Aero-engine tachometer testing device

Abstract

The utility model provides an aero-engine tachometer testing device, and relates to the technical field of aero-engine testing. According to the technical scheme, the aeroengine tachometer testing device comprises a box body, a power supply is arranged in the box body, the power supply is electrically connected with a direct-current brushless motor and a programmable controller, a motor control driver of the direct-current brushless motor is electrically connected with the programmable controller, a sensor switching adapter is installed at the output end of the direct-current brushless motor, and the sensor switching adapter is electrically connected with the programmable controller. The sensor switching adapter is provided with an installation interface used for installing a rotating speed sensor to be detected. The outer side of the box body is provided with an input port, an output port, an AC voltmeter and a display screen. The beneficial effects of the utility model are that the test device significantly improves the accuracy of a measurement result, effectively weakens the interference of voltage fluctuation on the measurement process, and ensures the stability and reliability of measurement data.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation engine testing, in particular to an aviation engine tachometer testing device. Background Art

[0002] Aircraft engine tachometer test equipment plays a vital role in the aviation industry. As the heart of an aircraft, the aircraft engine's tachometer speed is one of the key parameters reflecting its operating status and performance. Tachometer accuracy is directly related to the pilot's judgment of engine operating status, which in turn affects flight safety and economic efficiency. Testing tachometers using this test equipment ensures the accuracy and reliability of measurement results, avoiding misjudgments or failures caused by tachometer errors. This is crucial for ensuring flight safety, improving flight efficiency, and reducing operating costs.

[0003] Existing aircraft engine tachometer test equipment mainly uses an asynchronous motor to drive the active friction wheel to rotate and generate a reference speed. The active friction wheel drives the driven friction wheel to rotate through friction. By adjusting the position between the active friction wheel and the driven friction wheel, the speed of the driven friction wheel is controlled. Finally, the speed of the driven friction wheel is measured and compared with the tachometer reading to realize the tachometer test.

[0004] However, in practical applications, the speed of asynchronous motors is easily affected by external grid voltage fluctuations, which can introduce significant speed control errors. Furthermore, wear between the active and passive friction wheels is inevitable over time, further exacerbating speed deviations and affecting the accuracy of test results. Summary of the Invention

[0005] Aiming at the problem that an asynchronous motor is easily affected by voltage and thus causes rotation speed errors, the utility model provides an aviation engine tachometer test device which is not easily affected by voltage and does not easily cause rotation speed errors.

[0006] To solve the above problems, the present invention adopts a technical solution: an aircraft engine tachometer test device, comprising a housing, a power supply disposed within the housing, the power supply being electrically connected to a brushless DC motor and a programmable controller, the motor control driver of the brushless DC motor being electrically connected to the programmable controller, a sensor adapter being mounted at the output end of the brushless DC motor, the sensor adapter being provided with a mounting interface for mounting a speed sensor to be tested, an input port, an output port, an AC voltmeter, and a display screen being disposed on the outside of the housing, the input port being electrically connected to the output port, and the input port being capable of being electrically connected to the speed sensor to be tested, the output port being capable of being electrically connected to the indicator of the aircraft engine tachometer to be tested, the AC voltmeter being electrically connected to the input port, and the display screen being electrically connected to the programmable controller. The brushless DC motor is capable of simulating an aircraft engine, and the programmable controller is capable of controlling and driving the brushless DC motor to rotate via the motor control driver. The speed sensor on the sensor adapter detects the rotation of the brushless DC motor and generates a three-phase voltage signal. This three-phase voltage signal is transmitted to the input port and, through the output port, to the indicator on the aircraft engine tachometer. The speed displayed on the tachometer is the parameter to be tested. Simultaneously, an AC voltmeter displays the three-phase voltage signal from the speed sensor via the input port. The speed on the tachometer is displayed only when the three-phase voltage signal stabilizes. Furthermore, when the brushless DC motor rotates, the actual speed set by the programmable controller is displayed on the display. The speed displayed on the aircraft engine tachometer is adjusted based on the actual speed displayed on the display, completing the aircraft engine tachometer test.

[0007] Preferably, a control panel is provided on the outside of the housing, and a voltage switching knob is provided on the control panel, and the voltage switching knob is electrically connected to the AC voltmeter. By rotating the voltage switching knob, the display mode of the AC voltmeter can be flexibly switched to realize the display of various voltage states: including displaying disconnection, the AB phase voltage of the speed sensor to be tested, the BC phase voltage of the speed sensor to be tested, or the AC phase voltage of the speed sensor to be tested.

[0008] Preferably, the control panel is further provided with an operation panel, which is electrically connected to the programmable controller. Through the operation panel, the user can conveniently perform customized programming operations on the programmable controller.

[0009] Preferably, the control panel is further provided with a speed adjustment knob, which is electrically connected to the motor control driver and the display screen, respectively. The speed adjustment knob allows the user to manually and precisely control the operation of the motor driver. In manual mode, the actual speed set by the speed adjustment knob is displayed on the display screen.

[0010] Preferably, the side of the box is provided with heat dissipation holes, which can effectively promote the rapid dispersion and discharge of heat and improve the heat dissipation efficiency.

[0011] Preferably, a handle is provided on the side of the box body, which facilitates the movement of the box body.

[0012] The above technical solution demonstrates the advantages of the present invention, which includes a brushless DC motor that can simulate an aircraft engine, and precisely control its rotation via a programmable controller and motor control driver. The rotation of the brushless DC motor causes the speed sensor to generate a voltage signal, which is displayed on an AC voltmeter and also output to the aircraft engine tachometer via an output port. The speed displayed on the aircraft engine tachometer is the parameter to be tested. Simultaneously, the actual speed set is displayed on the display. Based on the actual speed displayed on the display, the speed displayed on the aircraft engine tachometer is adjusted to complete the aircraft engine tachometer test. Because brushless DC motors offer greater speed stability and greater resistance to voltage fluctuations than asynchronous motors, and because this device eliminates the need for active and passive friction wheels, speed errors are effectively reduced. In summary, this test device significantly improves the accuracy of measurement results and effectively mitigates the interference of voltage fluctuations on the measurement process, ensuring the stability and reliability of the measured data. BRIEF DESCRIPTION OF THE DRAWINGS

[0013] In order to more clearly illustrate the technical solution of the present invention, the following is a brief introduction to the drawings required for the description. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0014] Figure 1 It is a structural diagram of a specific implementation method of the utility model.

[0015] Figure 2 This is the schematic diagram of the brushless DC motor control structure.

[0016] Description of main reference numerals

[0017] In the figure: 1. Brushless DC motor, 2. Motor control driver, 3. Programmable controller, 4. Operation panel, 5. AC voltmeter, 6. Sensor adapter, 7. Power supply, 8. Voltage switching knob, 9. Speed ​​adjustment knob, 10. Switch, 11. Input port, 12. Output port, 13. Inverter, 14. Rotor position sensor. DETAILED DESCRIPTION

[0018] In order to make the purpose, features, and advantages of the present invention more obvious and easy to understand, the technical solutions of the present invention will be clearly and completely described below in conjunction with the drawings in the specific embodiments. Obviously, the embodiments described below are only part of the embodiments of the present invention, not all of them. Based on the embodiments in this patent, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this patent.

[0019] An aircraft engine tachometer test device, such as Figure 1 As shown, the test device includes a housing, the sides of which are provided with heat dissipation holes and a handle. A motor control driver 2 and a programmable controller 3 are installed inside the housing. The motor control driver 2 and the programmable controller 3 are electrically connected via a cable, and both the motor control driver 2 and the programmable controller 3 are existing devices. A brushless DC motor 1 is connected to the motor control driver 2, and the motor control driver 2 is capable of driving the brushless DC motor 1 to rotate. A power supply 7 is also installed inside the housing, and the power supply 7 is electrically connected to the brushless DC motor 1, the motor control driver 2, and the programmable controller 3 via a cable. The power supply 7 is capable of providing electrical energy to the device. A control panel is provided on the outside of the housing, and the test device can be controlled via the control panel.

[0020] In this embodiment, the control panel employs the following structure: An operation panel 4 is provided on the control panel, electrically connected to a programmable controller 3 via a cable. A display screen is mounted above the operation panel 4, and both the operation panel 4 and the display screen are electrically connected to the programmable controller 3 via a cable. The operation panel 4 selects different speed sensor models, setting different aircraft engine speeds, generating data commands that are sent to the programmable controller 3. The programmable controller 3 uses these commands to control the motor control driver 2, thereby achieving precise rotational control of the brushless DC motor 1 and realizing automatic control of the brushless DC motor 1.

[0021] In this specific embodiment, a rotor position sensor 14 is provided inside the brushless DC motor 1 to detect the rotor position and ensure the normal operation of the brushless DC motor 1. The brushless DC motor 1 works in conjunction with the motor control driver 2 to achieve precise control of the speed, covering a wide range from 1rpm to 10,000rpm. The brushless DC motor 1 is designed to have a terminal voltage of no more than 300V and an output power of no less than 600W, ensuring a strong driving force. At the same time, the control accuracy is as high as ±1rpm, meeting the needs of high-precision applications. Figure 2 As shown, the voltage equation of the brushless DC motor is as follows:

[0022]

[0023] The electromagnetic torque equation is:

[0024] T em =P n (e a i a +e b i b +e c i c ) / ω r

[0025] Where L a , L b , L c is the self-inductance of the three-phase winding, L a =L b =L c ;L ab is the mutual inductance of phase A and phase B windings, and vice versa, L ab =L ba =L ac =L ca =L bc =L cb =M; p is the differential operator; e a 、e b 、e c is the induced electromotive force of the three-phase winding; P n is the angular velocity of the brushless DC motor.

[0026] In this embodiment, a speed adjustment knob 9 is added to the control panel and is electrically connected to the motor control driver 2 via a cable. Rotating the speed adjustment knob 9 adjusts the resistance value of the built-in multi-turn potentiometer. This change signal is then captured and processed by the motor control driver 2, and then converted by the inverter 13, achieving real-time, precise adjustment and control of the speed of the brushless DC motor 1, thus enabling manual control of the brushless DC motor 1.

[0027] The control panel is integrated with a safe and efficient switch 10, which effectively ensures the electrical safety of the equipment during startup and shutdown, significantly reduces the risk of overheating and short circuit, and ensures the safety of operation and the long-term stable operation of the equipment.

[0028] The output end of the brushless DC motor 1 is equipped with a sensor adapter 6. This adapter 6 has various mounting interfaces, allowing it to accommodate various types of speed sensors. The speed sensor is the device being tested and is an existing device. The speed sensor contains a rotor, which is fixedly connected to the output end of the brushless DC motor 1 via a coupling. When the brushless DC motor 1 rotates, the rotor rotates synchronously, generating a three-phase voltage signal.

[0029] An AC voltmeter 5 is integrated into the control panel, with a voltage selector knob 8 located below the meter. The selector knob 8 is electrically connected to the meter via a cable. Rotating the selector knob 8 switches the display state of the meter 5, including displaying off, the AB phase voltage of the speed sensor to be tested, the BC phase voltage of the speed sensor to be tested, or the AC phase voltage of the speed sensor to be tested.

[0030] An input port 11 and an output port 12 are provided on the outside of the housing. These ports are electrically connected via a cable. The input port 11 can be electrically connected to the speed sensor to be tested, while the output port 12 can be electrically connected to the indicator of the aircraft engine tachometer to be tested. The voltage signal generated by the speed sensor to be tested can be displayed on the AC voltmeter 5 via the input port 11. Simultaneously, the voltage signal generated by the speed sensor to be tested can be output from the output port 12 and displayed on the indicator of the aircraft engine tachometer to be tested.

[0031] In addition, the speed adjustment knob 9 is electrically connected to the display screen. When the actual speed of the DC brushless motor 1 is adjusted by the speed adjustment knob 9, the actual speed of the DC brushless motor 1 is directly displayed on the display screen. Similarly, when the actual speed of the DC brushless motor 1 is adjusted by the programmable controller 3, the actual speed of the DC brushless motor 1 is also directly displayed on the display screen.

[0032] In this specific embodiment, the power supply 7 supports flexible input voltage configuration, which can accept 220VAC AC input and can also be directly connected to 28VDC DC input, thereby fully meeting the diverse power requirements of the entire equipment system and ensuring stable operation of the equipment and efficient energy consumption management.

[0033] The specific use process of the present invention is as follows: by operating the operation panel 4, inputting the preset program and selecting the adapted speed sensor model, the speed of the brushless DC motor 1 is controlled by the motor control driver 2. Alternatively, by operating the operation panel 4, entering the manual mode, rotating the speed adjustment knob 9, the speed of the brushless DC motor 1 is controlled by the motor control driver 2.

[0034] After the brushless DC motor 1 is started, its output drives the rotor of the speed sensor to be tested to rotate synchronously, generating a three-phase AC voltage signal. This voltage signal is displayed on the AC voltmeter 5 via input port 11. Rotating the voltage selector knob 8 switches the display state of the AC voltmeter 5, including displaying off, the AB phase voltage of the speed sensor to be tested, the BC phase voltage of the speed sensor to be tested, or the AC phase voltage of the speed sensor to be tested. Simultaneously, this voltage signal is transmitted via output port 12 to the indicator of the aircraft engine tachometer to be tested, where the speed displayed on the indicator is the speed to be tested.

[0035] Furthermore, when the output end of the brushless DC motor 1 rotates, the set actual speed value is transmitted to the display screen for display. Based on the actual speed displayed on the display screen, the speed displayed on the aircraft engine tachometer to be tested is adjusted to complete the aircraft engine tachometer test.

[0036] As can be seen from the above embodiments, the beneficial effect of the present invention is that the brushless DC motor can simulate an aircraft engine, and its rotation can be precisely controlled by a programmable controller and a motor control driver. The rotation of the brushless DC motor causes the speed sensor to generate a voltage signal. This voltage signal is displayed on the AC voltmeter and output to the aircraft engine tachometer to be tested through the output port. The speed displayed on the aircraft engine tachometer to be tested is the parameter to be tested. At the same time, the set actual speed is displayed on the display. According to the actual speed on the display, the speed displayed on the aircraft engine tachometer to be tested is adjusted to complete the aircraft engine tachometer test. Because brushless DC motors have higher speed stability and stronger resistance to voltage fluctuations than asynchronous motors, and this device eliminates the use of active and driven friction wheels, it effectively reduces speed errors. In summary, this test device significantly improves the accuracy of measurement results and effectively reduces the interference of voltage fluctuations on the measurement process, ensuring the stability and reliability of measurement data.

[0037] The above description of the disclosed embodiments will enable one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be readily apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not limited to the embodiments shown herein but is intended to conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An aircraft engine tachometer test device, comprising a box, characterized in that: A power supply (7) is provided in the box body. The power supply (7) is electrically connected to a brushless DC motor (1) and a programmable controller (3). A motor control driver (2) of the brushless DC motor (1) is electrically connected to the programmable controller (3). A sensor adapter (6) is installed at the output end of the brushless DC motor (1). The sensor adapter (6) is provided with an installation interface for installing a speed sensor to be detected. An input port (11), an output port (12), an AC voltmeter (5) and a display screen are provided on the outside of the box body. The input port (11) is electrically connected to the output port (12), and the input port (11) can be electrically connected to the speed sensor to be detected. The output port (12) can be electrically connected to an indicator of a speed meter of an aircraft engine to be detected. The AC voltmeter (5) is electrically connected to the input port (11), and the display screen is electrically connected to the programmable controller (3).

2. The aircraft engine tachometer test device according to claim 1, characterized in that: A control panel is provided on the outside of the box, and a voltage switching knob (8) is provided on the control panel. The voltage switching knob (8) is electrically connected to the AC voltmeter (5).

3. The aircraft engine tachometer test device according to claim 2, characterized in that: An operating panel (4) is also provided on the control panel, and the operating panel (4) is electrically connected to the programmable controller (3).

4. The aircraft engine tachometer test device according to claim 2, characterized in that: A speed regulating knob (9) is also provided on the control panel, and the speed regulating knob (9) is electrically connected to the motor control driver (2) and the display screen respectively.

5. The aircraft engine tachometer test device according to claim 1, characterized in that: Heat dissipation holes are provided on the side of the box.

6. The aircraft engine tachometer test device according to claim 1, characterized in that: A handle is provided on the side of the box.

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