Testing device for aero-engine driving device

Abstract

The utility model discloses an aero-engine driving device testing device, which comprises a crank to be tested and is characterized by comprising a power end and a load end, the power end comprises a servo motor, the load end comprises a magnetic powder brake, and two ends of the crank to be tested are fixedly connected with the servo motor and the magnetic powder brake respectively. The device is simple in structure and high in automation degree, the servo motor is used for providing power, the magnetic powder brake is used for providing counter torque, the torque, the rotating speed and the output power are collected through the torque rotating speed power collector, and automatic testing of the aero-engine driving device is achieved. Except manual product installation, other processes are all completed by a machine, and the automation rate is high.

Description

Technical Field

[0001] The utility model relates to the field of aviation engines, in particular to an aviation engine drive device test device. Background Art

[0002] The torque performance test of aircraft engine drive devices involves the load torque test of the crank. In the prior art, the torque performance test of aircraft engine drive devices mainly relies on manual testing, which requires manually fixing the crank and then manually applying torque to the crank.

[0003] The advantages and disadvantages of existing aircraft engine drive device testing methods are as follows: Advantages: Manual torque application can reach the specified torque instantly, shortening testing time. Disadvantages: 1. Manual torque application may not simulate the actual stress conditions of the product under actual operating conditions. 2. Manual torque application is labor-intensive. Utility Model Content

[0004] The purpose of the utility model is to provide an aero-engine drive device test device to solve the problems of low test accuracy in the prior art.

[0005] The utility model is implemented by adopting the following technical scheme: a test device for an aircraft engine drive device, including a crank to be tested, characterized in that it includes a power end and a load end, the power end includes a servo motor, the load end includes a magnetic powder brake, and the two ends of the crank to be tested are fixedly connected to the servo motor and the magnetic powder brake respectively.

[0006] Furthermore, the servo motor is mounted on a linear sliding module, and the sliding direction of the linear sliding module is along the axial direction of the servo motor output shaft.

[0007] Furthermore, the linear sliding module includes a power end bracket and a linear guide rail, the servo motor is fixed on the power end bracket, the power end bracket and the linear guide rail are slidably matched, and a locking mechanism is provided.

[0008] Furthermore, the magnetic powder brake is mounted on a rotary sliding module, which is rotatably connected to a rotating shaft. The rotating shaft rotates horizontally, and the axis of the rotating shaft intersects and is perpendicular to the axis of the servo motor output shaft.

[0009] Furthermore, the rotary sliding module includes an arc guide rail and a load end bracket, the magnetic powder brake is installed on the load end bracket, one end of the load end bracket is slidingly connected to the arc guide rail, and the other end is rotationally connected to the rotating shaft.

[0010] Furthermore, the power end and the load end are fixedly mounted on two separate workbenches respectively.

[0011] Furthermore, the servo motor and the magnetic powder brake are respectively provided with a power end speed torque sensor and a load end speed torque sensor, and both the power end speed torque sensor and the load end speed torque sensor are connected to a torque speed power collector.

[0012] Furthermore, the servo motor and the magnetic powder brake are both connected to the crank to be tested via a quick-change connector.

[0013] The beneficial effects of the present invention are:

[0014] (1) High degree of automation. By using a servo motor to provide power, a magnetic powder brake to provide reaction torque, and a torque, speed, and power acquisition instrument to collect torque, speed, and output power, automatic testing of aircraft engine drive devices is achieved. Except for manual installation of the product, the rest of the process is completed by machines, with a high degree of automation.

[0015] (2) High accuracy. The power end speed requirements, precision adjustment, and torque output requirements can be achieved by configuring a servo motor with a reducer. The speed regulation function can be achieved through the servo motor driver. The loading end can adopt the method of magnetic powder brake + torque speed sensor. The size of the loading damping can be adjusted by the programmable loading power supply, thereby adjusting the size of the magnetic powder brake torque output. The torque, speed, and output power are collected by the torque, speed, and power acquisition instrument, thereby realizing closed-loop control of torque, speed, and output functions. The actual product usage environment is simulated to accurately test whether the product is qualified.

[0016] (3) High production efficiency. By replacing the quick-change connector, different types of aircraft engine drive device tests can be carried out. After using this method, the equipment has strong versatility and can adapt to a variety of aircraft engine drive devices. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. 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 the structures shown in these drawings without paying any creative work.

[0018] Figure 1 This is a front view of an aircraft engine drive device test device;

[0019] Figure 2 This is a top view of an aircraft engine drive device test device;

[0020] In the figure, 1-servo motor, 2-power end speed and torque sensor, 3-linear sliding module, 4-crank handle bracket, 5-magnetic powder brake, 6-rotary sliding module, 7-load end speed and torque sensor, 8-rotating shaft, 31-power end bracket, 32-linear guide, 61-arc guide, 62-load end bracket. DETAILED DESCRIPTION

[0021] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0022] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but rather merely represents selected embodiments of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort are also within the scope of protection of the present invention.

[0023] like Figure 1-2 As shown, an aircraft engine drive unit test device comprises two main components: a power end and a load end. Its operating principle is as follows: On the power end, a servo motor 1 is coupled with a 1:12 planetary reducer, and a speed and torque sensor 2 is used to meet the product's power input requirements. On the load end, a magnetic powder brake 5 and a speed and torque sensor 7 are used. The loading damping can be adjusted using a programmable loading power supply, and a torque, speed, and power acquisition instrument is used to collect torque, speed, and output power.

[0024] The power end is used to drive the product to rotate under different test loads. The power end includes a servo motor 1, a planetary gear reducer, a power end speed torque sensor 2, a linear sliding module 3 and a power end quick connector. The power end can be separated from the torque test bench as a whole, and can meet the switching requirements of manual loading and electric loading modes. The linear sliding module 3 can control the left and right movement of the power end to adapt to the test requirements of products of different lengths. The linear sliding module 3 includes a power end bracket 31 and a linear guide rail 32. The servo motor 1 is fixed on the power end bracket 31. The power end bracket 31 slides with the linear guide rail 32 and is provided with a locking mechanism.

[0025] The load end can provide different test torques for the product. The load end is composed of a magnetic powder brake 5, a load end speed torque sensor 7, a rotary sliding module 6, a load end quick-change joint and a crank bracket 4. The magnetic powder brake 5 provides torque for the test, and the magnitude of the output torque of the magnetic powder brake is controlled by the load end speed torque sensor 7. The load end speed torque sensor 7 can measure the torque of the load end during the test. The magnetic powder brake 5 and the load end speed torque sensor 7 are installed on the rotary sliding module 6. Controlling the rotary sliding module 6 to rotate to different positions can meet the test requirements of different products. The rotary sliding module 6 includes an arc guide rail 61 and a load end bracket 62. The magnetic powder brake 5 and the load end speed torque sensor 7 are installed on the load end bracket 62. One end of the load end bracket 62 is slidably connected to the arc guide rail 61, and the other end is rotationally connected to the rotating shaft 8. The rotating shaft 8 is set on the axis of the servo motor 1.

[0026] The above embodiments describe the basic principles, main features, and advantages of the present invention. Those skilled in the art should understand that the present invention is not limited to the above embodiments. The above embodiments and descriptions are merely illustrative of the principles of the present invention. Without departing from the spirit and scope of the present invention, modifications and variations made by those skilled in the art without departing from the spirit and scope of the present invention should be within the scope of protection of the appended claims.

Claims

1. An aircraft engine drive device test device, comprising a crank to be tested, characterized in that: The invention comprises a power end and a load end, wherein the power end comprises a servo motor (1), and the load end comprises a magnetic powder brake (5). Both ends of the crank to be tested are fixedly connected to the servo motor (1) and the magnetic powder brake (5), respectively. The power end and the load end are fixedly mounted on two separate workbenches.

2. The aircraft engine drive device test device according to claim 1, characterized in that: The servo motor (1) is mounted on a linear sliding module (3), and the sliding direction of the linear sliding module (3) is along the axial direction of the output shaft of the servo motor (1).

3. The aircraft engine drive device test device according to claim 2, characterized in that: The linear sliding module (3) comprises a power end bracket (31) and a linear guide rail (32); the servo motor (1) is fixed on the power end bracket (31); the power end bracket (31) and the linear guide rail (32) are in sliding engagement and are provided with a locking mechanism.

4. The aircraft engine drive device test device according to claim 1, characterized in that: The magnetic powder brake (5) is mounted on a rotating sliding module (6), which is rotatably connected to a rotating shaft (8). The rotating shaft (8) rotates horizontally, and the axis of the rotating shaft (8) intersects and is perpendicular to the axis of the output shaft of the servo motor (1).

5. The aircraft engine drive device test device according to claim 4, characterized in that: The rotary sliding module (6) comprises an arc guide rail (61) and a load end bracket (62), the magnetic powder brake (5) is mounted on the load end bracket (62), one end of the load end bracket (62) is slidably connected to the arc guide rail (61), and the other end is rotationally connected to the rotating shaft (8).

6. The aircraft engine drive device test device according to claim 1, characterized in that: The servo motor (1) and the magnetic powder brake (5) are respectively provided with a power end speed torque sensor (2) and a load end speed torque sensor (7), and both the power end speed torque sensor (2) and the load end speed torque sensor (7) are connected to a torque speed power acquisition instrument.

7. The aircraft engine drive device test device according to claim 1, characterized in that: The servo motor (1) and the magnetic powder brake (5) are both connected to the crank to be tested via a quick-change joint.

Images