CN115493822A - Engine blade simulated load fatigue test device and method - Google Patents
Engine blade simulated load fatigue test device and method Download PDFInfo
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Abstract
本申请提供了一种发动机叶片模拟载荷疲劳试验装置及方法,属于航空发动机技术领域,装置包括水平设置的安装基准,安装基准的中间区域安装有可移动调节的叶片支架,叶片支架上侧安装叶片;安装基准上还设有可移动的支撑框,支撑框位于叶片支架的两侧,支撑框内设有多点力学测量组件,多点力学测量组件靠近叶片支架的一端与叶片表面接触进行作用力施加,多点力学测量组件远离叶片支架的一端与供气系统连接,供气系统用于对多点力学测量组件提供作用力;发动机叶片模拟载荷疲劳试验装置还包括CCD相机,CCD相机用于获取叶片的变形情况。通过本申请的处理方案,提高了叶片载荷疲劳试验的精确性,并有效降低叶片模拟载荷疲劳试验成本。
The application provides a simulated load fatigue test device and method for engine blades, which belong to the technical field of aero-engines. The device includes a horizontal installation datum, a movable and adjustable blade bracket is installed in the middle area of the installation datum, and blades are installed on the upper side of the blade bracket. There is also a movable support frame on the installation basis, the support frame is located on both sides of the blade support, and a multi-point mechanical measurement component is arranged in the support frame, and the end of the multi-point mechanical measurement component close to the blade support contacts the surface of the blade for force Applying, the end of the multi-point mechanical measurement component away from the blade support is connected to the air supply system, and the gas supply system is used to provide force to the multi-point mechanical measurement component; the engine blade simulated load fatigue test device also includes a CCD camera, which is used to obtain Deformation of the leaves. Through the processing scheme of the present application, the accuracy of the blade load fatigue test is improved, and the cost of the blade simulated load fatigue test is effectively reduced.
Description
技术领域technical field
本申请涉及航空发动机技术领域,尤其涉及一种发动机叶片模拟载荷疲劳试验装置及方法。The present application relates to the technical field of aero-engines, in particular to an engine blade simulation load fatigue test device and method.
背景技术Background technique
叶片是航空发动机的核心部件之一,并在很大程度上影响航空发动机的性能水平。航空发动机叶片在实际运行过程中受到高气动载荷的作用而发生变形。由于其运行工况复杂,难以通过常用试验方法来获得其在不同工况下的变形情况,且试验的费用昂贵。因此,亟待提升发动机叶片的试验技术能力。The blade is one of the core components of an aero-engine, and affects the performance level of an aero-engine to a great extent. Aeroengine blades are deformed by high aerodynamic loads during actual operation. Due to its complex operating conditions, it is difficult to obtain its deformation under different working conditions through common test methods, and the cost of the test is expensive. Therefore, it is urgent to improve the test technology capability of engine blades.
现有的发动机叶片试验装置,施加作用力的位置及数量受到限制,无法满足精确模拟气动载荷对于叶片的疲劳损伤效果,无法满足发动机叶片模拟载荷疲劳试验的要求。The existing engine blade test device is limited in the position and quantity of the applied force, and cannot accurately simulate the fatigue damage effect of the aerodynamic load on the blade, and cannot meet the requirements of the simulated load fatigue test of the engine blade.
发明内容Contents of the invention
有鉴于此,本申请实施例提供一种发动机叶片模拟载荷疲劳试验装置及方法,以达到提升发动机叶片在复杂工况下抗疲劳性能测试精度、降低试验验证成本的目的。第一方面,本申请实施例提供一种发动机叶片模拟载荷疲劳试验装置,包括水平设置的安装基准,所述安装基准的中间区域安装有可移动调节的叶片支架,所述叶片支架上侧安装叶片;所述安装基准上还设有可移动的支撑框,所述支撑框位于所述叶片支架的两侧,所述支撑框内设有多点力学测量组件,所述多点力学测量组件靠近所述叶片支架的一端与所述叶片表面接触进行作用力施加,所述多点力学测量组件远离所述叶片支架的一端与供气系统连接,所述供气系统用于对所述多点力学测量组件提供作用力;In view of this, the embodiment of the present application provides a simulated load fatigue test device and method for engine blades, so as to achieve the purpose of improving the test accuracy of the fatigue resistance performance of engine blades under complex working conditions and reducing the cost of test verification. In the first aspect, the embodiment of the present application provides a simulated load fatigue test device for engine blades, which includes a horizontal installation reference, a movable and adjustable blade support is installed in the middle area of the installation reference, and blades are installed on the upper side of the blade support. ; The installation datum is also provided with a movable support frame, the support frame is located on both sides of the blade bracket, and a multi-point mechanical measurement assembly is arranged inside the support frame, and the multi-point mechanical measurement assembly is close to the One end of the blade support is in contact with the surface of the blade to apply force, and the end of the multi-point mechanical measurement assembly away from the blade support is connected to an air supply system, and the air supply system is used for the multi-point mechanical measurement Components provide force;
所述发动机叶片模拟载荷疲劳试验装置还包括CCD相机,所述CCD相机用于获取所述叶片的变形情况。The engine blade simulated load fatigue test device also includes a CCD camera, and the CCD camera is used to obtain the deformation of the blade.
根据本申请实施例的一种具体实现方式,所述叶片支架与所述安装基准之间依次设有纵向精密导轨、横向精密导轨、角度调节盘和纵向粗调导轨,所述纵向粗调导轨与所述安装基准连接,所述纵向精密导轨与所述叶片支架的底部连接。According to a specific implementation of the embodiment of the present application, a longitudinal precision guide rail, a horizontal precision guide rail, an angle adjustment disc, and a longitudinal coarse adjustment guide rail are sequentially provided between the blade bracket and the installation reference, and the longitudinal coarse adjustment guide rail is connected to the The installation reference is connected, and the longitudinal precision guide rail is connected with the bottom of the blade support.
根据本申请实施例的一种具体实现方式,所述支撑框与所述安装基准之间设有横向粗调导轨,所述支撑框沿所述横向粗调导轨移动调节。According to a specific implementation manner of the embodiment of the present application, a horizontal coarse adjustment guide rail is provided between the support frame and the installation reference, and the support frame is moved and adjusted along the horizontal coarse adjustment guide rail.
根据本申请实施例的一种具体实现方式,所述多点力学测量组件包括依次连接的力学探头、力学探针和作动轴,所述作动轴远离所述力学探针的一端与所述供气系统连接,所述力学探头、所述力学探针和所述作动轴在所述支撑框内均分别设置为多个;所述力学探针用于将作用力所述叶片表面,所述力学探头用于时时反馈作用在所述叶片表面的作用力。According to a specific implementation of the embodiment of the present application, the multi-point mechanical measurement assembly includes a mechanical probe, a mechanical probe, and an actuating shaft connected in sequence, and the end of the actuating shaft far away from the mechanical probe is connected to the The gas supply system is connected, and the mechanical probes, the mechanical probes and the actuating shafts are respectively arranged in multiples in the support frame; the mechanical probes are used to apply force to the blade surface, and the The mechanical probe is used to constantly feed back the force acting on the surface of the blade.
根据本申请实施例的一种具体实现方式,所述供气系统包括与所述作动轴连接的输气管、设置在所述输气管上的压力调节阀以及与所述输气管远离所述作动轴的一端连接的气源,通过调节所述压力调节阀调节所述作动轴的作用力大小。According to a specific implementation of the embodiment of the present application, the air supply system includes an air delivery pipe connected to the actuating shaft, a pressure regulating valve arranged on the air delivery pipe, and a The air source connected to one end of the actuating shaft is used to adjust the force of the actuating shaft by adjusting the pressure regulating valve.
第二方面,本申请实施例还提供一种发动机叶片模拟载荷疲劳试验方法,采用如上述第一方面任一实施例所述的发动机叶片模拟载荷疲劳试验装置,所述方法包括:In the second aspect, the embodiment of the present application also provides a simulated load fatigue test method for engine blades, using the engine blade simulated load fatigue test device as described in any embodiment of the first aspect above, the method comprising:
采用CCD相机视觉测量方法获得叶片在稳态外流场下的气动变形情况,用来分析校准叶片稳态气动流场仿真计算所需的边界参数及数学模型;Using the CCD camera visual measurement method to obtain the aerodynamic deformation of the blade under the steady-state external flow field, it is used to analyze and calibrate the boundary parameters and mathematical models required for the simulation calculation of the steady-state aerodynamic flow field of the blade;
将叶片非稳态气动流场的运行过程拆分为多个典型的瞬态状态;Split the operation process of blade unsteady aerodynamic flow field into several typical transient states;
采用所获得的边界参数及数学模型,数值仿真瞬态下的叶片气动外流场;Using the obtained boundary parameters and mathematical models, numerically simulate the aerodynamic external flow field of the blade under transient state;
安装叶片到安装基准,标定叶片的空间位置;Install the blade to the installation datum, and calibrate the spatial position of the blade;
叶片结构空间网格离散化,确定特征位置;Discretization of blade structure space grid to determine feature position;
基于特征位置及流场仿真数据,计算获得对叶片表面施加的载荷,通过作动轴作用于力学探头并对实际叶片进行施加载荷;Based on the characteristic position and flow field simulation data, calculate the load applied to the blade surface, act on the mechanical probe through the actuating shaft and apply the load to the actual blade;
通过CCD相机获得叶片不同特征位置的变形,与叶片不同特征位置变形仿真值比较,若偏差值满足试验要求,记录该瞬态下的载荷大小及方向排布,否则将调整特征位置的选取;Obtain the deformation of different characteristic positions of the blade through the CCD camera, and compare it with the simulation value of the deformation of different characteristic positions of the blade. If the deviation value meets the test requirements, record the magnitude and direction of the load under the transient state, otherwise the selection of the characteristic position will be adjusted;
重复以上过程,开展下一个瞬态的外流场气动仿真载荷数据确定,形成载荷数据记录;Repeat the above process to determine the load data of the next transient external flow field aerodynamic simulation to form a load data record;
将记录位置及载荷数据形成载荷谱,施加于叶片,模拟在非稳态、循环载荷下的叶片载荷疲劳性能;The recorded position and load data are formed into a load spectrum, which is applied to the blade to simulate the load fatigue performance of the blade under unsteady and cyclic loads;
通过CCD相机观测并记录叶片的变形情况,评估抗疲劳性能。The deformation of the blade is observed and recorded by the CCD camera to evaluate the fatigue resistance.
根据本申请实施例的一种具体实现方式,所述基于特征位置及流场仿真数据,计算获得对叶片表面施加的载荷,通过作动轴作用于力学探头并对实际叶片进行施加载荷的步骤包括:According to a specific implementation of the embodiment of the present application, the step of calculating and obtaining the load applied to the surface of the blade based on the characteristic position and flow field simulation data, acting on the mechanical probe through the actuating shaft and applying the load to the actual blade includes: :
将叶片流场仿真几何模型坐标与试验装置空间坐标标定一致;The coordinates of the simulation geometric model of the blade flow field are calibrated consistent with the spatial coordinates of the test device;
基于特征位置及叶片外流场仿真数据,完成基于特征位置的仿真载荷局部面积分,获取载荷沿面法向分量;Based on the characteristic position and the simulation data of the external flow field of the blade, the local area integration of the simulation load based on the characteristic position is completed, and the normal component of the load along the surface is obtained;
提取特征位置的载荷沿面法向分量,传递给作动轴;Extract the normal component of the load along the feature position and transmit it to the actuating axis;
将特征位置与布置力学探头的测点位置一一对应,基于特征位置、法向载荷仿真数据,力学探头对实际叶片施加法向分量。The characteristic position is one-to-one corresponding to the position of the measuring point where the mechanical probe is arranged. Based on the characteristic position and the normal load simulation data, the mechanical probe applies the normal component to the actual blade.
根据本申请实施例的一种具体实现方式,在所述叶片结构空间网格离散化,确定特征位置的步骤中,所述特征位置的确定因素包括:According to a specific implementation manner of the embodiment of the present application, in the step of discretizing the spatial grid of the blade structure and determining the characteristic position, the determining factors of the characteristic position include:
叶片结构空间网格离散化方式;Discretization method of blade structural space grid;
力学探头及力学探针的空间分辨率,空间分辨率取决于力学探头及力学探针在支撑框上的分布数量和排列方式;The spatial resolution of mechanical probes and mechanical probes, the spatial resolution depends on the number and arrangement of mechanical probes and mechanical probes on the support frame;
叶片结构研究位置的选取。Selection of location for blade structure study.
根据本申请实施例的一种具体实现方式,所述通过力学探头对叶片进行施加载荷的步骤中,施加载荷是对叶片的压力面单独施加,或者是对叶片的压力面和吸力面双向施加。According to a specific implementation of the embodiment of the present application, in the step of applying a load to the blade by the mechanical probe, the load is applied to the pressure surface of the blade alone, or bidirectionally applied to the pressure surface and the suction surface of the blade.
根据本申请实施例的一种具体实现方式,所述特征位置的选取数量大于等于3个,所述叶片非稳态气动流场的运行过程拆分的典型的瞬态状态的数量大于等于2个。According to a specific implementation of the embodiment of the present application, the number of selected characteristic positions is greater than or equal to 3, and the number of typical transient states split by the operating process of the unsteady aerodynamic flow field of the blade is greater than or equal to 2 .
有益效果Beneficial effect
本申请实施例中的发动机叶片模拟载荷疲劳试验装置及方法,通过设置多点力学测量组件,采用多点接触的方式对叶片进行测试,能够更加精确地反映不同位置的载荷情况,能精确模拟发动机叶片在受到不同气动载荷过程中所受到的疲劳载荷情况,为叶片的抗疲劳强度优化提供测试手段,且有效降低不同工况下叶片测试试验成本。The engine blade simulation load fatigue test device and method in the embodiment of the application can more accurately reflect the load conditions at different positions by setting up multi-point mechanical measurement components and adopting a multi-point contact method to accurately simulate the engine The fatigue loads of the blades under different aerodynamic loads provide testing methods for the optimization of the fatigue strength of the blades, and effectively reduce the cost of blade testing under different working conditions.
附图说明Description of drawings
为了更清楚地说明本申请实施例的技术方案,下面将对实施例中所需要使用的附图作简单地介绍,显而易见地,下面描述中的附图仅仅是本申请的一些实施例,对于本领域普通技术人员来讲,在不付出创造性劳动的前提下,还可以根据这些附图获得其它的附图。In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the accompanying drawings that need to be used in the embodiments. Obviously, the accompanying drawings in the following description are only some embodiments of the present application. Those of ordinary skill in the art can also obtain other drawings based on these drawings without any creative effort.
图1为根据本发明一实施例的发动机叶片模拟载荷疲劳试验装置侧视图;Fig. 1 is a side view of an engine blade simulated load fatigue test device according to an embodiment of the present invention;
图2为根据本发明一实施例的发动机叶片模拟载荷疲劳试验装置俯视图;Fig. 2 is a top view of an engine blade simulated load fatigue test device according to an embodiment of the present invention;
图3为根据本发明一实施例的发动机叶片模拟载荷疲劳试验装置工作侧视图;Fig. 3 is a working side view of an engine blade simulated load fatigue test device according to an embodiment of the present invention;
图4为根据本发明一实施例的发动机叶片模拟载荷疲劳试验装置工作俯视图;Fig. 4 is a working top view of an engine blade simulated load fatigue test device according to an embodiment of the present invention;
图5为根据本发明一实施例的发动机叶片模拟载荷疲劳试验装置工作示意图;Fig. 5 is a working schematic diagram of an engine blade simulated load fatigue test device according to an embodiment of the present invention;
图6为根据本发明一实施例的发动机叶片结构示意图;Fig. 6 is a schematic structural diagram of an engine blade according to an embodiment of the present invention;
图7为根据本发明一实施例的发动机叶片模拟载荷疲劳试验装置叶片安装图;Fig. 7 is a blade installation diagram of an engine blade simulated load fatigue test device according to an embodiment of the present invention;
图8为根据本发明一实施例的发动机叶片模拟载荷疲劳试验装置工作安装示意图;Fig. 8 is a schematic diagram of working and installation of an engine blade simulated load fatigue test device according to an embodiment of the present invention;
图9为根据本发明一实施例的发动机叶片模拟载荷疲劳试验装置测试方法;Fig. 9 is a test method of an engine blade simulated load fatigue test device according to an embodiment of the present invention;
图10为根据本发明一实施例的发动机叶片模拟载荷疲劳试验方法叶片网格图;Fig. 10 is a blade grid diagram of an engine blade simulated load fatigue test method according to an embodiment of the present invention;
图11为根据本发明一实施例的发动机叶片模拟载荷疲劳试验方法叶片受载荷模拟示意图;Fig. 11 is a schematic diagram of a simulated load simulation method for a blade of an engine blade according to an embodiment of the present invention;
图12为根据本发明一实施例的发动机叶片模拟载荷疲劳试验装置力学探头对叶片施加载荷示意图。Fig. 12 is a schematic diagram of a mechanical probe applying a load to a blade of an engine blade simulated load fatigue test device according to an embodiment of the present invention.
图中:1、叶片;1-1、压力面;1-2、吸力面;1-3、叶尖;1-4、榫根;1-5、叶前缘;1-6、叶后缘;2、力学探头;3、力学探针;4、作动轴;5、支撑框;6、输气管;7、压力调节阀;8、气源;9、安装基准;10、叶片支架;11、纵向精密导轨;12、横向精密导轨;13、角度调节盘;14、纵向粗调导轨;15、横向粗调导轨;16、CCD相机;17、特征位置。In the figure: 1, blade; 1-1, pressure surface; 1-2, suction surface; 1-3, blade tip; 1-4, tenon root; 1-5, leaf leading edge; 1-6, leaf trailing edge ;2. Mechanical probe; 3. Mechanical probe; 4. Actuating shaft; 5. Support frame; 6. Air pipe; 7. Pressure regulating valve; 8. Air source; 1. Longitudinal precision guide rail; 12. Horizontal precision guide rail; 13. Angle adjustment disc; 14. Longitudinal coarse adjustment guide rail; 15. Horizontal coarse adjustment guide rail; 16. CCD camera; 17. Characteristic position.
具体实施方式detailed description
下面结合附图对本申请实施例进行详细描述。Embodiments of the present application will be described in detail below in conjunction with the accompanying drawings.
以下通过特定的具体实例说明本申请的实施方式,本领域技术人员可由本说明书所揭露的内容轻易地了解本申请的其他优点与功效。显然,所描述的实施例仅仅是本申请一部分实施例,而不是全部的实施例。本申请还可以通过另外不同的具体实施方式加以实施或应用,本说明书中的各项细节也可以基于不同观点与应用,在没有背离本申请的精神下进行各种修饰或改变。需说明的是,在不冲突的情况下,以下实施例及实施例中的特征可以相互组合。基于本申请中的实施例,本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其他实施例,都属于本申请保护的范围。Embodiments of the present application are described below through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Apparently, the described embodiments are only some of the embodiments of this application, not all of them. The present application can also be implemented or applied through other different specific implementation modes, and various modifications or changes can be made to the details in this specification based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the case of no conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of this application.
要说明的是,下文描述在所附权利要求书的范围内的实施例的各种方面。应显而易见,本文中所描述的方面可体现于广泛多种形式中,且本文中所描述的任何特定结构及/或功能仅为说明性的。基于本申请,所属领域的技术人员应了解,本文中所描述的一个方面可与任何其它方面独立地实施,且可以各种方式组合这些方面中的两者或两者以上。举例来说,可使用本文中所阐述的任何数目个方面来实施设备及/或实践方法。另外,可使用除了本文中所阐述的方面中的一或多者之外的其它结构及/或功能性实施此设备及/或实践此方法。It is noted that the following describes various aspects of the embodiments that are within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is illustrative only. Based on the present application one skilled in the art should appreciate that an aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, any number of the aspects set forth herein can be used to implement an apparatus and/or practice a method. In addition, such an apparatus may be implemented and/or such a method practiced using other structure and/or functionality than one or more of the aspects set forth herein.
还需要说明的是,以下实施例中所提供的图示仅以示意方式说明本申请的基本构想,图式中仅显示与本申请中有关的组件而非按照实际实施时的组件数目、形状及尺寸绘制,其实际实施时各组件的型态、数量及比例可为一种随意的改变,且其组件布局型态也可能更为复杂。It should also be noted that the diagrams provided in the following embodiments are only schematically illustrating the basic idea of the application, and only the components related to the application are shown in the drawings rather than the number, shape and number of components in actual implementation. Dimensional drawing, the type, quantity and proportion of each component can be changed arbitrarily during actual implementation, and the component layout type may also be more complicated.
另外,在以下描述中,提供具体细节是为了便于透彻理解实例。然而,所属领域的技术人员将理解,可在没有这些特定细节的情况下实践所述方面。Additionally, in the following description, specific details are provided to facilitate a thorough understanding of examples. However, it will be understood by those skilled in the art that the described aspects may be practiced without these specific details.
申请人研究发现,目前的现有技术中公开了一种气动热力联合试验系统及试验方法,该试验舱的两侧分别与电弧加热器、风洞附属设备连接,能尽可能真实的模拟气动环境及开展强度考核,试验设备自身干扰小。但该设备实现叶片在复杂工况下的疲劳性能试验难度较大、费用昂贵。The applicant's research found that the current prior art discloses an aerodynamic-thermal joint test system and test method. The two sides of the test chamber are respectively connected with the arc heater and the auxiliary equipment of the wind tunnel, which can simulate the aerodynamic environment as realistically as possible. And carry out strength assessment, the test equipment itself has little interference. However, it is difficult and expensive for this equipment to realize the fatigue performance test of blades under complex working conditions.
另一种关于航空发动机涡轮转子叶片弯曲刚度试验装置的技术,该装置通过采用电动推杆来完成对涡轮转子叶片的载荷施加,以完成对弯曲载荷的模拟。而另一个现有技术公开了一种航空发动机叶片试验装置,且至少一个支撑件的支撑部的方位会随着叶片试样的变形而自动调整,从而避免因支撑位置和方位不协调而导致附加载荷的引入,提高施加载荷的准确性和试验的准确性。但以上专利无法精确模拟叶片在实际运行过程中所受到的复杂、耦合的气动力,施加作用力的位置及数量受到限制。Another technology related to the bending stiffness test device of the turbine rotor blade of the aero-engine, the device completes the load application on the turbine rotor blade by using the electric push rod to complete the simulation of the bending load. And another prior art discloses an aeroengine blade test device, and the orientation of the support part of at least one support member can be automatically adjusted along with the deformation of the blade sample, thereby avoiding additional damage caused by uncoordinated support position and orientation. The introduction of the load improves the accuracy of the applied load and the accuracy of the test. However, the above patents cannot accurately simulate the complex and coupled aerodynamic forces experienced by the blades during actual operation, and the position and amount of force applied are limited.
另一种关于材料高低周复合疲劳性能原位测试装置及方法的技术,低频载荷加载模块采用伺服液压驱动,高频载荷加载模块采用电磁谐振驱动,并可完成原位监测,用于实现对试样疲劳裂纹萌生、扩展以及断裂过程的高分辨率可视化动态监测。但该装置施加的节点数量有限,无法实现密集的作用力施加,无法满足精确模拟气动载荷对于叶片的疲劳损伤效果。Another technology related to the in-situ test device and method for the high-low cycle composite fatigue performance of materials. The low-frequency load loading module is driven by servo hydraulics, and the high-frequency load loading module is driven by electromagnetic resonance, and in-situ monitoring can be completed to realize the test High-resolution visual dynamic monitoring of sample fatigue crack initiation, growth and fracture process. However, the number of nodes applied by this device is limited, and intensive force application cannot be realized, and the accurate simulation of the fatigue damage effect of aerodynamic load on the blade cannot be satisfied.
申请人为解决上述现有技术存在的问题,经过努力试验研究,开发了一种发动机叶片模拟载荷疲劳试验装置及方法,下面参照图1至图12进行详细描述。In order to solve the above-mentioned problems in the prior art, the applicant has developed an engine blade simulated load fatigue test device and method through diligent testing and research, which will be described in detail below with reference to FIGS. 1 to 12 .
第一方面,本申请实施例提供一种发动机叶片模拟载荷疲劳试验装置,参照图1和图2,包括水平设置的安装基准9,安装基准9的中间区域安装有可移动调节的叶片支架10,叶片支架10上侧安装叶片1;安装基准9上还设有可移动的支撑框5,支撑框5位于叶片支架10的两侧,支撑框5内设有多点力学测量组件,多点力学测量组件靠近叶片支架10的一端与叶片1表面接触进行作用力施加,多点力学测量组件远离叶片支架10的一端与供气系统连接,供气系统用于对多点力学测量组件提供作用力;发动机叶片模拟载荷疲劳试验装置还包括CCD相机16(charge coupled device,电荷耦合器件),CCD相机16用于获取叶片1的变形情况。In the first aspect, the embodiment of the present application provides a simulated load fatigue test device for engine blades, referring to Fig. 1 and Fig. 2, including a horizontally arranged
在一个实施例中,多点力学测量组件包括依次连接的力学探头2、力学探针3和作动轴4,作动轴4远离力学探针3的一端与供气系统连接,力学探头2、力学探针3和作动轴4在支撑框5内均分别设置为多个,每组力学探头2、力学探针3和作动轴4可单独调节,力学探针3用于将作用力作用于叶片表面,力学探头2用于时时反馈作用在叶片表面的作用力。安装时,发动机叶片1安装在叶片支架10上,实现结构的精确定位,力学探头2与力学探针3集成在一起,作动轴4通过力学探针3作用于力学探头2,用于对发动机叶片1的压力面1-1及吸力面1-2施加作用力,其作动能力来源于供气系统。In one embodiment, the multi-point mechanical measurement assembly includes a
在一个实施例中,叶片支架10与安装基准9之间依次设有纵向精密导轨11、横向精密导轨12、角度调节盘13和纵向粗调导轨14,纵向粗调导轨14与安装基准9连接,纵向精密导轨11与叶片支架10的底部连接。在发动机叶片1的检测过程中,需要精确调节叶片1与力学探头2及力学探针3的相对位置,将叶片1在实际载荷中所受到的气动力等效为力学探头2所施加的特定挤压载荷,并检验叶片1在特定载荷中的实际变形情况,并与数值仿真计算结果进行对比校准,以最终形成一套成熟的计算及仿真方法,最终为检验叶片1在不同的运行工况下的变形情况提供技术条件。调节相对位置主要是通过调节叶片1自身的空间位置,通过调节横向精密导轨12、纵向精密导轨11、角度调节盘13、纵向粗调导轨14以实现对叶片1空间位置的精确调节。In one embodiment, between the
进一步的,支撑框5与安装基准9之间设有横向粗调导轨15,支撑框5沿横向粗调导轨15移动调节,通过横向粗调导轨15实现支撑框5与叶片1空间距离的大幅度调整。通过以上调节机构,能够确保叶片流场仿真几何模型坐标与试验装置测试空间坐标标定一致,使得通过叶片流场仿真获得的特征位置的局部面积分理论法向分量能够精准作用于实际的叶片表面位置,使得叶片1的数值仿真工况和试验测试工况保持一致,提升模拟载荷疲劳试验装置的测试准确性。Further, a horizontal coarse
在一个实施例中,供气系统包括与作动轴4连接的输气管6、设置在输气管6上的压力调节阀7以及与输气管6远离作动轴4的一端连接的气源8,通过调节压力调节阀7调节力学探针3的作用力大小。In one embodiment, the air supply system includes an
参照图3至图5,在实际运行中,支撑框5中的力学探针3按照设计的位置及作用力作用于叶片1的表面,而力学探针3前缘的力学探头2时时反馈作用在叶片表面的作用力。通过调整叶片支架10、横向粗调导轨15等结构相对于叶片1的位置以模拟在实际运行中的模拟气动载荷的作用方向,从而精准模拟叶片1在实际过程中所受到的气动作用力。在施加模拟气动载荷时,采用多点接触的方式,能够更加精确地反映不同位置的载荷情况。施加载荷过程可以是在叶片1的压力面单独施加,也可以是在叶片1的压力面及吸力面双向施加。施加载荷过程中,叶片1每个面的接触点的位置(特征位置17)不少于3个。实际施加载荷过程中,力学探针3的施加力范围可以覆盖叶片1全部特征。Referring to Figures 3 to 5, in actual operation, the
参照图6,为叶片1结构的示意图,叶片包含压力面1-1、吸力面1-2、叶尖1-3、榫根1-4、叶前缘1-5、叶后缘1-6。主要施加载荷的位置为叶片1的压力面1-1、吸力面1-2,且叶片1的榫根1-4主要用于实现叶片1的空间位置的精确定位。Referring to Figure 6, it is a schematic diagram of the structure of the
参照图7和图8,叶片支架10是用来与叶片1的榫根1-4结构配合,并固定在测试系统中。横向精密导轨12、纵向精密导轨11组合并用于精密、小幅度调节叶片1在平面内的空间坐标位置,角度调节盘13用于调节叶片1在平面内与力学探针3的空间夹角。纵向粗调导轨14用于大幅度调节叶片1在平面内的空间坐标位置。因此,测试系统主要是通过横向粗调导轨15、纵向粗调导轨14的粗调实现叶片1的初步定位,通过横向精密导轨12、纵向精密导轨11实现叶片1的精确定位,通过角度调节盘13实现叶片1相对力学探针3的空间夹角定位。Referring to Fig. 7 and Fig. 8, the
第二方面,本申请实施例还提供一种发动机叶片模拟载荷疲劳试验方法,采用如第一方面任一实施例的发动机叶片模拟载荷疲劳试验装置,参照图9,该方法包括:In the second aspect, the embodiment of the present application also provides a simulated load fatigue test method for engine blades, using the engine blade simulated load fatigue test device as in any embodiment of the first aspect, referring to FIG. 9 , the method includes:
步骤1、采用CCD相机16视觉测量方法获得叶片在稳态外流场下的气动变形情况,用来分析校准叶片稳态气动流场仿真计算所需的边界参数及数学模型。
步骤2、将叶片非稳态气动流场的运行过程拆分为多个典型的瞬态状态。
步骤3、采用所获得的边界参数及数学模型,数值仿真瞬态下的叶片气动外流场。
步骤4、安装叶片1到安装基准9,标定叶片1的空间位置。
步骤5、叶片结构空间网格离散化,确定特征位置17。
步骤6、基于特征位置17及流场仿真数据,计算获得对叶片1表面施加的载荷,通过作动轴4作用于力学探头2并对实际叶片1进行施加载荷。
本步骤具体包括:This step specifically includes:
步骤61、将叶片流场仿真几何模型坐标与试验装置空间坐标完成一致化的标定;Step 61, complete the consistent calibration of the coordinates of the simulation geometric model of the blade flow field and the spatial coordinates of the test device;
步骤62、基于特征位置17及叶片外流场仿真数据,完成基于特征位置的仿真载荷局部面积分,获取载荷沿面法向分量;Step 62, based on the
步骤63、提取特征位置17的载荷沿面法向分量,传递给作动轴4;Step 63, extracting the normal component of the load at the
步骤64、将特征位置17与布置力学探头2的测点位置一一对应,基于特征位置17、法向载荷仿真数据,力学探头2对实际叶片1施加法向分量。Step 64: Corresponding the
步骤7、通过CCD相机16获得叶片1不同特征位置17的变形,与叶片1不同特征位置17变形仿真值比较,若偏差值满足试验要求,记录该瞬态下的载荷大小及方向排布,否则将调整特征位置17的选取。
步骤8、重复以上过程,开展下一个瞬态的外流场气动仿真载荷数据确定,形成载荷数据记录。
步骤9、将记录位置及载荷数据形成载荷谱,施加于叶片1,模拟在非稳态、循环载荷下的叶片载荷疲劳性能。
步骤10、通过CCD相机16观测并记录叶片1的变形情况,评估抗疲劳性能。
下面对上述实施例的方法做详细描述。The method in the above embodiment will be described in detail below.
参照图10,叶片1在仿真软件中完成离散化操作,形成空间的各个特征位置17,每个特征位置17的空间位置可以精确定位。因此,特征位置17的确定因素包括:Referring to FIG. 10 , the discretization operation of the
叶片结构空间网格离散化方式,离散后的点的排布应能够满足力学探针3空间可实现的要求;Discretization of blade structure space grid, the arrangement of discretized points should be able to meet the spatially achievable requirements of
力学探头2及力学探针3的空间分辨率,空间分辨率取决于力学探头2及力学探针3在支撑框5上的分布数量和排列方式;The spatial resolution of the
叶片结构研究位置的选取,不同的叶片1对于疲劳载荷考察的位置不一致,需根据实际情况选择在压力面1-1、吸力面1-2、叶尖1-3、榫根1-4、叶前缘1-5、叶后缘1-6位置排布不同数量的特征位置17。The selection of the research location of the blade structure,
参照图11,叶片1在仿真软件中完成力学仿真。叶片1在实际工况中所受到的主要是压力面1-1、吸力面1-2处的气动载荷,但气动载荷在叶片1的不同位置处为不同数值,实际测试中难以实现每个点位置的不同力值加载。因此,本实施例中主要是通过在叶片1的特定点(特征位置17)处实现力的多点加载,以高精度模拟叶片1所受到的不断变化的气动载荷,进而完成在该气动载荷下叶片1的疲劳强度的测试。Referring to Fig. 11, the mechanical simulation of the
参照图12,为力学探头2对叶片1施加载荷的示意图,在开展叶片1气动流场数值仿真前,先开展叶片1在典型稳态运行工况下的试验测试,通过CCD相机16采用DIC(DigitalImage Correlation,数字图像相关法)非接触式现代光学测量实验技术获得叶片1在该状态下的变形情况,并与叶片1气动流场数值仿真结果进行比对,不断调整气动流场数值仿真的数学模型及参数设置,使得气动流场数值仿真的结果与CCD相机16采用DIC方法获得的实验值偏差保持在允许误差范围内,使得气动流场数值仿真的结果能够反映叶片1真实变形情况。Referring to FIG. 12 , it is a schematic diagram of the
将叶片1在运行中的气动流场通过仿真的方式获得,并将非稳态的运行过程拆分为多个典型的瞬态状态,拆分的瞬态状态数量N≥2。结合叶片1结构的压力面1-1、吸力面1-2、叶尖1-3等具体特征来确定叶片1重点考核试验部位;结合试验装置力学探头2及力学探针3空间分辨率及排列来明确叶片1能够研究、布置的测点力学探头2能够实现的位置的密度;确定叶片1结构空间网格离散化方式,使得布置的特征位置17(力学探头2能够实现的位置)与叶片1结构空间网格离散化后的面特征位置17一一对应。使得力学探针3能够通过力学探头2在叶片1的特定位置17实现力的施加,且施加的位置及大小与叶片1的仿真保持一致。The aerodynamic flow field of the
在实际试验前,需要将叶片1坐标与试验装置空间坐标完成一致化的标定,通过调整横向精密导轨12、纵向精密导轨11、横向粗调导轨15、纵向粗调导轨14及角度调节盘13实现叶片1在测试系统内的空间位置及姿态调整,也可以通过设计叶片支架10的具体结构以补充调整叶片1在测试系统内的空间位置及姿态。Before the actual test, the coordinates of the
力学探头2及力学探针3对叶片1表面的载荷的大小是通过仿真获得的,基于已经确定的特征位置17,以特征位置17为中心,合理划分离散区域,并进行面积分,获得以该点为中心区域的载荷值。由于力学探头2的圆弧与叶片1的表面圆弧呈相切关系,因此其作用力主要沿接触点法向传递,主要为沿表面的法向分量F,并将该法向分量值F在仿真软件中提取,并传递给作动轴4,作为力的输出对实际叶片1施加作用力。而在实际作用中还包含力学探头2对叶片1表面的切向的摩擦载荷f,力学探头2对叶片表面的切向的摩擦载荷f为该测量方式额外引入的干扰量。由于力学探头2及叶片1表面光滑,且力学探头2输入载荷在该方向的分量亦较小,因此该摩擦载荷f的量级较小,可忽略不计。通过CCD相机16获得叶片1不同特征位置17的变形情况,并与叶片1不同特征位置17变形仿真值进行比较,若该偏差值满足试验要求,即可将该瞬态(瞬态1)下的载荷大小及方向排布进行记录,用于后期的疲劳试验。若偏差值不满足要求,则调整特征位置17的选取,最终获得满足偏差要求的位置情况。实际选择过程中,特征位置17的选择数量≥3个。The magnitude of the load on the surface of the
在完成叶片1外流场气动仿真(瞬态1)的载荷记录后,重复以上过程,开展叶片1外流场气动仿真(瞬态2)的载荷数据确定,最终形成一套载荷数据记录,且瞬态状态的数量≥2个。将记录位置及载荷数据形成载荷谱施加于叶片1,模拟在非稳态、循环载荷下的叶片1载荷疲劳性能,并通过CCD相机16观测并记录叶片1的变形情况,评估叶片1的抗疲劳性能。After completing the load records of the aerodynamic simulation (transient 1) of the outer flow field of
本申请的发动机叶片模拟载荷疲劳试验装置,能够精确调节叶片与力学探头及力学探针的相对位置以实现结构的精确定位,作动轴通过集成在力学探针上的力学探头作用于叶片压力面及吸力面施加作用力,将叶片在实际载荷中所受到的气动力等效为力学探头所施加的特定挤压载荷,并检验叶片在特定载荷中的实际变形情况,并与数值仿真计算结果进行对比校准,以最终形成一套成熟的计算及仿真方法,最终为检验叶片在不同的运行工况下的变形情况提供技术条件。The engine blade simulation load fatigue test device of the present application can accurately adjust the relative position of the blade, the mechanical probe and the mechanical probe to realize the precise positioning of the structure, and the actuating shaft acts on the pressure surface of the blade through the mechanical probe integrated on the mechanical probe and the suction surface to apply force, the aerodynamic force of the blade in the actual load is equivalent to the specific extrusion load applied by the mechanical probe, and the actual deformation of the blade in the specific load is checked, and compared with the numerical simulation calculation results Compare and calibrate to finally form a set of mature calculation and simulation methods, and finally provide technical conditions for testing the deformation of blades under different operating conditions.
以上所述,仅为本申请的具体实施方式,但本申请的保护范围并不局限于此,任何熟悉本技术领域的技术人员在本申请揭露的技术范围内,可轻易想到的变化或替换,都应涵盖在本申请的保护范围之内。因此,本申请的保护范围应以权利要求的保护范围为准。The above is only a specific embodiment of the application, but the scope of protection of the application is not limited thereto. Any person familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the application. All should be covered within the scope of protection of this application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.
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