Integrated testing device and testing method for airplane wheel cooling device

Abstract

The invention discloses an integrated testing device and testing method for an airplane wheel cooling device, and particularly relates to the field of testing technologies of airplane wheel cooling devices. An eddy current dynamometer is connected with the output end of a fan motor; the power analyzer is connected in series between the output end of the fan motor controller and the input end of the motor and is used for acquiring the input power and the output power of the fan motor; the dynamometer controller is connected with the eddy current dynamometer and is used for sending an instruction of applying a preset torque to the eddy current dynamometer, and the dynamometer controller is also connected with the power analyzer and is used for determining the efficiency and the power factor according to the input power and the output power of the fan motor; the temperature acquisition and test module is used for providing an analog temperature signal for the fan motor controller; the air volume collecting and testing module is used for collecting cooling air volume generated by the fan motor. Based on the device and the method, the three functions are integrated, and the testing efficiency of the aircraft brake cooling device is improved.

Description

Technical Field

[0001] The present application relates to the technical field of testing wheel cooling devices, and in particular to an integrated testing device and testing method for aircraft wheel cooling devices. Background Art

[0002] As aircraft usage scenarios continue to expand, shortening re-deployment time and increasing aircraft usage frequency have become key design principles for aircraft landing gear systems. Rapid cooling of the brake heat reservoir can significantly shorten re-deployment time and improve aircraft operational responsiveness. Wheel cooling units, the core components of rapid cooling technology, are experiencing increasing demand. Therefore, ground-based functional performance testing of wheel cooling units is crucial for ensuring their reliability.

[0003] The existing functional performance test system of the wheel cooling device can only perform motor drive test or cooling effect test separately, and the cooling effect test is realized through flow field simulation of simulation software, and the cooling effect of the wheel cooling device cannot be intuitively monitored. Summary of the Invention

[0004] The main purpose of the present application is to provide an integrated testing device and testing method for an aircraft wheel cooling device, aiming to solve the problem that the functional performance testing system of the existing wheel cooling device has a single testing function.

[0005] To achieve the above-mentioned objectives, the present application provides an integrated testing device for an aircraft wheel cooling device, wherein the wheel cooling device includes a fan motor and a fan motor controller, and the testing device includes: an eddy current dynamometer connected to the output end of the fan motor; used to apply a preset torque to the fan motor and collect the torque and speed of the fan motor; a power analyzer connected in series between the output end of the fan motor controller and the input end of the motor, for obtaining the input power and output power of the fan motor; a dynamometer controller connected to the eddy current dynamometer, for sending an instruction to apply a preset torque to the eddy current dynamometer, and also connected to the power analyzer, for determining the efficiency and power factor based on the input power and output power of the fan motor; a power supply device connected to the input end of the dynamometer controller; a temperature acquisition test module connected to the fan motor controller, for providing an analog temperature signal to the fan motor controller; and an air volume acquisition test module located on the outside of the aircraft's wheel, for collecting the cooling air volume generated by the fan motor.

[0006] Optionally, the temperature acquisition test module includes: a temperature source device, used to simulate the temperature of the brake device when the aircraft wheel brakes; a brake temperature sensor, connected to the temperature source device, used to collect the temperature signal output by the temperature source device; a detection device, respectively connected to the fan motor controller and the brake temperature sensor, used to obtain the temperature signal output by the brake temperature sensor, and send the temperature signal to the fan motor controller.

[0007] Optionally, the detection device is further used to detect the output accuracy of the temperature sensor.

[0008] Optionally, the air volume collection test module includes: an air duct located outside the wheel of the aircraft, a flow collector and a fan are sequentially arranged at the inlet end of the air duct, and a pressure gauge and a flow meter are arranged inside the air duct.

[0009] Optionally, there are two wind tubes, which are located on both sides of the aircraft wheel.

[0010] Optionally, a power meter is further connected between the output terminal of the power supply device and the input terminal of the dynamometer controller, and the power meter is used to detect the current and bus voltage of the power supply.

[0011] Optionally, the output end of the power analyzer is further connected to a dynamometer controller, and the dynamometer controller is used to display the voltage and current of the fan motor collected by the power analyzer.

[0012] To achieve the above-mentioned purpose, the present application also provides a testing method for an integrated testing device for an aircraft wheel cooling device, comprising: providing an analog temperature signal to a fan motor controller through a temperature acquisition test module, the fan motor controller determining the starting threshold of the fan motor based on the temperature signal, and controlling the rotation of the fan motor; the dynamometer controller sending an instruction to apply a preset torque to an eddy current dynamometer, the eddy current dynamometer applying the preset torque to the fan motor according to the instruction, and collecting the torque and speed of the fan motor; the power analyzer obtaining the input power and output power of the fan motor; determining the efficiency and power factor of the fan motor based on the input power and output power; collecting the wind generated by the rotation of the fan motor blade assembly through a collector into a wind duct, and collecting the wind pressure and air volume correspondingly through a pressure gauge and a flow meter, and evaluating the cooling effect of the aircraft wheel brake based on the wind pressure and air volume.

[0013] Optionally, the efficiency and power factor of the fan motor are determined based on the input power and output power, including: determining the efficiency of the fan motor based on the ratio of the input power to the output power of the fan motor; determining the active power based on the ratio of the output power and the efficiency of the fan motor; the input power of the fan motor is apparent power, and determining the power factor based on the ratio of the active power to the apparent power.

[0014] Optionally, a simulated temperature signal is provided to the fan motor controller through a temperature acquisition test module, including: simulating the brake device temperature when the aircraft wheel brakes through a temperature source device, the brake temperature sensor acquires the temperature of the temperature source device, and the detection device obtains the temperature acquired by the brake temperature sensor and sends it to the fan motor controller.

[0015] Compared with the prior art, the present invention has the following advantages: The integrated testing device for an aircraft wheel cooling device of the present invention simulates load and transmission through an eddy current dynamometer, a dynamometer controller, and a power analyzer, thereby realizing motor characteristic testing under onboard operating conditions. The temperature acquisition test module is used to simulate and acquire the aircraft wheel brake temperature, and the air volume acquisition test module is used to acquire the cooling air volume of the fan motor, thereby enabling intuitive monitoring of the cooling effect of the wheel cooling device. The integration of the above three functions is compatible with existing aircraft cooling systems, thereby improving the testing efficiency of aircraft brake cooling devices. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a schematic structural diagram of an integrated testing device for an aircraft wheel cooling device according to the present application; Figure 2 The figure is a schematic diagram of the structure of a drive test module in an integrated test device for an aircraft wheel cooling device.

[0017] The realization of the objectives, functional features and advantages of this application will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0018] To make the objectives, technical solutions, and advantages of this application more clear, the technical solutions of this application will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the embodiments described are only part of the embodiments of this application, not all of them. Based on the embodiments of this application, all other embodiments obtained by ordinary technicians in this field without making any creative efforts are within the scope of protection of this application.

[0019] A first embodiment of the present invention provides an integrated test device for an aircraft wheel cooling device, wherein the wheel cooling device includes a fan motor connected to a fan motor controller, such as Figure 1-2As shown, the test device includes an eddy current dynamometer, a dynamometer controller, a power analyzer, a power supply device, a temperature acquisition test module and an air volume acquisition test module; the eddy current dynamometer is connected to the output end of the fan motor through a coupling; it is used to apply a preset torque to the fan motor (fan blade assembly) and collect the torque and speed of the fan motor; the power analyzer is connected in series between the output end of the fan motor controller and the input end of the motor, and is used to obtain the power output from the fan motor controller to the fan motor (that is, the input power of the fan motor), and the output power of the fan motor, specifically, for collecting the three-phase voltage and current of the output of the fan motor, and determining the speed of the fan motor based on the three-phase voltage and current. The output power is determined, and the bus current of the fan motor controller and the current and voltage output to the fan motor can be collected and measured, and the input power can be calculated; the dynamometer controller is connected to the eddy current dynamometer, and is used to send an instruction to the eddy current dynamometer to apply a preset torque, so that the fan motor can simulate the actual operating conditions on the machine and rotate stably. The dynamometer controller is also connected to the power analyzer, which is used to determine the efficiency and power factor according to the input power and output power of the fan motor; the power supply equipment is connected to the input end of the dynamometer controller; the temperature acquisition test module is connected to the fan motor controller, which is used to provide a simulated temperature signal to the fan motor controller; the air volume acquisition test module is used to collect the cooling air volume of the fan motor.

[0020] The preset torque is determined by the dynamometer controller based on the excitation current. By controlling the excitation current, the output torque is maintained stable. Furthermore, the dynamometer controller includes a display connected to the power analyzer and the electric turbine dynamometer, displaying the power output by the power analyzer and the torque and speed recorded by the electric turbine dynamometer. An exemplary power analyzer is the PA323. It integrates a power meter and current sensor, enabling measurement of electrical parameters such as fan motor voltage, current, frequency, and power factor. It can also be used to measure bus current, output current, and power of the fan motor controller. It is compatible with electrical parameter measurements for both permanent magnet synchronous motors and AC asynchronous motors. The eddy current dynamometer integrates a torque sensor and a speed sensor, enabling measurement of fan motor torque and speed. The power analyzer is a three-channel power analyzer with a built-in three-phase power meter, enabling electrical parameter acquisition of three-phase AC motors (fan motors). For DC fan motors, the high-voltage DC power can be inverted through the IGBT integrated circuit by the fan motor controller, and then output to the fan motor as three-phase AC power after inversion, and collected and measured by the power analyzer.

[0021] It is worth noting that the fan motor mentioned in this embodiment is a fan motor assembly.

[0022] In this embodiment, an eddy current dynamometer, a dynamometer controller, and a power analyzer are used to simulate load and transmission, thereby realizing motor characteristic testing under in-flight operating conditions. A temperature acquisition test module is used to simulate and acquire the aircraft wheel brake temperature, and an air volume acquisition test module is used to acquire the cooling air volume of the fan motor, thereby enabling intuitive monitoring of the cooling effect of the wheel cooling device. The above three functions are integrated to be compatible with existing aircraft cooling systems and the testing of DC motors, three-phase AC motors, and current-output temperature sensors, thereby improving the testing efficiency of the aircraft brake cooling device and eliminating the need for separate testing.

[0023] Specifically, the temperature acquisition test module includes a temperature source device, a brake temperature sensor, and a detection device. The temperature source device is used to simulate the temperature of the brake device when the aircraft wheel brakes; the brake temperature sensor is connected to the temperature source device and is used to collect the temperature signal output by the temperature source device; the detection device is connected to the fan motor controller and the brake temperature sensor respectively, and is used to obtain the output signal of the brake temperature sensor and send the output signal to the fan motor controller. Specifically, when the brake temperature sensor is a voltage output temperature sensor, the output signal of the detection device is a standard thermocouple, which can be converted into a 4mA to 20mA current signal by the detection device; when the brake temperature sensor is a current output temperature sensor, the output signal of the detection device is a 4mA to 20mA current signal that can be directly output. The temperature inside the temperature source device can be set to 300°C.

[0024] In this embodiment, the temperature acquisition test module can simulate the acquisition process of the aircraft wheel brake temperature field. By replacing the wheel brake device with a temperature source device, the wheel brake temperature sensor directly senses the temperature of the temperature source temperature field and transmits the sensed temperature to the wheel cooling fan motor controller through a current signal. The wheel brake temperature signal is used as a judgment condition for cooling startup and participates in wheel brake cooling.

[0025] The air volume collection test module includes an air duct located outside the aircraft's wheel. A flow collector and a fan are sequentially installed at the inlet of the air duct, with a pressure gauge and a flow meter installed inside the air duct. Furthermore, the air duct includes two air ducts, one on each side of the aircraft's wheel. The pressure and flow meters collect the wind pressure and air volume generated by the rotation of the fan motor's blade assembly to test the cooling effect. When using two air ducts, the wind pressure is the average of the pressure gauges in the two air ducts, and the air volume is determined in the same way.

[0026] As will be appreciated, the fan motor is installed within the main landing gear axle. The air duct in this embodiment is designed based on the aircraft wheel hub dimensions. To improve data collection accuracy, flow collectors, pressure gauges, and flow meters are evenly spaced every 20 mm within the duct. This duct collects air volume, allowing for integrated testing and replacing flow field simulation software with simulation software to monitor real-time brake cooling air volume. This allows for intuitive monitoring and accurate assessment of the wheel cooling system's cooling effectiveness.

[0027] A power meter is also connected between the output end of the power supply device and the input end of the dynamometer controller to detect the current and bus voltage of the power supply.

[0028] A second embodiment of the present invention provides a testing method for an integrated testing device for an aircraft wheel cooling device, such as Figure 1 As shown, the specific steps include: Step S1, providing a simulated temperature signal to the fan motor controller through the temperature acquisition test module, and the fan motor controller determines the starting threshold of the fan motor according to the temperature signal and controls the rotation of the fan motor; Specifically, the temperature of the brake device when the aircraft wheel brakes is simulated by a temperature source device, the brake temperature sensor collects the temperature of the temperature source device, the detection device obtains the temperature signal collected by the brake temperature sensor and sends it to the fan motor controller. The fan motor controller determines the starting threshold of the fan motor according to the collected temperature signal and controls the rotation of the fan motor.

[0029] For example, when testing a current-type brake temperature sensor, the brake temperature sensor conditions and compensates the collected mV-level thermoelectromotive force signal and outputs it to the detection device as a (4-20) mA current signal.

[0030] In step S2, the dynamometer controller sends an instruction to apply a preset torque (the torque of the fan blade assembly) to the eddy current dynamometer. The eddy current dynamometer applies the preset torque to the fan motor according to the instruction, collects the torque and speed of the fan motor, and adjusts the preset torque based on the collected results. The power analyzer obtains the input power and output power of the fan motor. The dynamometer controller determines the efficiency and power factor of the fan motor based on the input power and output power. The specific determination method is as follows.

[0031] Based on the voltage and current output from the fan motor controller to the fan motor (i.e., the fan motor's input voltage and current) and the fan motor's output voltage and current, collected by the power analyzer, the power analyzer can determine the fan motor's input power and output power using built-in formulas. The fan motor controller calculates the ratio of the fan motor's input power to its output power, which is the fan motor's efficiency. The fan motor controller determines the active power based on the fan motor's output power and efficiency. Active power is the ratio of the fan motor's output power to its efficiency. The fan motor's input power is the apparent power, and the power factor is calculated from the ratio of active power to apparent power, enabling testing of the fan motor's efficiency and power factor.

[0032] In step S3, the wind generated by the rotation of the fan motor blade assembly is collected into the wind duct through the collector, and the wind pressure and air volume are collected correspondingly through the pressure gauge and flow meter, and the cooling effect of the aircraft wheel brake is evaluated based on the wind pressure and air volume.

[0033] Furthermore, based on the test results of the aircraft wheel cooling device, the various accessory products in the wheel cooling device can be adjusted and optimized, and improvement directions for optimizing and enhancing product performance can be proposed. The specific directions are: The efficiency and current test data of the fan motor serve as the acceptance functional performance data of the fan motor. When the measured efficiency and current exceed the design indicators, the power supply equipment should be adjusted to ensure stable power supply; and the fixing fixture and coupling of the eddy current dynamometer should be adjusted to keep the transmission process level to avoid eccentric wear during the transmission process, which will cause significant mechanical wear and reduce the efficiency of the fan motor. After adjusting the above power supply equipment and fixing fixture, the performance parameter test of the fan motor should be carried out again. If the measured efficiency and current still exceed the design indicators, the fan motor can be disassembled and the gap adjusted before testing.

[0034] When the cooling air volume of the wheel cooling device cannot meet the design indicators, the software drive parameters of the fan motor controller should be adjusted to increase the fan motor speed and the cooling air volume.

[0035] When the output accuracy of the brake temperature sensor cannot meet the design indicators, the current-type wheel brake temperature sensor should be recalibrated; if the tested wheel brake output temperature signal shows a jump or step, the filter design of the wheel brake temperature sensor should be optimized or the transmission cable shielding should be improved.

[0036] In this embodiment, the testing method of the integrated testing device is compatible with the existing aircraft cooling system and can realize a highly integrated driving test including motor drive testing, cooling function quantitative testing, energy consumption collection, and temperature collection.

[0037] The above are only preferred embodiments of the present application and do not limit the patent scope of the present application. Any equivalent structure or equivalent process transformation made using the contents of the present application specification and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present application.

Claims

1. An integrated test device for an aircraft wheel cooling device, characterized in that: The wheel cooling system includes a fan motor and a fan motor controller. The test system includes: an eddy current dynamometer connected to the output end of the fan motor; used to apply a preset torque to the fan motor and collect the torque and speed of the fan motor; a power analyzer connected in series between the output terminal of the fan motor controller and the input terminal of the motor, for obtaining the input power and output power of the fan motor; a dynamometer controller connected to the eddy current dynamometer and configured to send a command to the eddy current dynamometer to apply a preset torque; the dynamometer controller is further connected to a power analyzer and configured to determine efficiency and power factor based on input power and output power of the fan motor; A power supply device connected to the input terminal of the dynamometer controller; a temperature acquisition and testing module connected to the fan motor controller and configured to provide a simulated temperature signal to the fan motor controller; The air volume collection and testing module is located outside the aircraft wheel and is used to collect the cooling air volume generated by the fan motor.

2. The integrated testing device for an aircraft wheel cooling device according to claim 1, characterized in that: The temperature acquisition test module includes: Temperature source equipment, used to simulate the temperature of the brake device when the aircraft wheel brakes; Brake temperature sensor, connected to the temperature source device, used to collect the temperature signal output by the temperature source device; The detection device is connected to the fan motor controller and the brake temperature sensor respectively, and is used to obtain the temperature signal output by the brake temperature sensor and send the temperature signal to the fan motor controller.

3. The integrated testing device for an aircraft wheel cooling device according to claim 1, characterized in that: The detection device is also used to detect the output accuracy of the temperature sensor.

4. The integrated testing device for an aircraft wheel cooling device according to claim 1, characterized in that: The air volume collection test module includes: The wind duct is located outside the wheel of the aircraft. A flow collector and a fan are sequentially arranged at the inlet end of the wind duct, and a pressure gauge and a flow meter are arranged inside the wind duct.

5. The integrated testing device for an aircraft wheel cooling device according to claim 4, characterized in that: The two wind tubes are located on both sides of the aircraft wheel.

6. The integrated testing device for an aircraft wheel cooling device according to claim 1, characterized in that: A power meter is further connected between the output end of the power supply device and the input end of the dynamometer controller, and the power meter is used to detect the current and bus voltage of the power supply.

7. The integrated testing device for an aircraft wheel cooling device according to claim 1, characterized in that: The output end of the power analyzer is also connected to a dynamometer controller, and the dynamometer controller is used to display the voltage and current of the fan motor collected by the power analyzer.

8. A testing method for an integrated testing device for an aircraft wheel cooling device, characterized in that: include: The temperature acquisition test module provides a simulated temperature signal to the fan motor controller, and the fan motor controller determines the starting threshold of the fan motor according to the temperature signal and controls the rotation of the fan motor; The dynamometer controller sends a command to the eddy current dynamometer to apply a preset torque. The eddy current dynamometer applies the preset torque to the fan motor according to the command and collects the torque and speed of the fan motor. The power analyzer obtains the input power and output power of the fan motor. The dynamometer controller determines the efficiency and power factor of the fan motor based on the input power and the output power; The wind generated by the rotation of the fan motor's blade assembly is collected into the wind duct through a collector, and the wind pressure and air volume are collected correspondingly through a pressure gauge and a flow meter. The cooling effect of the aircraft wheel brake is evaluated based on the wind pressure and air volume.

9. The testing method for an integrated testing device for an aircraft wheel cooling device according to claim 1, characterized in that: Determining the efficiency and power factor of the fan motor according to the input power and the output power includes: Determine the efficiency of the fan motor based on the ratio of its input power to its output power; Determine the active power based on the ratio of the fan motor's output power and efficiency; The input power of the fan motor is apparent power, and the power factor is determined by the ratio of active power to apparent power.

10. The testing method for an integrated testing device for an aircraft wheel cooling device according to claim 1, characterized in that: The method of providing a simulated temperature signal to the fan motor controller through the temperature acquisition test module includes: The temperature of the brake device when the aircraft wheel brakes is simulated by the temperature source device, the brake temperature sensor collects the temperature of the temperature source device, and the detection device obtains the temperature signal collected by the brake temperature sensor and sends it to the fan motor controller.

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