杆,39-直线滑动轴承,40-外球面轴承,41-扭转轴固定杆,42-俯仰弹簧连接柱,43-光滑线性直杆,44-扭转支杆固定螺栓,45-沉浮弹性机构固定螺栓,46-外球面轴承固定螺栓,47-浮动磁铁固定螺栓,48-扭转轴夹具固定螺栓,49-支撑板固定螺栓,50-风洞固定板固定螺栓,51-沉浮限位装置金属支撑柱,52-沉浮限位装置金属垫片,53-沉浮限位装置橡胶制动块,54-沉浮限位装置沉头连接螺栓,55-俯仰限位装置金属固定片,56-俯仰限位装置金属固定片连接螺栓,57-俯仰限位装置橡胶制动块,58-俯仰限位装置沉头连接螺栓,59-俯仰限位装置沉头连接螺栓配套螺母。In the figure, 1-wind tunnel anti-turbulence cover, 2-multi-channel data acquisition instrument, 3-PC terminal signal analysis system, 4-pressure transmitter, 5-strain signal input line, 6-pressure measuring tube, 7- Special network cable for multi-channel data acquisition instrument, 8-wind tunnel, 9-wing model, 10-end plate, 11-pressure measuring hole, 12-through hole for placing bolts, 13-high-strength torsion shaft bolts, 14-anti-slip sheet , 15-torsion shaft locknut, 16-fixing bolt, 17-locknut, 18-mass block fixing bolt, 19-mass block locknut, 20-conventional mass block, 21-eccentric mass block, 22-air Flow channel, 23-wind tunnel fixing plate, 24-supporting plate, 25-linear bracket, 26-floating limit device, 27-pitch limit device, 28-angular displacement sensor fixing flange, 29-angular displacement sensor, 30-non-contact hysteresis telescopic displacement sensor, 31-floating magnet, 32-floating elastic mechanism, 33-floating linear spring, 34-floating linear spring fixing seat, 35-U-bolt, 36-U-bolt matching nut, 37-pitch linear spring, 38-torsion strut, 39-linear sliding bearing, 40-outer spherical bearing, 41-torsion shaft fixing rod, 42-pitch spring connecting column, 43-smooth linear straight rod, 44-torsion strut Fixing bolts, 45-fixing bolts for sinking and floating elastic mechanisms, 46-fixing bolts for outer spherical bearings, 47-fixing bolts for floating magnets, 48-fixing bolts for torsion shaft clamps, 49-fixing bolts for supporting plates, 50-fixing bolts for wind tunnel fixing plates, 51-Metal support column of sinking and floating limiting device, 52-Metal gasket of sinking and floating limiting device, 53-Rubber brake block of sinking and floating limiting device, 54-Sunk head connecting bolt of sinking and floating limiting device, 55-Metal fixing of pitching limiting device Sheet, 56-pitch limiting device metal fixing piece connecting bolt, 57-pitch limiting device rubber brake block, 58-pitch limiting device countersunk head connecting bolt, 59-pitch limiting device countersunk head connecting bolt supporting nut.

具体实施方式Detailed ways

下面结合具体实施例对本发明进行详细说明。以下实施例将有助于本领域的技术人员进一步理解本发明,但不以任何形式限制本发明。应当指出的是,对本领域的普通技术人员来说,在不脱离本发明构思的前提下,还可以做出若干变形和改进。这些都属于本发明的保护范围。The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

如图1-图16所示,本发明实施例的一种两自由度的气动弹性实验装置,包括风洞实验模型、两自由度支撑机构、信号采集系统;As shown in Figures 1-16, a two-degree-of-freedom aeroelasticity experimental device according to an embodiment of the present invention includes a wind tunnel experimental model, a two-degree-of-freedom support mechanism, and a signal acquisition system;

所述的风洞实验模型包括一个翼段模型9,16~28个测压管6、两块端板10,一套中心扭转轴,一套锁紧机构,一套质心调节机构;The wind tunnel test model includes a wing section model 9, 16-28 piezometric tubes 6, two end plates 10, a set of central torsion shafts, a set of locking mechanisms, and a set of center-of-mass adjustment mechanisms;

所述的翼段模型9经3D打印制造所得,翼段模型9内部设计有放置螺栓的通孔12,在翼段模型9跨中位置处的上下表面分别设计有直径为1.6mm的8~14个测压孔11,8~14个测压孔11均沿翼型表面的法线方向,测压孔11通过翼段模型9内部设计的空气流道22与测压管6连接,测压管6延伸至风洞8外,与压力变送器4进行连接;The wing section model 9 is manufactured by 3D printing. The wing section model 9 is designed with through holes 12 for placing bolts. The upper and lower surfaces of the wing section model 9 at the mid-span position are respectively designed with holes 8 to 14 with a diameter of 1.6 mm. pressure measuring holes 11, 8-14 pressure measuring holes 11 are all along the normal direction of the airfoil surface, the pressure measuring holes 11 are connected with the pressure measuring tube 6 through the air flow channel 22 designed inside the airfoil model 9, and the pressure measuring tube 6 extends to the outside of the wind tunnel 8, and is connected with the pressure transmitter 4;

所述的两块端板10经3D打印制造所得,其含有与翼段模型9截面镂空形状相同的镂空设计,通过螺栓固定连接在翼段模型9两端,以防止翼段的端部效应,确保流动为准二维流动;The two end plates 10 are manufactured by 3D printing, which have the same hollow-out design as the section hollow-out shape of the wing section model 9, and are fixedly connected to both ends of the wing section model 9 by bolts to prevent the end effect of the wing section. Ensure that the flow is a quasi-two-dimensional flow;

所述的一套中心扭转轴包括一个高强度扭转轴螺栓13和一个扭转轴防松螺母15以及一个防滑片14,高强度扭转轴螺栓13穿过防滑片14、两块端板10以及翼段模型9内部预留的放置螺栓的通孔12与两自由度支撑机构上的扭转轴固定杆41相连接,并用扭转轴防松螺母15进行固定,其中防滑片14的一部分嵌入到远离支撑机构一侧的端板中,并与高强度扭转轴螺栓13的头部固定连接,以防止高强度扭转轴螺栓13与翼段模型9之间发生相对滑动;The set of central torsion shafts includes a high-strength torsion shaft bolt 13, a torsion shaft locknut 15 and an anti-slip sheet 14, and the high-strength torsion shaft bolt 13 passes through the anti-slip sheet 14, two end plates 10 and the wings The bolt-placed through-hole 12 reserved inside the model 9 is connected to the torsion axis fixing rod 41 on the two-degree-of-freedom support mechanism, and fixed with the torsion axis locknut 15, wherein a part of the anti-slip sheet 14 is embedded in a position far away from the support mechanism. and fixedly connected with the head of the high-strength torsion shaft bolt 13 to prevent relative sliding between the high-strength torsion shaft bolt 13 and the wing model 9;

所述的一套锁紧机构位于翼段模型9靠近后缘的位置,包括固定螺栓16以及防松螺母17,固定螺栓16通过端板10以及翼段模型9内部预留的放置螺栓的通孔12将翼段模型9和两个端板10连接在一起,并用防松螺母17进行固定;The set of locking mechanisms is located near the trailing edge of the wing model 9 and includes fixing bolts 16 and locknuts 17. The fixing bolts 16 pass through the end plate 10 and through holes reserved inside the wing model 9 for placing bolts. 12 Connect the wing section model 9 and the two end plates 10 together, and fix them with locknuts 17;

所述的一套质心调节机构包括两个常规质量块20、两个偏心质量块21和一套质量块固定机构;两个常规质量块20为黄铜材质,中心打孔,两个偏心质量块21为黄铜材质,偏心打孔,偏心质量块21与常规质量块20的重量相同;两个常规质量块20组合使用,用于调节翼段模型9的质心位置,使其更靠近扭转轴中心,使翼段模型9从前缘到后缘形成气动力心-扭转轴中心(重心)的三心相对位置关系;两个偏心质量块21组合使用,用于调节翼段模型9质心位置,使其更靠近翼段模型9的前缘,使翼段模型9从前缘到后缘形成气动力心-重心-扭转轴中心的三心相对位置关系,一个常规质量块20与一个偏心质量块21组合使用,用于调节翼段模型9质心位置,使其更靠近翼段模型9的后缘,使翼段模型9从前缘到后缘形成气动力心-扭转轴中心-重心的三心相对位置关系;一套质量块固定机构由质量块固定螺栓18和质量块防松螺母19构成,通过根据试验中对不同质心位置的需求,利用质量块固定螺栓18和质量块防松螺母19将两个质量块分别固定在翼段模型9两侧的端板10上,从而实现翼段模型9质心位置的改变;The set of center-of-mass adjustment mechanism includes two conventional mass blocks 20, two eccentric mass blocks 21 and a set of mass block fixing mechanisms; the two conventional mass blocks 20 are made of brass, with a hole in the center, and the two eccentric mass blocks 21 is made of brass, eccentrically drilled, and the eccentric mass 21 has the same weight as the conventional mass 20; two conventional mass 20 are used in combination to adjust the position of the center of mass of the wing model 9, making it closer to the center of the torsion axis , so that the wing section model 9 forms a three-center relative positional relationship of aerodynamic center-torsion axis center (center of gravity) from the leading edge to the trailing edge; two eccentric masses 21 are used in combination to adjust the position of the wing section model 9 center of mass, so that Closer to the leading edge of the wing section model 9, so that the wing section model 9 forms a three-center relative positional relationship of aerodynamic center-center of gravity-torsion axis center from the leading edge to the trailing edge, and a conventional mass 20 is used in combination with an eccentric mass 21 , for adjusting the position of the center of mass of the wing section model 9, making it closer to the trailing edge of the wing section model 9, so that the wing section model 9 forms a three-center relative positional relationship of aerodynamic center-torsion axis center-center of gravity from the leading edge to the trailing edge; A set of mass fixing mechanism is composed of mass fixing bolts 18 and mass locking nuts 19. According to the requirements for different centroid positions in the test, the mass fixing bolts 18 and mass locking nuts 19 are used to connect the two mass respectively fixed on the end plates 10 on both sides of the wing section model 9, so as to realize the change of the position of the center of mass of the wing section model 9;

所述的两自由度支撑机构包括风洞固定板23、风洞抗扰流罩1、两块支撑板24、两个线性托架25、一个角位移传感器固定法兰28、一根扭转轴固定杆41、两根扭转支杆38、四根光滑线性直杆43、四组沉浮弹性机构32、四组俯仰线性弹簧37、八个俯仰弹簧连接柱42、八个直线滑动轴承39、两个外球面轴承40、四套沉浮限位装置26和八套俯仰限位装置27;The two-degree-of-freedom support mechanism includes a wind tunnel fixing plate 23, a wind tunnel anti-turbulence cover 1, two support plates 24, two linear brackets 25, an angular displacement sensor fixing flange 28, and a torsion shaft fixing Rod 41, two torsion struts 38, four smooth linear straight rods 43, four groups of ups and downs elastic mechanisms 32, four groups of pitch linear springs 37, eight pitch spring connecting columns 42, eight linear sliding bearings 39, two outer Spherical bearing 40, four sets of ups and downs limit devices 26 and eight sets of pitch limit devices 27;

所述信号采集系统包括16~28个压力变送器4、一个角位移传感器29,一个非接触式磁滞伸缩位移传感器30和一套多通道数据采集分析系统,16~28个压力变送器4的压力测量端分别与从风洞8中引出的测压管6连接,另一端通过应变信号输入线5分别连接在多通道数据采集仪2的信号采集通道上,角位移传感器29固定在角位移传感器固定法兰28上,进而与扭转轴固定杆41的配套轴孔进行连接,角位移传感器29的信号输出端通过应变信号输入线5连接在多通道数据采集仪2的信号采集通道上,用于采集风洞实验模型的瞬时俯仰角信号,非接触式磁滞伸缩位移传感器30连接在风洞固定板23上,其与固定在线性托架25上浮动磁铁31的距离为2mm;通过风洞实验模型的上下运动带动线性托架25的线性运动进而带动浮动磁铁31的线性运动,通过浮动磁铁31在非接触式磁滞伸缩位移传感器30的测杆上滑动的距离进而测量出风洞实验模型的瞬时沉浮位移。非接触式磁滞伸缩位移传感器30的信号输出端通过应变信号输入线5连接在多通道数据采集仪2的信号采集通道上,用于采集风洞实验模型的瞬时沉浮位移信号。The signal acquisition system includes 16 to 28 pressure transmitters 4, an angular displacement sensor 29, a non-contact magnetic hysteresis displacement sensor 30 and a set of multi-channel data acquisition and analysis system, 16 to 28 pressure transmitters The pressure measuring ends of 4 are respectively connected to the pressure measuring tubes 6 drawn from the wind tunnel 8, and the other ends are respectively connected to the signal acquisition channels of the multi-channel data acquisition instrument 2 through the strain signal input lines 5, and the angular displacement sensor 29 is fixed at the angle The displacement sensor is fixed on the flange 28, and then connected with the supporting shaft hole of the torsion shaft fixed rod 41, the signal output end of the angular displacement sensor 29 is connected to the signal acquisition channel of the multi-channel data acquisition instrument 2 through the strain signal input line 5, For collecting the instantaneous pitch angle signal of the wind tunnel experimental model, the non-contact hysteresis telescopic displacement sensor 30 is connected on the wind tunnel fixed plate 23, and the distance between it and the floating magnet 31 fixed on the linear bracket 25 is 2 mm; The up and down motion of the hole test model drives the linear motion of the linear bracket 25, which in turn drives the linear motion of the floating magnet 31. The distance that the floating magnet 31 slides on the measuring rod of the non-contact magneto-hysteretic displacement sensor 30 is used to measure the distance of the wind tunnel experiment. The instantaneous heave displacement of the model. The signal output end of the non-contact hysteresis stretching displacement sensor 30 is connected to the signal acquisition channel of the multi-channel data acquisition instrument 2 through the strain signal input line 5, and is used for collecting instantaneous ups and downs displacement signals of the wind tunnel experimental model.

组装时,包括如下步骤:进行两自由度支撑机构的组装,具体地,首先,将八个沉浮线性弹簧33分别利用六十四个U型螺栓35和六十四个U型螺栓配套螺母36固定在十六个沉浮线性弹簧固定座34上,进而组装成四组即八个沉浮弹性机构32。需要注意的是:四组沉浮弹性机构32是以每个线性托架25上下对称的两个沉浮弹性机构32为一组,其中每个线性托架25通过两组沉浮弹性机构32悬挂。然后将四套沉浮限位装置26分别安装到上下两块支撑板24上,每套沉浮限位装置26均由两个沉浮限位装置金属支撑柱51、一个沉浮限位装置金属垫片52、一个沉浮限位装置橡胶制动块53以及两个沉浮限位装置沉头连接螺栓54所构成,其中,沉浮限位装置金属支撑柱51的一端设置有螺纹,另一端设置有螺栓孔,八个沉浮限位装置金属支撑柱51分别连接在上下两块支撑板24上,然后八个沉浮限位装置沉头连接螺栓54分别穿过四个沉浮限位装置橡胶制动块53以及四个沉浮限位装置金属垫片52连接在八个沉浮限位装置金属支撑柱51一侧的螺栓孔内。需要注意的是:每块支撑板24上均安装有两套沉浮限位装置26,上下两块支撑板24上的沉浮限位装置26相互对称布置。接着将四根光滑线性直杆43的螺纹端连接在上支撑板上预留的螺栓孔内。其中光滑线性直杆43的一端设置有螺纹,另一端设置有螺栓孔,且在上支撑板上还设置有固定沉浮弹性机构32的凹槽,然后将四个沉浮弹性机构32分别穿过4根光滑线性直杆43,并将四个沉浮弹性机构32一端的沉浮线性弹簧固定座34通过沉浮弹性机构固定螺栓45固定在上支撑板上的凹槽内。During assembly, the following steps are included: assembling the two-degree-of-freedom support mechanism, specifically, first, fixing the eight ups and downs linear springs 33 with sixty-four U-bolts 35 and sixty-four U-bolt matching nuts 36 On the sixteen ups and downs linear spring holders 34, four groups of eight ups and downs elastic mechanisms 32 are then assembled. It should be noted that the four sets of ups and downs elastic mechanisms 32 are a group of two up and down symmetrical up and down elastic mechanisms 32 for each linear bracket 25 , wherein each linear bracket 25 is suspended by two sets of ups and downs elastic mechanisms 32 . Then four sets of sinking and floating limiting devices 26 are respectively installed on the upper and lower two support plates 24, and each set of sinking and floating limiting devices 26 is composed of two sinking and floating limiting device metal support columns 51, a sinking and floating limiting device metal gasket 52, A sinking and floating limiting device rubber brake block 53 and two sinking and floating limiting device countersunk head connecting bolts 54 are formed, wherein one end of the sinking and floating limiting device metal support column 51 is provided with threads, and the other end is provided with bolt holes, eight The metal support columns 51 of the sinking and floating limiting devices are respectively connected to the upper and lower support plates 24, and then the eight sinking head connecting bolts 54 of the sinking and floating limiting devices respectively pass through the four rubber brake blocks 53 of the sinking and floating limiting devices and the four rubber brake blocks 53 of the sinking and floating limiting devices. The position device metal gasket 52 is connected in the bolt holes on one side of the metal support columns 51 of the eight ups and downs limit devices. It should be noted that two sets of ups and downs limiting devices 26 are installed on each support plate 24 , and the ups and downs limit devices 26 on the upper and lower support plates 24 are symmetrically arranged. Then the threaded ends of four smooth linear straight rods 43 are connected in the reserved bolt holes on the upper support plate. Wherein one end of smooth linear straight rod 43 is provided with screw thread, and the other end is provided with bolt hole, and also is provided with the groove of fixed ups and downs elastic mechanism 32 on the upper support plate, then four ups and downs elastic mechanisms 32 pass through 4 respectively smooth linear straight bar 43, and the ups and downs linear spring holders 34 at one end of the four ups and downs elastic mechanisms 32 are fixed in the grooves on the upper support plate through the ups and downs elastic mechanism fixing bolts 45.

其次将四个直线滑动轴承39分别穿过四根光滑线性直杆43与连接在上支撑板上的四个沉浮弹性机构32另外一端的沉浮线性弹簧固定座34相连接,然后将连接有上支撑板的四根光滑线性直杆43穿过内外两个线性托架25上设置的通孔,并利用沉浮弹性机构固定螺栓45将连接有直线滑动轴承39的沉浮线性弹簧固定座34固定在内外两个线性托架25上方设置的凹槽内。这里提到的内侧线性托架指的是靠近风洞固定板23一侧的线性托架,外侧线性托架指的是远离风洞固定板23一侧的线性托架。Secondly, four linear sliding bearings 39 are respectively passed through four smooth linear straight rods 43 and connected with the sinking and floating linear spring holders 34 at the other end of the four sinking and floating elastic mechanisms 32 on the upper supporting plate, and then the upper supporting The four smooth linear straight rods 43 of the board pass through the through holes provided on the inner and outer linear brackets 25, and the ups and downs linear spring fixing seat 34 connected with the linear sliding bearing 39 is fixed on the inner and outer two by using the ups and downs elastic mechanism fixing bolts 45. In the groove provided above the linear bracket 25. The inner linear bracket mentioned here refers to the linear bracket on the side close to the wind tunnel fixing plate 23 , and the outer linear bracket refers to the linear bracket on the side away from the wind tunnel fixing plate 23 .

然后将另外四个直线滑动轴承39与另外四个沉浮弹性机构32一端的沉浮线性弹簧固定座34相连接,接着将连接好的沉浮弹性机构32和直线滑动轴承39穿过连接在上支撑板上的四根光滑线性直杆43,并利用沉浮弹性机构固定螺栓45将连接有直线滑动轴承39的沉浮线性弹簧固定座34固定在内外两个线性托架25下方设置的凹槽内。Then other four linear sliding bearings 39 are connected with the sinking and floating linear spring holders 34 at one end of the other four sinking and floating elastic mechanisms 32, and then the connected sinking and floating elastic mechanisms 32 and linear sliding bearings 39 are passed through and connected to the upper support plate Four smooth linear straight rods 43, and utilize the ups and downs elastic mechanism fixing bolt 45 to be connected with the ups and downs of the linear sliding bearing 39.

然后将固定有沉浮限位装置26的下支撑板安装在四根光滑线性直杆43上有螺栓孔的一端,其中在下支撑板的两个面上分别设置有连接光滑线性直杆43的四个沉头螺栓孔和四个圆柱凹槽,其中下支撑板顶部的四个圆柱凹槽用于连接四根光滑线性直杆43的螺栓孔一端,下支撑板底部的四个沉头螺栓孔,用于螺栓固定连接四根光滑线性直杆43底端的螺栓孔。此外在下支撑板上还设置有用于固定沉浮弹性机构32的凹槽。接着将连接在内外两个线性托架25下方的四个沉浮弹性机构32另外一端的沉浮线性弹簧固定座34通过沉浮弹性机构固定螺栓45固定在下支撑板上的凹槽内。Then the lower support plate that is fixed with the ups and downs limiter 26 is installed on one end of four smooth linear straight rods 43 with bolt holes, wherein two surfaces of the lower support plate are respectively provided with four connecting smooth linear straight rods 43 Countersunk bolt holes and four cylindrical grooves, wherein the four cylindrical grooves on the top of the lower support plate are used to connect one end of the bolt holes of four smooth linear straight rods 43, and the four countersunk bolt holes on the bottom of the lower support plate are used The bolt holes at the bottoms of four smooth linear straight rods 43 are fixedly connected by bolts. In addition, a groove for fixing the ups and downs elastic mechanism 32 is also provided on the lower support plate. Then the ups and downs linear spring holder 34 at the other end of the four ups and downs elastic mechanisms 32 that are connected below the two linear brackets 25 inside and outside is fixed in the groove on the lower support plate by the ups and downs elastic mechanism fixing bolt 45 .

然后将两个外球面轴承40用外球面轴承固定螺栓46固定在内外两个线性托架25外侧的凹槽内,这里提到的外侧指的是内侧线性托架靠近风洞固定板23的一侧以及外侧线性托架远离风洞固定板23的一侧。接着将扭转轴固定杆41穿过两个外球面轴承40并进行轴与轴承的紧固配合,然后将两个扭转支杆38竖直穿过扭转轴固定杆41的前后两个预留的通孔中,并通过扭转支杆固定螺栓44将其固定在扭转轴固定杆41上。其中所提到的扭转轴固定杆41前后预留的通孔,均设置在距离内外两个线性托架25外侧面的相同距离处。然后在内外两个线性托架25的外侧分别通过螺纹连接安装有四组即八个俯仰弹簧连接柱42,其中以每个线性托架25一侧的左右对称的两个俯仰弹簧连接柱42为一组,每个线性托架25上分别关于扭转轴固定杆41的截面中心,对称的安装有两组俯仰弹簧连接柱42。然后四组俯仰线性弹簧37将四组俯仰弹簧连接柱42与两个扭转支杆38连接在一起,其中以每个线性托架25一侧的左右对称的两个俯仰线性弹簧37为一组,每个线性托架25上安装有两组俯仰线性弹簧37。接着将八套俯仰限位装置27分别安装于内外两个线性托架25上,其中每个线性托架25的外侧均安装有四套俯仰限位装置27,以每两套为一组对称的安装于扭转支杆38的两侧,每个线性托架25上的两组俯仰限位装置27分别关于扭转轴固定杆41的截面中心相对称。每套俯仰限位装置27均由一个俯仰限位装置金属固定片55、四个俯仰限位装置金属固定片连接螺栓56、一个俯仰限位装置橡胶制动块57以及两个俯仰限位装置沉头连接螺栓58和两个俯仰限位装置沉头连接螺栓配套螺母59所构成。其中,以一套俯仰限位装置27的安装为例进行说明:一个俯仰限位装置金属固定片55通过四个俯仰限位装置金属固定片连接螺栓56固定在一个线性托架25上,然后两个俯仰限位装置沉头连接螺栓58穿过一个俯仰限位装置橡胶制动块57,通过两个俯仰限位装置沉头连接螺栓配套螺母59固定在一个俯仰限位装置金属固定片55上。接着通过螺栓将角位移传感器固定法兰28与角位移传感器29进行固定,然后将固定有角位移传感器29的角位移传感器固定法兰28用螺栓固定在外侧线性托架上。接着将与非接触式磁滞伸缩位移传感器30配套使用的浮动磁铁31用浮动磁铁固定螺栓47固定在内侧线性托架上,然后将非接触式磁滞伸缩位移传感器30用螺栓固定在风洞固定板23上,然后将组装好的上下两块支撑板24用支撑板固定螺栓49固定在风洞固定板23上,接着将风洞抗扰流罩1通过风洞固定板固定螺栓50连接在风洞固定板23上,然后将整体的两自由度支撑机构用风洞固定板固定螺栓50固定在风洞8的外侧壁面上。Then two outer spherical bearings 40 are fixed in the grooves on the outside of the two linear brackets 25 inside and outside with the outer spherical bearing fixing bolts 46. The outside mentioned here refers to a part of the inner linear bracket close to the wind tunnel fixing plate 23. The side and the outer linear bracket are away from the side of the wind tunnel fixing plate 23 . Then the torsion shaft fixed rod 41 is passed through two outer spherical bearings 40 and the fastening fit of the shaft and the bearing is carried out; and fix it on the torsion shaft fixing rod 41 by twisting the rod fixing bolt 44. The through holes mentioned in the front and rear of the torsion shaft fixing rod 41 are all set at the same distance from the outer surfaces of the inner and outer linear brackets 25 . Then on the outside of the two linear brackets 25 inside and outside, four groups or eight pitch spring connecting columns 42 are respectively installed by threaded connection, wherein the left and right symmetrical two pitch spring connecting columns 42 on one side of each linear bracket 25 are One set, two sets of pitch spring connecting columns 42 are symmetrically installed on each linear bracket 25 with respect to the section center of the torsion axis fixing rod 41 . Then the four sets of pitching linear springs 37 connect the four sets of pitching spring connecting columns 42 and the two torsion struts 38 together, wherein the left and right symmetrical two pitching linear springs 37 on one side of each linear bracket 25 form a group, Two sets of pitch linear springs 37 are mounted on each linear bracket 25 . Then eight sets of pitch limiting devices 27 are installed on two linear brackets 25 inside and outside respectively, wherein four sets of pitch limiting devices 27 are installed on the outside of each linear bracket 25, with every two sets as a group of symmetrical Installed on both sides of the torsion strut 38 , two sets of pitch limiting devices 27 on each linear bracket 25 are respectively symmetrical with respect to the center of the section of the torsion axis fixing rod 41 . Every set of pitch limiter 27 is composed of a pitch limiter metal fixing piece 55, four pitch limiter metal fixing pieces connecting bolts 56, a pitch limiter rubber brake block 57 and two pitch limiter 24 Head connecting bolt 58 and two pitch limiter countersunk head connecting bolt supporting nuts 59 are formed. Wherein, the installation of a set of pitch limiter 27 is taken as an example for illustration: a pitch limiter metal fixing piece 55 is fixed on a linear bracket 25 through four pitch limiter metal fixing piece connecting bolts 56, and then two A pitch limit device countersunk connecting bolt 58 passes through a pitch limit device rubber brake block 57, and is fixed on a pitch limit device metal retainer 55 by two pitch limit device countersunk head connecting bolt supporting nuts 59. Then the angular displacement sensor fixing flange 28 and the angular displacement sensor 29 are fixed by bolts, and then the angular displacement sensor fixing flange 28 fixed with the angular displacement sensor 29 is fixed on the outer linear bracket with bolts. Then the floating magnet 31 used in conjunction with the non-contact hysteresis telescopic displacement sensor 30 is fixed on the inner linear bracket with the floating magnet fixing bolt 47, and then the non-contact hysteresis telescopic displacement sensor 30 is fixed on the wind tunnel with bolts. plate 23, and then the assembled upper and lower support plates 24 are fixed on the wind tunnel fixed plate 23 with support plate fixing bolts 49, and then the wind tunnel anti-turbulence cover 1 is connected to the wind tunnel through the wind tunnel fixing plate fixing bolts 50. On the hole fixing plate 23, then the integral two-degree-of-freedom support mechanism is fixed on the outer wall surface of the wind tunnel 8 with the wind tunnel fixing plate fixing bolt 50.

然后进行风洞实验模型的组装,具体地,首先将测压管6与翼段模型9内部的空气流道22相连接,然后在翼段模型9的空气流道22与测压管6的接口处用密封胶进行密封。其中在翼段模型9跨中位置处的上下表面分别高精度的设计有直径为1.6mm的10个测压孔11,所设计的测压孔11均沿翼段模型9表面的法线方向,测压孔11通过翼段模型9内部设计的空气流道22与测压管6连接。其中所提到的翼段模型9内部设计的空气流道22,其入口端与测压孔11光滑连接,空气流道22的出口端位于设有两自由度支撑机构一侧的翼段模型9的端部。接着用一套中心扭转轴以及一套锁紧机构将翼段模型9与两块端板10固定在一起。其中两块端板10含有与翼段模型9截面镂空形状相同的镂空设计,通过螺栓固定连接在翼段模型9两端,以防止翼段模型9的端部效应,确保流动为准二维流动。所提到的一套中心扭转轴包括一个高强度扭转轴螺栓13和一个扭转轴防松螺母15以及一个防滑片14,其中防滑片14的一部分嵌入到远离支撑机构一侧的端板中,并与高强度扭转轴螺栓13的头部固定连接,以防止高强度扭转轴螺栓13与翼段模型9之间发生相对滑动。所提到的一套锁紧机构位于翼段模型9靠近后缘的位置,包括固定螺栓16以及防松螺母17。固定螺栓16通过端板10以及翼段模型9内部预留的放置螺栓的通孔12将翼段模型9和两个端板10连接在一起,并用防松螺母17进行固定。然后把连接好的风洞实验模型的高强度扭转轴螺栓13用扭转轴夹具固定螺栓48固定在两自由度支撑机构上的扭转轴固定杆41的扭转轴固定夹具一端。然后将质心调节机构安装到翼段模型9上,其中一套质心调节机构包括两个常规质量块20,两个偏心质量块21,一套质量块固定机构。其中偏心质量块21与常规质量块20的重量相同。所提到的偏心质量块21为偏心打孔设计,所提到的常规质量块20为中心打孔设计,质量块均为黄铜材质,用于调节翼段模型9质心位置。一套质量块固定机构由质量块固定螺栓18和质量块防松螺母19构成,通过利用质量块固定螺栓18和质量块防松螺母19将两个质量块分别固定在翼段模型9两侧的端板10上,试验中可以根据不同的质心需求,对质量块的位置进行调节,进而达到改变质心位置的效果。Carry out the assembly of wind tunnel experiment model then, specifically, at first the pressure measuring tube 6 is connected with the air channel 22 inside the wing section model 9, and then at the interface of the air channel 22 of the wing section model 9 and the pressure measuring tube 6 Seal with sealant. Among them, 10 pressure measuring holes 11 with a diameter of 1.6mm are designed with high precision on the upper and lower surfaces at the mid-span position of the wing model 9, and the designed pressure measuring holes 11 are all along the normal direction of the surface of the wing model 9, The pressure measuring hole 11 is connected with the pressure measuring tube 6 through the air channel 22 designed inside the airfoil model 9 . The air channel 22 designed inside the wing section model 9 mentioned therein has its inlet end smoothly connected with the pressure measuring hole 11, and the outlet end of the air channel 22 is located on the wing section model 9 on the side of the two-degree-of-freedom support mechanism. the end of. Then use a set of central torsion shaft and a set of locking mechanism to fix the wing section model 9 and the two end plates 10 together. Two of the end plates 10 have the same hollow-out design as the cross-sectional hollow shape of the wing model 9, and are fixedly connected to both ends of the wing model 9 by bolts to prevent the end effect of the wing model 9 and ensure that the flow is a quasi-two-dimensional flow . The mentioned set of central torsion shafts includes a high-strength torsion shaft bolt 13, a torsion shaft locknut 15, and an anti-slip sheet 14, wherein a part of the anti-slip sheet 14 is embedded in the end plate on the side away from the support mechanism, and It is fixedly connected with the head of the high-strength torsion shaft bolt 13 to prevent relative sliding between the high-strength torsion shaft bolt 13 and the wing model 9 . The set of locking mechanisms mentioned is located near the trailing edge of the wing segment model 9 and includes fixing bolts 16 and locknuts 17 . Fixing bolts 16 connect the wing section model 9 and the two end plates 10 through the end plate 10 and through holes 12 for placing bolts reserved inside the wing section model 9 , and are fixed with locknuts 17 . Then the high-strength torsion shaft bolt 13 of the wind tunnel experiment model that is connected is fixed on the torsion shaft fixing fixture one end of the torsion shaft fixing rod 41 on the two-degree-of-freedom support mechanism with the torsion shaft clamp fixing bolt 48. Then the center of mass adjustment mechanism is installed on the wing section model 9, wherein a set of center of mass adjustment mechanism includes two conventional mass blocks 20, two eccentric mass blocks 21, and a set of mass block fixing mechanisms. Wherein the eccentric mass 21 has the same weight as the conventional mass 20 . The mentioned eccentric mass 21 is designed with an eccentric hole, and the mentioned conventional mass 20 is designed with a center hole. The masses are made of brass and are used to adjust the position of the center of mass of the wing model 9 . A set of mass block fixing mechanism is composed of mass block fixing bolts 18 and mass block locknuts 19, and the two mass blocks are respectively fixed on the two sides of the wing section model 9 by using the mass block fixing bolts 18 and the mass block locknuts 19. On the end plate 10, the position of the mass block can be adjusted according to different requirements of the center of mass during the test, thereby achieving the effect of changing the position of the center of mass.

最后进行测压管路与信号采集系统的连接,具体地,首先将与翼段模型9的空气流道22连接好的测压管6的另外一端引出风洞8外部并与压力变送器4的测压端进行连接,然后利用压力变送器4以及多通道数据采集分析系统对连接好的测压通道进行气密性检查。确保所有测压通道气密性完好后,将角位移传感器29和非接触式磁滞伸缩位移传感器30与多通道数据采集分析系统进行连接。其中多通道数据采集分析系统包括:应变信号输入线5、多通道数据采集仪2以及PC端信号分析系统3。所提到的应变信号输入线5分别将传感器输出端与多通道数据采集仪2的信号输入端连接起来,然后多通道数据采集仪2通过多通道数据采集仪专用网线7与PC端的网线接口端相连接。其中应变信号输入线5用于传递传感器采集到的信号,多通道数据采集仪2用于采集试验过程中传感器输出的电信号,PC端信号分析系统3用于分析处理由多通道数据采集仪2采集到的电信号,进而用户可以实时对采集到的待测物理量进行处理分析。Finally, connect the pressure measuring pipeline with the signal acquisition system, specifically, first lead the other end of the pressure measuring tube 6 connected to the air channel 22 of the airfoil model 9 out of the wind tunnel 8 and connect it with the pressure transmitter 4 Connect the pressure measuring end, and then use the pressure transmitter 4 and the multi-channel data acquisition and analysis system to check the air tightness of the connected pressure measuring channel. After ensuring that the airtightness of all the pressure measurement channels is intact, the angular displacement sensor 29 and the non-contact magnetostrictive displacement sensor 30 are connected to the multi-channel data acquisition and analysis system. The multi-channel data acquisition and analysis system includes: a strain signal input line 5 , a multi-channel data acquisition instrument 2 and a PC terminal signal analysis system 3 . The mentioned strain signal input line 5 respectively connects the output end of the sensor with the signal input end of the multi-channel data acquisition instrument 2, and then the multi-channel data acquisition instrument 2 is connected to the network cable interface end of the PC through the dedicated network cable 7 of the multi-channel data acquisition instrument connected. Among them, the strain signal input line 5 is used to transmit the signal collected by the sensor, the multi-channel data acquisition instrument 2 is used to collect the electrical signal output by the sensor during the test, and the PC terminal signal analysis system 3 is used for analysis and processing by the multi-channel data acquisition instrument 2 The collected electrical signal, and then the user can process and analyze the collected physical quantity to be measured in real time.

至此本发明所设计的所有实验装置安装完成,下面将通过几个实施例对连接好的实验装置进行进一步的说明:So far all the experimental devices designed by the present invention have been installed, and the connected experimental devices will be further described below through several embodiments:

实施例1Example 1

以风力机翼段模型质心位置对颤振影响的试验研究为例进行操作说明。Taking the experimental study of the influence of the centroid position of the wind turbine wing section model on flutter as an example, the operation is explained.

在风洞8未吹风时,通过将高精度数字倾角仪短暂固定到翼段模型9一端的端板10上,然后调节高强度扭转轴螺栓13相对于扭转轴固定杆41一端的扭转轴固定夹具的角度,再通过数字倾角仪显示的翼段模型9实时的倾角,将三种质心位置下的翼段模型9固定在同一攻角下,其中翼段模型9三种质心位置的调节是通过调节质心调节机构中质量块的位置来实现的。对于本发明公开的一种两自由度的气动弹性实验装置,在翼段模型9内部设置了三处用于固定质量块的螺栓通孔,分别对应于翼段模型9的三种质心位置,即气动中心-扭转轴中心(重心)(如图4所示);气动中心-重心-扭转轴中心(如图5所示);气动中心-扭转轴中心-重心(如图6所示)。三种质心位置下,质心与扭转轴中心的距离x与翼型弦长c的比值分别为0、+0.0303、-0.0623。然后在不同的质心位置下,通过逐步增加风洞风速,同时利用角位移传感器29、非接触式磁滞伸缩位移传感器30以及压力变送器4对试验数据进行采集,然后通过应变信号输入线5将传感器采集到的电信号传输到多通道数据采集仪2中,最后通过PC端信号分析系统3和多通道数据采集仪2对电信号的分析处理,进而转化为试验需要测量的翼段模型9的瞬时俯仰角、瞬时沉浮位移以及翼段模型9的表面压力信号。然后通过观察三种质心位置下翼段模型9的振动情况,进而确定三种质心位置下翼段模型9的颤振临界风速,然后对翼段模型9处于极限环振荡状态下俯仰、沉浮运动数据以及其表面的压力信号进行记录。最后通过探究翼段模型9质心位置对临界颤振速度的影响,进而找出翼段模型9的最优质心位置,实现对翼段模型9颤振边界的控制。When the wind tunnel 8 is not blowing, temporarily fix the high-precision digital inclinometer to the end plate 10 at one end of the wing model 9, and then adjust the high-strength torsion shaft bolt 13 relative to the torsion shaft fixing fixture at one end of the torsion shaft fixing rod 41 The angle of the wing section model 9 displayed by the digital inclinometer is used to fix the wing section model 9 under the three centroid positions at the same angle of attack, and the adjustment of the three centroid positions of the wing section model 9 is by adjusting The position of the mass block in the center of mass adjustment mechanism is realized. For a two-degree-of-freedom aeroelasticity experimental device disclosed in the present invention, three bolt through holes for fixing the mass blocks are provided inside the wing model 9, corresponding to the three centroid positions of the wing model 9, namely Aerodynamic center-torsion axis center (center of gravity) (as shown in Figure 4); pneumatic center-gravity center-torsion axis center (as shown in Figure 5); aerodynamic center-torsion axis center-gravity center (as shown in Figure 6). Under the three centroid positions, the ratios of the distance x between the centroid and the center of the torsion axis and the airfoil chord length c are 0, +0.0303, -0.0623 respectively. Then, at different centroid positions, by gradually increasing the wind speed in the wind tunnel, the angular displacement sensor 29, the non-contact magnetic hysteresis displacement sensor 30 and the pressure transmitter 4 are used to collect the test data at the same time, and then through the strain signal input line 5 The electrical signal collected by the sensor is transmitted to the multi-channel data acquisition instrument 2, and finally the electrical signal is analyzed and processed by the PC terminal signal analysis system 3 and the multi-channel data acquisition instrument 2, and then converted into the wing section model that needs to be measured in the test9 The instantaneous pitch angle, the instantaneous ups and downs displacement and the surface pressure signal of the wing section model 9. Then by observing the vibration of the wing section model 9 under the three centroid positions, the flutter critical wind speed of the wing section model 9 under the three centroid positions is determined, and then the pitching and heaving motion data of the wing section model 9 in the limit cycle oscillation state are determined. And the pressure signal on its surface is recorded. Finally, by exploring the influence of the position of the centroid of the wing model 9 on the critical flutter velocity, the optimal centroid position of the wing model 9 is found to realize the control of the flutter boundary of the wing model 9 .

实施例2Example 2

以探究低速风洞中翼型失速颤振的分岔行为为例进行操作说明。Taking the bifurcation behavior of airfoil stall flutter in a low-speed wind tunnel as an example to illustrate the operation.

通过在翼段模型9上安装质量块将翼段模型9的质心位置固定后,在风洞8未吹风时,调节翼段模型9的攻角到某一角度。接着开启风洞8,通过利用压力变送器4、测压管6、翼段模型9内部的空气流道22以及测压孔11对翼段模型9表面跨中位置处的气流压力进行测量,进而测得压力信号,同时结合角位移传感器29测得的瞬时俯仰角,进而得出翼段模型9的升力系数以及俯仰力矩系数随时间的变化曲线。同时结合翼段模型9瞬时俯仰、沉浮位移随时间的变化曲线判断翼段模型9经历的振动状态,当翼段模型9振动达到失速颤振状态时,记录翼段模型9俯仰角(沉浮位移、升力系数、俯仰力矩系数)所经历的极限环振动幅值随风洞风速的变化关系。接着改变翼段模型9在无风条件下的攻角,重复以上试验步骤,最终得出多组翼段模型9在不同攻角下,其俯仰角(沉浮位移、升力系数、俯仰力矩系数)所经历的极限环振动幅值随风洞风速的变化关系,进而从中探究翼段模型9在失速颤振时其经历的分岔行为。After the mass center position of the wing section model 9 is fixed by installing mass blocks on the wing section model 9, when the wind tunnel 8 is not blowing, adjust the angle of attack of the wing section model 9 to a certain angle. Then the wind tunnel 8 is opened, and the air flow pressure at the mid-span position on the surface of the wing section model 9 is measured by utilizing the pressure transmitter 4, the pressure measuring tube 6, the air passage 22 inside the wing section model 9, and the pressure measuring hole 11, Then the pressure signal is measured, combined with the instantaneous pitch angle measured by the angular displacement sensor 29 , and then the lift coefficient and the pitch moment coefficient of the wing section model 9 are obtained. Simultaneously in conjunction with wing section model 9 instantaneous pitch, the change curve of ups and downs displacement with time judges the vibration state that wing section model 9 experiences, when wing section model 9 vibrations reach stall flutter state, record wing section model 9 pitch angles (heavy displacement, ups and downs displacement, The relationship between the limit cycle vibration amplitude experienced by the lift coefficient and the pitching moment coefficient and the wind speed in the wind tunnel. Then change the angle of attack of the wing section model 9 under the condition of no wind, repeat the above test steps, and finally obtain that the pitch angle (heavy displacement, lift coefficient, pitch moment coefficient) of multiple groups of wing section models 9 under different angles of attack The relationship between the amplitude of the experienced limit cycle vibration and the wind speed in the wind tunnel is used to explore the bifurcation behavior of the airfoil model 9 during stall flutter.

实施例3Example 3

以机翼失速颤振时其表面的流动分离现象为例进行操作说明。The operation is explained by taking the flow separation phenomenon on the surface of the wing when it stalls and flutters as an example.

通过在翼段模型9上安装质量块将翼段模型9的质心位置固定后,在风洞8未吹风时,调节翼段模型9的攻角到某一角度。接着开启风洞8,当翼段模型9振动达到失速颤振状态时,通过利用压力变送器4、测压管6、翼段模型9内部的空气流道22以及测压孔11对翼段模型9表面跨中位置处的气流压力进行测量,进而研究翼段模型9在经历不同俯仰角时,翼段模型9上下表面压力系数随翼型弦长的变化情况,进而分析翼段模型9表面的气动特性。此外还可以结合粒子图像测速技术对翼段模型9表面的流动分离情况进行进一步的研究,从而与压力变送器4测得的翼段模型9表面的压力变化趋势进行对照比较,进而对翼段模型9的诱发失速颤振的机理进行探究。After the mass center position of the wing section model 9 is fixed by installing mass blocks on the wing section model 9, when the wind tunnel 8 is not blowing, adjust the angle of attack of the wing section model 9 to a certain angle. Then open the wind tunnel 8, when the vibration of the wing section model 9 reaches the stall flutter state, by using the pressure transmitter 4, the pressure measuring tube 6, the air flow channel 22 inside the wing section model 9 and the pressure measuring hole 11 to the wing section The airflow pressure at the mid-span position on the surface of the model 9 is measured, and then the variation of the pressure coefficient of the upper and lower surfaces of the wing model 9 with the airfoil chord length is studied when the wing model 9 experiences different pitch angles, and then the surface of the wing model 9 is analyzed. aerodynamic characteristics. In addition, the flow separation on the surface of the airfoil model 9 can be further studied in combination with the particle image velocimetry technology, so that it can be compared with the pressure change trend on the surface of the airfoil model 9 measured by the pressure transmitter 4, and then the airfoil section The mechanism of the induced stall flutter of model 9 is explored.

以上对本发明的具体实施例进行了描述。需要理解的是,本发明并不局限于上述特定实施方式,本领域技术人员可以在权利要求的范围内做出各种变形或修改,这并不影响本发明的实质内容。Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention.

Claims (10)

1. The two-degree-of-freedom aeroelasticity experimental device is characterized in that: the device comprises a wind tunnel experiment model, a two-degree-of-freedom supporting mechanism and a signal acquisition system;
the wind tunnel experimental model comprises a wing section model, 16-28 pressure measuring pipes, two end plates, a set of central torsion shaft, a set of locking mechanism and a set of mass center adjusting mechanism;
the wing section model is manufactured through 3D printing, a through hole for placing a bolt is designed in the wing section model, 8-14 pressure measuring holes with the diameter of 1.6mm are respectively designed on the upper surface and the lower surface of the middle position of the wing section model span, the 8-14 pressure measuring holes are all arranged along the normal direction of the wing section surface, the pressure measuring holes are connected with a pressure measuring pipe through an air flow channel designed in the wing section model, and the pressure measuring pipe extends out of the wind tunnel and is connected with a pressure transmitter;
the two end plates are manufactured through 3D printing, contain hollow designs with the same hollow shapes as the section of the wing section model, and are connected to the two ends of the wing section model through locking mechanisms so as to prevent the end effect of the wing section and ensure that the flow is quasi two-dimensional flow;
the set of central torsion shaft comprises a high-strength torsion shaft bolt, a torsion shaft locknut and an anti-slip sheet, wherein the high-strength torsion shaft bolt penetrates through the anti-slip sheet, the two end plates and a through hole reserved in the wing section model and used for placing a bolt, is connected with a torsion shaft fixing rod on the two-freedom-degree supporting mechanism and is fixed by the torsion shaft locknut, and one part of the anti-slip sheet is embedded into the end plate on one side far away from the supporting mechanism and is fixedly connected with the head of the high-strength torsion shaft bolt so as to prevent the central torsion shaft and the wing section model from sliding relatively;
the locking mechanism is positioned at the position, close to the rear edge, of the wing section model and comprises a fixing bolt and a locknut, the fixing bolt connects the wing section model and the two end plates together through the end plates and through holes, reserved in the wing section model, for placing bolts, and the fixing bolt is fixed by the locknuts;
the set of mass center adjusting mechanism comprises two conventional mass blocks, two eccentric mass blocks and a set of mass block fixing mechanism; the two conventional mass blocks are made of brass, holes are formed in the centers of the two conventional mass blocks, the two eccentric mass blocks are made of brass, holes are formed in the centers of the two eccentric mass blocks, and the weights of the eccentric mass blocks and the conventional mass blocks are the same; the two conventional mass blocks are used in combination and used for adjusting the mass center position of the wing section model to enable the mass center position to be closer to the center of the torsion shaft, so that the wing section model forms a three-center relative position relation of a pneumatic center and the center of the torsion shaft from the front edge to the rear edge; the two eccentric mass blocks are used in combination and used for adjusting the mass center position of the wing section model to enable the mass center position to be closer to the front edge of the wing section model, so that the wing section model forms a three-center relative position relation of a pneumatic power center-gravity center-torsion shaft center from the front edge to the rear edge; the conventional mass block is combined with an eccentric mass block for use, and is used for adjusting the mass center position of the wing section model to enable the mass center position to be closer to the rear edge of the wing section model, so that the wing section model forms a three-center relative position relation of a pneumatic power center-torsion shaft center-gravity center from the front edge to the rear edge; the set of mass block fixing mechanisms are composed of mass block fixing bolts and mass block locknuts, and two mass blocks are respectively fixed on end plates on two sides of the wing section model by the mass block fixing bolts and the mass block locknuts according to the requirements on different mass center positions in the test, so that the change of the mass center position of the wing section model is realized;
the two-degree-of-freedom supporting mechanism comprises a wind tunnel fixing plate, a wind tunnel turbulence-resisting cover, two supporting plates, two linear brackets, an angular displacement sensor fixing flange, a torsion shaft fixing rod, two torsion supporting rods, four smooth linear straight rods, four groups of ups and downs elastic mechanisms, four groups of pitching linear springs, eight pitching spring connecting columns, eight linear sliding bearings, two spherical outside surface bearings, four sets of ups and downs limiting devices and eight sets of pitching limiting devices;
the signal acquisition system comprises 16-28 pressure transmitters, an angular displacement sensor, a non-contact hysteresis telescopic displacement sensor and a set of multichannel data acquisition and analysis system, wherein the pressure measurement ends of the 16-28 pressure transmitters are respectively connected with pressure measurement pipes led out from a wind tunnel, the other ends of the pressure transmitters are respectively connected with a signal acquisition channel of the multichannel data acquisition instrument through strain signal input lines, the angular displacement sensor is fixed on an angular displacement sensor fixing flange and further connected with a matched shaft hole of a torsion shaft fixing rod, the signal output end of the angular displacement sensor is connected with the signal acquisition channel of the multichannel data acquisition instrument through the strain signal input lines and used for acquiring an instantaneous pitch angle signal of a wind tunnel experimental model, the non-contact hysteresis telescopic displacement sensor is connected with a wind tunnel fixing plate, and the distance between the non-contact hysteresis telescopic displacement sensor and a floating magnet fixed on a linear bracket is 2mm; the up-and-down motion through the wind tunnel experiment model drives the linear motion of linear bracket and then drives the linear motion of floating magnet, and then measure the instantaneous ups and downs displacement of wind tunnel experiment model through the gliding distance of floating magnet on non-contact hysteresis extension displacement sensor's measuring staff, non-contact hysteresis extension displacement sensor's signal output part is connected on the signal acquisition passageway of multichannel data acquisition instrument through the signal input line that meets an emergency for gather the instantaneous ups and downs displacement signal of wind tunnel experiment model.
2. The two-degree-of-freedom aeroelasticity experimental device as claimed in claim 1, wherein: the inlet end of an air flow channel in the wing section model is in smooth connection with a pressure measuring hole, the outlet end of the air flow channel is located at the end part of the wing section model on one side provided with the supporting mechanism, and then the pressure of the surface of the wing section model is led out to a pressure transmitter located outside the wind tunnel by penetrating a pressure measuring pipe into the outlet end of the air flow channel at the end part of the wing section model.
3. The two-degree-of-freedom aeroelasticity experimental device as claimed in claim 1, wherein: the pressure measuring pipe is connected with an air flow channel inside the wing section model through one end and sealed by sealant at a joint, and the other end of the pressure measuring pipe is connected with a pressure measuring end of a pressure transmitter outside the wind tunnel, so that the surface pressure of the wing section model is measured.
4. The two-degree-of-freedom aeroelasticity experimental device as claimed in claim 1, wherein: the contact positions of the eccentric mass block and the end plate are provided with anti-skidding grooves so as to prevent the eccentric mass block from sliding relative to the end plate in the motion process of the wing section model.
5. The two-degree-of-freedom aeroelasticity experimental apparatus as claimed in claim 1, wherein: the wind tunnel fixing plate is used for fixing the two supporting plates, the wind tunnel anti-turbulence cover and the non-contact hysteresis telescopic displacement sensor, and is fixed on the side wall of the wind tunnel closed section through a wind tunnel fixing plate fixing bolt; the wind tunnel turbulence resisting cover is fixed on the wind tunnel fixing plate through a wind tunnel fixing plate fixing bolt, and a two-degree-of-freedom supporting mechanism outside the wind tunnel is covered inside the wind tunnel turbulence resisting cover and used for preventing the influence of an opening on the side wall of the wind tunnel on the airflow inside the wind tunnel; two backup pads include backup pad and bottom suspension fagging, fix on the wind-tunnel fixed plate through backup pad fixing bolt respectively, all be provided with the bolt hole of fixed ups and downs stop device and be used for the fixed recess of ups and downs elastic mechanism on last backup pad and the bottom suspension fagging, and go up and still be provided with the bolt hole of connecting smooth linear straight-bar on the backup pad, be provided with countersunk head bolt hole and the cylinder recess of connecting smooth linear straight-bar on two faces of bottom suspension fagging respectively.
6. The two-degree-of-freedom aeroelasticity experimental device as claimed in claim 1, wherein: the two linear brackets comprise an inner linear bracket and an outer linear bracket, the two linear brackets are respectively provided with a through hole for penetrating through the smooth linear straight rod and the torsion shaft fixing rod and a groove for fixing an outer spherical surface bearing, a linear sliding bearing and a sinking-floating elastic mechanism, in addition, a bolt hole for fixing a pitching spring connecting column and a pitching limiting device is also arranged, and the outer linear bracket is also provided with a bolt hole for fixing a fixing flange of the angular displacement sensor; the eight linear sliding bearings and the eight sinking and floating linear spring fixing seats are fixed in grooves formed in the linear brackets through sinking and floating elastic mechanism fixing bolts, and the two linear brackets are respectively suspended between the upper supporting plate and the lower supporting plate through four groups of sinking and floating elastic mechanisms; the middle parts of the two linear brackets are respectively provided with an outer spherical bearing, the torsion shaft fixing rod is connected with the linear brackets through the outer spherical bearings, the two linear brackets are respectively connected with eight pitching spring connecting columns and two torsion supporting rods through four groups of pitching linear springs, so that pitching restoring moment of the wind tunnel experiment model is provided, and floating magnets matched with the non-contact hysteresis telescopic displacement sensor for use are further installed on the side edges of the inner side linear brackets, so that sinking and floating motion data of the wind tunnel experiment model can be collected in real time.
7. The two-degree-of-freedom aeroelasticity experimental apparatus as claimed in claim 1, wherein: the eight pitching limiting devices are used for limiting the large displacement phenomenon of the wind tunnel experiment model in the pitching motion process so as to prevent the damage of the two-degree-of-freedom supporting mechanism and the sensor system caused by the overlarge pitching displacement; each set of pitching limiting device is composed of a pitching limiting device metal fixing piece, four pitching limiting device metal fixing piece connecting bolts, a pitching limiting device rubber brake block, two pitching limiting device countersunk head connecting bolts and two pitching limiting device countersunk head connecting bolt matching nuts, wherein the eight pitching limiting device metal fixing pieces are fixed on the two linear brackets through thirty-two pitching limiting device metal fixing piece connecting bolts respectively, then the sixteen pitching limiting device countersunk head connecting bolts penetrate through the eight pitching limiting device rubber brake blocks respectively, and are fixed on the eight pitching limiting device metal fixing pieces through the sixteen pitching limiting device countersunk head connecting bolt matching nuts.
8. The two-degree-of-freedom aeroelasticity experimental apparatus as claimed in claim 1, wherein: the angular displacement sensor fixing flange is fixed on the outer linear bracket, and the angular displacement sensor, the linear bracket and the torsion shaft fixing rod are fixed together, so that pitching motion of the wind tunnel experiment model can be measured while the wind tunnel experiment model performs sinking and floating motion; one end of the torsion shaft fixing rod is provided with a torsion shaft fixing clamp, and the other end of the torsion shaft fixing rod is provided with a connecting port matched with the angular displacement sensor and respectively connected with the two linear brackets through two spherical outside bearings; the torsion strut vertically penetrates through the torsion shaft fixing rod, is fixed on the torsion shaft fixing rod through a torsion strut fixing bolt, and is respectively connected with two torsion struts and eight pitching spring connecting columns through four groups of pitching linear springs for converting the pitching motion of the wind tunnel experiment model into the linear motion of the pitching linear springs; one end of each of the four smooth linear straight rods is provided with a thread, and the other end of each of the four smooth linear straight rods is provided with a bolt hole; the four groups of sinking and floating elastic mechanisms comprise eight sinking and floating linear springs, sixteen sinking and floating linear spring fixing seats, sixty-four U-shaped bolts and sixty-four matched nuts of the U-shaped bolts, wherein each sinking and floating elastic mechanism respectively fixes two ends of one sinking and floating linear spring on the two sinking and floating linear spring fixing seats through the eight U-shaped bolts and the eight matched nuts of the U-shaped bolts, 8 sinking and floating linear springs in the four groups of sinking and floating elastic mechanisms adopt pre-loaded extension springs, one end of each sinking and floating elastic mechanism is connected on a supporting plate through a sinking and floating elastic mechanism fixing bolt, the other end of each sinking and floating elastic mechanism is connected on a linear bracket through a sinking and floating elastic mechanism fixing bolt, and the two groups of sinking and floating elastic mechanisms form a group, and one linear bracket is suspended through the two groups of sinking and floating elastic mechanisms, the linear bracket and the wind tunnel experiment model connected with the linear bracket are suspended between an upper supporting plate and a lower supporting plate, so that when the wind tunnel experiment model is subjected to the action force of air flow in a wind tunnel to perform up-and-down sinking and floating movement, restoring force is provided for the wind tunnel experiment model in the sinking and floating movement, four groups of pitching linear springs adopt preloaded extension springs, two pitching linear springs positioned at two sides of a torsion support rod on one side of the linear bracket are taken as one group, torsion restoring moment is provided for the wind tunnel experiment model in the pitching movement in a mode that one end of each pitching linear spring is fixed on a pitching spring connecting column, and the other end of each pitching linear spring connecting column is fixed on the torsion support rod penetrating through a torsion shaft fixing rod, and eight pitching spring connecting columns are connected through threads and fixed on the two linear brackets and are used for fixing the four groups of pitching linear springs; the eight linear sliding bearings are respectively connected with the sinking-floating linear spring fixing seats at one ends of the four groups of sinking-floating elastic mechanisms, the sinking-floating linear spring fixing seats with one ends of the sinking-floating elastic mechanisms connected with the linear sliding bearings are fixed in grooves formed in the inner linear bracket and the outer linear bracket by utilizing the sinking-floating elastic mechanism fixing bolts, so that the linear sliding bearings are fixedly connected with the linear brackets, and the eight linear sliding bearings are respectively fixed in the grooves at the connecting positions of the smooth linear straight rods and the linear brackets so as to reduce the friction force of the wind tunnel test model in the sinking-floating motion process; the two outer spherical bearings are respectively fixed at the connecting part of the torsion shaft fixing rod and the linear bracket so as to reduce the friction force of the wind tunnel experiment model in the pitching motion process; the four sets of sinking and floating limiting devices are used for limiting the large displacement phenomenon of the wind tunnel experimental model in the sinking and floating movement process so as to prevent the damage of the two-degree-of-freedom supporting mechanism and the sensor system caused by the excessive sinking and floating displacement; each set of sinking and floating limiting device consists of two sinking and floating limiting device metal supporting columns, a sinking and floating limiting device metal gasket, a sinking and floating limiting device rubber brake block and two sinking and floating limiting device countersunk head connecting bolts; wherein, the one end of the stop device metal support post that floats that sinks is provided with the screw thread, and the other end is provided with the bolt hole, and eight stop device metal support posts that float that sink are connected respectively in two upper and lower backup pads, then eight stop device countersunk head connecting bolt that float that sink pass four stop device rubber brake pads that float and four stop device metal gaskets that float that sink are connected in the bolt hole of eight stop device metal support post one side that float that sink respectively.
9. The two-degree-of-freedom aeroelasticity experimental device as claimed in claim 1, wherein: the set of multi-channel data acquisition and analysis system comprises: 18-30 strain signal input lines, a multichannel data acquisition instrument, PC end signal analysis system, 18-30 strain signal input lines are connected the signal input end of sensor output end and multichannel data acquisition instrument respectively for the signal of telecommunication that the transmission sensor was gathered.
10. The two-degree-of-freedom aeroelasticity experimental device as claimed in claim 1, wherein: the multichannel data acquisition instrument is used for acquiring electric signals output by the sensor in the test process, and the multichannel data acquisition instrument is connected with the PC end signal analysis system to convert the electric signals into identifiable physical quantity to be detected, the PC end signal analysis system is used for analyzing and processing the electric signals acquired by the multichannel data acquisition instrument, and then a user can process and analyze the acquired physical quantity to be detected in real time.
CN202210807650.1A 2022-07-12 2022-07-12 A two-degree-of-freedom aeroelasticity experimental device Pending CN115266001A (en)

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