CN110194282B - Airplane wheel brake vibration testing method applying vibration measurement technology - Google Patents
Airplane wheel brake vibration testing method applying vibration measurement technology Download PDFInfo
- Publication number
- CN110194282B CN110194282B CN201910531906.9A CN201910531906A CN110194282B CN 110194282 B CN110194282 B CN 110194282B CN 201910531906 A CN201910531906 A CN 201910531906A CN 110194282 B CN110194282 B CN 110194282B
- Authority
- CN
- China
- Prior art keywords
- vibration
- wheel
- aircraft
- test method
- brake
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000005259 measurement Methods 0.000 title claims description 29
- 238000012360 testing method Methods 0.000 title claims description 22
- 238000005516 engineering process Methods 0.000 title claims description 17
- 230000001133 acceleration Effects 0.000 claims abstract description 48
- 238000000034 method Methods 0.000 claims abstract description 27
- 230000008569 process Effects 0.000 claims abstract description 22
- 238000004088 simulation Methods 0.000 claims abstract description 12
- 238000006073 displacement reaction Methods 0.000 claims abstract description 8
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 6
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 6
- 238000010998 test method Methods 0.000 claims description 20
- 230000003068 static effect Effects 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 4
- 230000006835 compression Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims description 2
- 229910000838 Al alloy Inorganic materials 0.000 claims 1
- 229910000831 Steel Inorganic materials 0.000 claims 1
- 239000010959 steel Substances 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000002474 experimental method Methods 0.000 description 5
- 230000007423 decrease Effects 0.000 description 4
- 238000004458 analytical method Methods 0.000 description 3
- 230000008859 change Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000001914 filtration Methods 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
- 238000012795 verification Methods 0.000 description 2
- 230000003321 amplification Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000003750 conditioning effect Effects 0.000 description 1
- 239000004035 construction material Substances 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 238000001179 sorption measurement Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND 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
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
Description
技术领域technical field
本发明涉及一种应用振动测量技术的飞机机轮刹车振动测试方法，属于飞机测试技术领域。The invention relates to an aircraft wheel brake vibration test method using vibration measurement technology, which belongs to the technical field of aircraft testing.
背景技术Background technique
航空机轮刹车装置的检测需要通过大量的试验验证来确保刹车效率和结构可靠性，同时也需要不断调整参数和不同的控制方法来完成。如果通过实际飞机的起降来完成的话会导致成本剧增，试验周期过长。并且惯性试验台可以模拟飞机在着陆、起飞、滑跑等过程中飞机实际刹车、着陆起飞载荷等飞行状况。因此，行业内一般都通过惯性试验台来完成航空机轮刹车装置的相关试验验证工作。以此来检测机轮和防滑系统的性能，为新产品研制，已有产品的改进提供依据。The detection of aircraft wheel brake devices requires a large number of experimental verifications to ensure the braking efficiency and structural reliability, and also requires constant adjustment of parameters and different control methods to complete. If it is completed through the take-off and landing of the actual aircraft, the cost will increase sharply and the test cycle will be too long. And the inertial test bench can simulate the actual flight conditions of the aircraft such as braking, landing and take-off loads during the process of landing, taking off, and rolling. Therefore, in the industry, the inertial test bench is generally used to complete the relevant test verification work of the aircraft wheel brake device. In order to detect the performance of the wheel and the anti-skid system, it provides a basis for the development of new products and the improvement of existing products.
对生产效率越来越高的要求以及设计时基于经济方面的考虑，要求机器以较高的速度运转和大量使用轻质的结构材料。这些趋势使得机器在运行过程中发生共振的可能性增大，同时降低了系统的可靠性。因此，为了保证足够的安全裕度，对机械结构的振动特性进行测试是十分必要的。任何观察到的固有频率或其他振动特性的变化，往往表明机器系统已经发生了故障或需要及时维修。The increasing demands on production efficiency and the design based on economical considerations require the operation of machines at high speeds and the extensive use of lightweight construction materials. These tendencies increase the likelihood of machine resonance during operation and reduce system reliability. Therefore, in order to ensure a sufficient safety margin, it is necessary to test the vibration characteristics of the mechanical structure. Any observed change in natural frequency or other vibration characteristics often indicates that a machine system has failed or requires prompt repair.
在许多应用中，都需要确定结构或机器能否承受特定的振动环境。如果一个结构或机器系统经过特定环境的振动测试后仍能完成预期的目标，就可以认为它能够承受这类特殊的振动环境而不发生破坏。In many applications, it is necessary to determine whether a structure or machine can withstand a specific vibration environment. If a structure or machine system can still achieve the expected goal after passing the vibration test in a specific environment, it can be considered that it can withstand this special vibration environment without damage.
通过测量振动系统输入和输出的特性，有助于识别系统的质量、刚度和阻尼。然而，到目前为止，还未见关于测量飞机机轮刹车振动情况的相关报道。By measuring the characteristics of the input and output of a vibrating system, it helps to identify the mass, stiffness and damping of the system. However, so far, there is no relevant report about measuring the vibration of aircraft wheel brakes.
发明内容Contents of the invention
本发明技术解决问题：首次提出了通过利用测量模拟飞机刹车机轮振动过程的系统，飞机在模拟超载着陆、中止起飞、正常着陆等工况下刹车的机轮振动情况，实现机轮组件的振动加速值测量。The present invention solves the problem by using the system for measuring and simulating the vibration process of the aircraft brake wheel for the first time, and realizes the vibration of the wheel assembly when the aircraft brakes under overload landing, suspended takeoff, normal landing and other working conditions. Acceleration value measurement.
本发明一种应用振动测量技术的飞机机轮刹车振动测试方法，所述方法基于测量模拟飞机刹车振动过程的系统而展开；The present invention is an aircraft wheel brake vibration test method using vibration measurement technology, the method is developed based on a system for measuring and simulating the aircraft brake vibration process;
所述测量模拟飞机刹车振动过程的系统包括：The system for measuring and simulating the braking vibration process of an aircraft includes:
惯性试验台，由电机、鼓轮、支架、鼓轮主轴组成，支架用于放置机轮，鼓轮用来提供刹车能量；电机用于驱动鼓轮；The inertia test bench is composed of a motor, a drum, a bracket, and a drum spindle. The bracket is used to place the wheel, and the drum is used to provide braking energy; the motor is used to drive the drum;
测量装置，包括加速度传感器、动态信号调理器、数据采集器，加速度传感器与机轮中的组件及动态信号调理器相互连接，动态信号调理器与数据采集器相连；The measuring device includes an acceleration sensor, a dynamic signal conditioner, and a data collector. The acceleration sensor is connected to the components in the wheel and the dynamic signal conditioner, and the dynamic signal conditioner is connected to the data collector;
测试过成中，先通过交流或直流电机带动鼓轮转动，然后驱动电机则控制机轮与鼓轮相互接触完成飞机刹车模型过程，利用测量装置获取刹车工况下的数字信息，分析数字信息，得到测试结果；所述数字信息包括刹车过程中各机轮组件的位移、加速度时域曲线；所述测试结果包括机轮各组件的振动位移值和加速值；通过对比机轮动力学模型仿真得到的机轮各部件的加速度曲线和位移曲线与实验曲线的吻合度，验证了机轮动力学模型的准确性和适用性。During the test, the drum is first driven to rotate by an AC or DC motor, and then the driving motor controls the contact between the wheel and the drum to complete the aircraft braking model process. The measurement device is used to obtain digital information under braking conditions and analyze the digital information. The test result is obtained; the digital information includes the displacement and acceleration time domain curves of each wheel assembly in the braking process; the test result includes the vibration displacement value and the acceleration value of each assembly of the wheel; it is obtained by comparing the wheel dynamics model simulation The accuracy and applicability of the wheel dynamics model are verified by the coincidence of the acceleration curves and displacement curves of each part of the wheel with the experimental curves.
本发明一种应用振动测量技术的飞机机轮刹车振动测试方法；测量系统应用范围为飞机机轮刹车。The invention discloses an aircraft wheel brake vibration test method using the vibration measurement technology; the application range of the measurement system is the aircraft wheel brake.
本发明一种应用振动测量技术的飞机机轮刹车振动测试方法；所述测量系统中测量结构为机轮的组件，所属机轮的组件选自轮毂、缸座、扭力筒、碳盘（包括压紧盘、动盘、静盘和承压盘）中的至少一种。The present invention is an aircraft wheel brake vibration test method using vibration measurement technology; the measurement structure in the measurement system is an assembly of an aircraft wheel, and the assembly of the associated aircraft wheel is selected from a wheel hub, a cylinder seat, a torsion cylinder, a carbon disc (including a pressure At least one of tight disc, dynamic disc, static disc and pressure disc).
本发明一种应用振动测量技术的飞机机轮刹车振动测试方法；所述测量系统中，飞机刹车工况选自正常着陆、中止起飞、超载着陆中的至少一种。The present invention is an aircraft wheel brake vibration test method using vibration measurement technology; in the measurement system, the aircraft brake working condition is selected from at least one of normal landing, suspended takeoff, and overloaded landing.
本发明一种应用振动测量技术的飞机机轮刹车振动测试方法；所述测量系统中，加速器传感器的工作温度在-40℃-+120℃，量程在±200g，频率范围0.7-11000Hz，重量小于20g。The invention discloses a vibration test method for aircraft wheel brakes using vibration measurement technology; in the measurement system, the working temperature of the accelerator sensor is -40°C-+120°C, the range is ±200g, the frequency range is 0.7-11000Hz, and the weight is less than 20g.
本发明一种应用振动测量技术的飞机机轮刹车振动测试方法；所述测量系统中，使用的刹车装置为碳刹车盘。The invention discloses an aircraft wheel brake vibration test method using vibration measurement technology; in the measurement system, the brake device used is a carbon brake disc.
本发明一种应用振动测量技术的飞机机轮刹车振动测试方法；所述测量系统中，轮毂材料为LD10，扭力筒材料为ZG30Cr18Mn12Si2N。The invention discloses an aircraft wheel brake vibration test method using vibration measurement technology; in the measurement system, the wheel hub material is LD10, and the torque tube material is ZG30Cr18Mn12Si2N.
本发明以惯性试验台为基础平台；惯性台的支架用于支撑机轮，通过电机对鼓轮施加转速，模拟飞机的着陆能量，驱动电机使机轮与鼓轮相互接触，开始模型飞机刹车过程；在不同的工况实验过程中，测量人员远离实验设备确保安全性；测量设备中的加速度传感器通过磁铁吸附或胶粘方式直接与机轮组件相连，然后输入信号到动态信号调理器再到信号采集器，最后数据传输与电脑相连；动态信号调理器具有放大测量信号和过滤杂波的功能。The present invention uses the inertial test bench as the basic platform; the bracket of the inertial bench is used to support the machine wheel, and the motor applies rotational speed to the drum wheel to simulate the landing energy of the aircraft, and drives the motor to make the machine wheel and the drum wheel contact each other, and the braking process of the model aircraft begins ;During the experiments under different working conditions, the measuring personnel stay away from the experimental equipment to ensure safety; the acceleration sensor in the measuring equipment is directly connected to the wheel assembly through magnet adsorption or glue, and then the input signal is sent to the dynamic signal conditioner and then to the signal The collector is finally connected to the computer for data transmission; the dynamic signal conditioner has the functions of amplifying the measurement signal and filtering clutter.
附图说明Description of drawings
图1为振动实验系统装置简图。Figure 1 is a schematic diagram of the vibration experiment system.
图2为振动实验系统实物图。Figure 2 is a physical diagram of the vibration experiment system.
图3为实施例1中旅缸座轴向振动加速度曲线。Fig. 3 is the axial vibration acceleration curve of the cylinder seat in the first embodiment.
图4缸座轴向2~3秒时间段振动航空机轮的的动力学响应分析加速度曲线。Fig. 4 The dynamic response analysis acceleration curve of the vibrating aircraft wheel in the axial direction of the cylinder seat for 2-3 seconds.
图5缸座径向振动加速度曲线。Fig. 5 Radial vibration acceleration curve of cylinder block.
图6缸座径向2~3秒时间段振动加速度曲线。Fig. 6 The vibration acceleration curve of the radial direction of the cylinder seat in the period of 2 to 3 seconds.
图7扭力筒轴向振动加速度曲线。Fig. 7 Axial vibration acceleration curve of torque cylinder.
图8扭力筒轴向2~3秒时间段振动加速度曲线。Fig. 8 The vibration acceleration curve of the axial direction of the torque cylinder in the period of 2 to 3 seconds.
图9压紧盘轴向振动加速度曲线。Fig. 9 Axial vibration acceleration curve of the pressure plate.
图10压紧盘轴向3~4秒时间段振动加速度曲线。Fig. 10 The vibration acceleration curve of the pressure plate axial direction in the period of 3 to 4 seconds.
图11扭力筒轴向仿真振动加速度曲线。Figure 11 Torque cylinder axial simulation vibration acceleration curve.
图12扭力筒轴向2~3秒时间段仿真振动加速度曲线。Fig. 12 Simulation vibration acceleration curve in the axial direction of the torque cylinder for 2 to 3 seconds.
图1中，1为驱动电机、2为支架、3为航空机轮、4为鼓轮、5为交流或直流电机、6为鼓轮主轴。In Fig. 1, 1 is a drive motor, 2 is a bracket, 3 is an aircraft wheel, 4 is a drum, 5 is an AC or DC motor, and 6 is a drum main shaft.
从图2中可以看出，本发明所设计的方案以及通过实际实验。As can be seen from Fig. 2, the scheme designed by the present invention has been passed through actual experiments.
图3-6给出了缸座的轴向和径向振动加速度曲线，当刹车压力处于一个上升状态时，轴向振动加速度幅值就稳定在0.5g，径向振动加速度幅值则稳定在1.2g。Figure 3-6 shows the axial and radial vibration acceleration curves of the cylinder seat. When the brake pressure is in a rising state, the axial vibration acceleration amplitude is stable at 0.5g, and the radial vibration acceleration amplitude is stable at 1.2 g.
图7、8图给出的是机轮扭力筒的轴向振动加速度曲线，可以看出扭力筒的振动加速度幅值稳定在0.4g附近，相比于静盘、缸座的轴向振动都小；在刹车过程刚开始的瞬间，最大的加速度值也只有3.6g。对比刹车压力曲线可以看出，当刹车压力在8秒后趋于稳定时，扭力筒的振动幅值有了小幅度减小。Figures 7 and 8 show the axial vibration acceleration curves of the wheel torsion cylinder. It can be seen that the vibration acceleration amplitude of the torsion cylinder is stable around 0.4g, which is smaller than the axial vibration of the static plate and cylinder seat; At the moment of the beginning of the braking process, the maximum acceleration value is only 3.6g. Comparing the brake pressure curve, it can be seen that when the brake pressure tends to be stable after 8 seconds, the vibration amplitude of the torque tube decreases slightly.
由图9、10可以看出在刹车力矩逐渐增大这一过程中，静盘的轴向振动加速度幅值处于稳定状态，并有小幅度的减小。It can be seen from Figures 9 and 10 that during the process of gradually increasing the braking torque, the amplitude of the axial vibration acceleration of the static disc is in a stable state and decreases slightly.
图11、12位仿真中扭力筒振动加速度曲线，对比实验曲线，在加速度振动最大幅值、力矩稳定区域幅值、曲线变化等情况，实验和仿真结果接近，误差基本不超过0.1g；表明系统动力学方程的仿真结果是准确可靠的，适用于该机轮振动特性分析的。Figure 11. Torque cylinder vibration acceleration curve in 12-bit simulation, compared with the experimental curve, in the case of the maximum amplitude of acceleration vibration, the amplitude of torque stable area, and the curve change, the experimental and simulation results are close, and the error basically does not exceed 0.1g; it shows that the system The simulation results of the dynamic equations are accurate and reliable, and are suitable for the analysis of the vibration characteristics of the wheel.
具体实施方式Detailed ways
实施例1Example 1
振动实验系统实物如附图2所示，将所需测量的航空机轮安装在惯性台支架上，然后通过交流或直流电机带动鼓轮转动，施加刹车能量，驱动电机则控制机轮与鼓轮相互接触完成飞机刹车模型过程；安装加速度传感器与机轮结构表面，刹车过程中，加速度传感器将测量的电信号传递到信号调理设备中，进行放大和滤波，然后再传递到信号采集设备，最后通过电脑端予以显示，完成结构的振动加速度测量过程。The physical object of the vibration experiment system is shown in Figure 2. The aircraft wheel to be measured is installed on the inertial table bracket, and then the drum is driven to rotate by an AC or DC motor, and the braking energy is applied. The driving motor controls the wheel and the drum. Contact each other to complete the aircraft braking model process; install the acceleration sensor and the surface of the wheel structure. During the braking process, the acceleration sensor transmits the measured electrical signal to the signal conditioning equipment for amplification and filtering, and then transmits it to the signal acquisition equipment. Finally, through It will be displayed on the computer to complete the vibration acceleration measurement process of the structure.
（1）惯性轮转速： 0～2500 rpm。(1) Speed of inertia wheel: 0～2500 rpm.
（2）输出能量：最小：2.0 MJ；最大：80 MJ ；能量（示值）精度：±1.0 %。(2) Output energy: minimum: 2.0 MJ; maximum: 80 MJ; energy (indication) accuracy: ±1.0%.
（3）机轮重量：70Kg。(3) Wheel weight: 70Kg.
（4）缸座测试结果见图3、4、5、6。(4) See Figures 3, 4, 5 and 6 for the test results of the cylinder block.
图3-6给出了缸座的轴向和径向振动加速度曲线，当刹车压力处于一个上升状态时，轴向振动加速度幅值就稳定在0.5g，径向振动加速度幅值则稳定在1.2g。Figure 3-6 shows the axial and radial vibration acceleration curves of the cylinder seat. When the brake pressure is in a rising state, the axial vibration acceleration amplitude is stable at 0.5g, and the radial vibration acceleration amplitude is stable at 1.2 g.
（5）扭力筒测试结果，见图7、8。(5) Torque barrel test results, see Figures 7 and 8.
图7、8图给出的是机轮扭力筒的轴向振动加速度曲线，可以看出扭力筒的振动加速度幅值稳定在0.4g附近，相比于静盘、缸座的轴向振动都小。在刹车过程刚开始的瞬间，最大的加速度值也只有3.6g。对比刹车压力曲线可以看出，当刹车压力在8秒后趋于稳定时，扭力筒的振动幅值有了小幅度减小。Figures 7 and 8 show the axial vibration acceleration curves of the wheel torsion cylinder. It can be seen that the vibration acceleration amplitude of the torsion cylinder is stable at around 0.4g, which is smaller than the axial vibration of the static plate and cylinder seat. At the moment of the beginning of the braking process, the maximum acceleration value is only 3.6g. Comparing the brake pressure curve, it can be seen that when the brake pressure tends to be stable after 8 seconds, the vibration amplitude of the torque tube decreases slightly.
（6）压紧盘测试结果，见图9、10。(6) See Figures 9 and 10 for the test results of the compression disc.
由图9、10可以看出在刹车力矩逐渐增大这一过程中，静盘的轴向振动加速度幅值处于稳定状态，并有小幅度的减小。It can be seen from Figures 9 and 10 that during the process of gradually increasing the braking torque, the amplitude of the axial vibration acceleration of the static disc is in a stable state and decreases slightly.
（7）仿真结果与实验结果对比，见图11、12。(7) Comparison of simulation results and experimental results, see Figures 11 and 12.
图11、12位仿真中扭力筒振动加速度曲线，对比实验曲线，在加速度振动最大幅值、力矩稳定区域幅值、曲线变化等情况，实验和仿真结果接近，误差基本不超过0.1g。表明系统动力学方程的仿真结果是准确可靠的，适用于该机轮振动特性分析的。Figure 11. Torque cylinder vibration acceleration curve in 12-bit simulation. Compared with the experimental curve, the experimental and simulation results are close to each other in terms of the maximum amplitude of acceleration vibration, the amplitude of the torque stability area, and the curve change, and the error basically does not exceed 0.1g. It shows that the simulation result of the system dynamic equation is accurate and reliable, and is suitable for the analysis of the vibration characteristics of the wheel.
Claims (8)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910531906.9A CN110194282B (en) | 2019-06-19 | 2019-06-19 | Airplane wheel brake vibration testing method applying vibration measurement technology |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910531906.9A CN110194282B (en) | 2019-06-19 | 2019-06-19 | Airplane wheel brake vibration testing method applying vibration measurement technology |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110194282A CN110194282A (en) | 2019-09-03 |
| CN110194282B true CN110194282B (en) | 2022-11-04 |
Family
ID=67754759
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910531906.9A Active CN110194282B (en) | 2019-06-19 | 2019-06-19 | Airplane wheel brake vibration testing method applying vibration measurement technology |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110194282B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114186349B (en) * | 2021-12-17 | 2024-12-31 | 中国飞机强度研究所 | A method for predicting aircraft structure vibration under specific working conditions |
| CN117909659B (en) * | 2024-03-20 | 2024-05-14 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method and device for processing aerodynamic force signals of balance in wind tunnel dynamic test of variant aircraft |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4101985A1 (en) * | 1991-01-24 | 1992-07-30 | Domarkas Andrew | Test for irregularities of cooperative elements, esp. gears - involves computation of sum of acoustic emissions superimposed at fixed phase w.r.t. relevant outputs of accelerometer |
| CA2230202A1 (en) * | 1998-02-23 | 1999-08-23 | Yvon Rancourt | Dynamometer |
| JP2004352191A (en) * | 2003-05-30 | 2004-12-16 | Aruze Corp | Aircraft wheel support mechanism |
| CN101000238A (en) * | 2007-01-17 | 2007-07-18 | 北京航空航天大学 | Plane wheel space displacement measuring system of landing gear lowering shock test |
| CN102121846A (en) * | 2010-11-30 | 2011-07-13 | 中南大学 | Method and device for testing vibration effect of multi-combination hydraulic long pipeline system |
| CN103803098A (en) * | 2014-02-13 | 2014-05-21 | 西安航空制动科技有限公司 | Airplane wheel speed simulation device |
| CN105138805A (en) * | 2015-09-29 | 2015-12-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Load simulation method for cataplane landing gear |
| CN105480431A (en) * | 2014-10-11 | 2016-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Method for avoiding excessive vibration of undercarriage in overhead state |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103553695B (en) * | 2013-10-23 | 2015-01-21 | 中南大学 | Carbon-ceramic composite brake disc and preparation method thereof |
-
2019
- 2019-06-19 CN CN201910531906.9A patent/CN110194282B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4101985A1 (en) * | 1991-01-24 | 1992-07-30 | Domarkas Andrew | Test for irregularities of cooperative elements, esp. gears - involves computation of sum of acoustic emissions superimposed at fixed phase w.r.t. relevant outputs of accelerometer |
| CA2230202A1 (en) * | 1998-02-23 | 1999-08-23 | Yvon Rancourt | Dynamometer |
| JP2004352191A (en) * | 2003-05-30 | 2004-12-16 | Aruze Corp | Aircraft wheel support mechanism |
| CN101000238A (en) * | 2007-01-17 | 2007-07-18 | 北京航空航天大学 | Plane wheel space displacement measuring system of landing gear lowering shock test |
| CN102121846A (en) * | 2010-11-30 | 2011-07-13 | 中南大学 | Method and device for testing vibration effect of multi-combination hydraulic long pipeline system |
| CN103803098A (en) * | 2014-02-13 | 2014-05-21 | 西安航空制动科技有限公司 | Airplane wheel speed simulation device |
| CN105480431A (en) * | 2014-10-11 | 2016-04-13 | 中国航空工业集团公司西安飞机设计研究所 | Method for avoiding excessive vibration of undercarriage in overhead state |
| CN105138805A (en) * | 2015-09-29 | 2015-12-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Load simulation method for cataplane landing gear |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110194282A (en) | 2019-09-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106323618B (en) | Electric Servo Mechanism Load Simulation System and Simulation Method | |
| CN103616107B (en) | A kind of varying load Variable inertia electromechanics performance testing device | |
| CN107870093B (en) | 1/4 vehicle braking simulation and performance experimental test system and method | |
| CN201993232U (en) | Bus hub bearing loading simulation testing device | |
| CN112393869B (en) | Impact test device and method for passenger vehicle gearbox | |
| CN102749205A (en) | Simulation braking bench for automobile disc brake | |
| CN101604490B (en) | Semi-physical simulation platform structure of airplane brake system | |
| CN110194282B (en) | Airplane wheel brake vibration testing method applying vibration measurement technology | |
| CN202661273U (en) | Simulation braking bench of automobile disc brake | |
| CN111693297A (en) | Dynamic bench test equipment and test method for vehicle driving/braking control system | |
| CN104359686A (en) | Automobile disc brake braking judder and squeal test bed | |
| CN104236795A (en) | Method and device for measuring rotation inertia of revolution body online | |
| CN2708293Y (en) | Test-bed for automobile ABS performance | |
| CN103487182A (en) | High-accuracy measuring method and device for high-speed rotor flow resistance torque | |
| CN103345158A (en) | Ventilating disc type brake test stand and electric inertia simulating control method thereof | |
| CN103344424B (en) | Ventilation disk brake electric inertia simulation testing stand and electric inertia simulation control method thereof | |
| CN103335832B (en) | Electric inertia simulation Ventilation disk brake testing stand and electric inertia simulation control method | |
| CN109738203A (en) | Brake test device and test method for dynamic brake performance of automatic driving vehicle | |
| CN109738204A (en) | Automatic braking test device and test method for dynamic braking performance of automatic driving vehicle | |
| Cantoni et al. | Brake and pneumatic wheel performance assessment–A new test rig | |
| CN103217284B (en) | Measurement method for modal damping coefficient of rotary machine | |
| US3208266A (en) | Testing apparatus | |
| CN213779472U (en) | Shaft end endurance experiment device of new energy electric drive system | |
| CN107631885A (en) | A kind of drum of inspector for automotive vehicle | |
| CN209656303U (en) | A kind of train disc caliper brake tester with rigidity adjustable structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |