Automatic running-in test device for aircraft ball screw actuator

Abstract

The utility model discloses an airplane ball screw actuator automatic running-in test device, comprising a running-in test device main body, two sides of the running-in test device main body are fixedly connected with slide rails, the inner walls of the slide rails are slidably connected with slide blocks, the upper surface of the running-in test device main body is fixedly connected with a housing, and the housing is fixedly connected with an air cylinder. The outer surface of the shell is fixedly connected with a servo motor, the output end of the servo motor is fixedly connected with a first bevel gear, a plurality of ball screw actuators are connected to a rotating connecting rod in series through a flexible rotating shaft, twelve ball screw actuators are fixed into a row through a sliding rail and a sliding block, then the first bevel gear is rotated through the servo motor, and the second bevel gear is driven to rotate. The meshed bevel gear II and a rotary connecting rod on the inner wall of the bevel gear II are rotated, and the ball screw actuator is subjected to running-in; through rotation of the screw motor on the sliding seat, the camera in threaded connection can move, monitoring is carried out when the ball screw actuator carries out running-in, and abnormal conditions can be found in time.

Description

Technical Field

[0001] This utility model relates to the field of ball screw actuator technology, and in particular to an automatic break-in test device for aircraft ball screw actuators. Background Technology

[0002] The ball screw actuator of an aircraft engine is an important component of the aircraft's air system. The ball screw actuator of an aircraft engine uses a flexible shaft linkage switch to control the bleed air switch, thereby achieving the purpose of adjustable bleed air switch. The number of ball screw actuators sent for repair in civil airliner engines is relatively large. After their repair and assembly, due to the preload effect, the actuators are not flexible in operation. They can only be manually operated one by one for break-in, which is extremely inefficient. Utility Model Content

[0003] The purpose of this invention is to at least solve one of the technical problems existing in the prior art, and to provide an automatic running-in testing device for aircraft ball screw actuators. Multiple ball screw actuators are connected in series on a rotating connecting rod via a flexible rotating shaft. Twelve ball screw actuators are fixed in a row by a slide rail and a slider. A servo motor rotates a first bevel gear, causing a meshing second bevel gear and the rotating connecting rod on its inner wall to rotate, thus running in the ball screw actuators. The rotation of the screw motor on the sliding seat allows the threaded camera to move, monitoring the ball screw actuators during the running-in process and enabling timely detection of abnormalities.

[0004] This utility model also provides an automatic break-in testing device for an aircraft ball screw actuator, comprising: a break-in testing device body; slide rails fixedly connected to both sides of the break-in testing device body; a slider slidably connected to the inner wall of the slide rails; a housing fixedly connected to the upper surface of the break-in testing device body; a servo motor fixedly connected to the outer surface of the housing; a bevel gear one fixedly connected to the output end of the servo motor; a bevel gear two meshing with the outer surface of the bevel gear one; a rotating connecting rod fixedly connected to the inner wall of the bevel gear two; a sliding seat fixedly connected to the outer surface of the break-in testing device body; a ball screw motor fixedly connected to the outer surface of the sliding seat; and a camera threadedly connected to the output end of the ball screw motor.

[0005] According to the present invention, an automatic running-in testing device for an aircraft ball screw actuator is provided, wherein the outer surface of the rotating connecting rod is rotatably connected to the housing, and the position of the rotating connecting rod is located above the slider. The rotatable connection between the rotating connecting rod and the housing enables the device to achieve a flexible structural design.

[0006] According to the present invention, an automatic running-in testing device for an aircraft ball screw actuator is provided, wherein the first bevel gear and the second bevel gear are located inside the housing, and the upper surface of the housing is detachably connected to a cover. The location of the first bevel gear and the second bevel gear inside the housing effectively prevents the influence of the external environment on the gear system, thereby improving the durability and reliability of the device.

[0007] According to the present invention, an automatic running-in testing device for an aircraft ball screw actuator is provided, wherein a protective cover is fixedly connected to the outer surface of the housing, and the servo motor is located inside the protective cover. The design of the protective cover can effectively protect the servo motor from external impacts and extend the service life of the motor.

[0008] According to the present invention, an automatic running-in testing device for an aircraft ball screw actuator is provided, wherein a second protective cover is fixedly connected to the outer surface of the sliding seat, and the position of the screw motor is located inside the second protective cover. The design of the second protective cover can effectively protect the servo motor from external impacts and extend the service life of the motor.

[0009] According to the present invention, an automatic running-in testing device for an aircraft ball screw actuator is provided, wherein a guide rod is fixedly connected to the inner side of the sliding seat, and the outer surface of the guide rod is slidably connected to the camera. The design of the guide rod allows the camera to remain stable during movement, thereby improving the accuracy of image acquisition and monitoring.

[0010] According to the present invention, an automatic break-in testing device for an aircraft ball screw actuator is provided. The camera is located outside the slider, and the lower surface of the camera is slidably connected to the sliding seat. The camera's location outside the slider allows for better acquisition of the overall break-in process and effective recording and monitoring of the working status.

[0011] According to the present invention, an automatic running-in testing device for an aircraft ball screw actuator is provided with anti-slip pads on the lower surfaces of the main body and the sliding seat of the running-in testing device. Ventilation openings are provided on the outer surfaces of the first and second protective covers. The anti-slip pads on the lower surfaces of the main body and the sliding seat of the running-in testing device can effectively prevent slippage during the testing process, making the device stable and reliable. The ventilation opening design of the first and second protective covers helps to dissipate internal heat and maintain the normal operating temperature of the equipment.

[0012] Beneficial effects

[0013] 1. Compared with the existing technology, the automatic running-in test device for aircraft ball screw actuators connects multiple ball screw actuators in series on a rotating connecting rod through a flexible rotating shaft. The twelve ball screw actuators are fixed in a row by a slide rail and a slider. Then, a servo motor is used to rotate bevel gear one, causing the meshing bevel gear two and the rotating connecting rod on its inner wall to rotate, thereby running in the ball screw actuators.

[0014] 2. Compared with existing technologies, this automatic running-in test device for aircraft ball screw actuators uses the rotation of the screw motor on the sliding seat to move the threaded camera, which monitors the ball screw actuator during the running-in process and can detect abnormalities in a timely manner. Attached Figure Description

[0015] The present invention will be further described below with reference to the accompanying drawings and embodiments:

[0016] Figure 1 This is an overall structural diagram of the automatic break-in testing device for aircraft ball screw actuators of this utility model;

[0017] Figure 2 This is a schematic diagram of the sliding seat connection of the automatic break-in test device for aircraft ball screw actuators of this utility model;

[0018] Figure 3 This is a schematic diagram of the guide rail connection of the automatic break-in test device for aircraft ball screw actuators of this utility model;

[0019] Figure 4 This is a schematic diagram of the rotating connecting rod connection of the automatic break-in test device for aircraft ball screw actuators according to this utility model.

[0020] Legend:

[0021] 1. Main body of the break-in test device; 2. Slide rail; 3. Slider; 4. Housing; 5. Servo motor; 6. Bevel gear one; 7. Bevel gear two; 8. Rotating connecting rod; 9. Sliding seat; 10. Screw motor; 11. Camera; 12. Guide rod; 13. Protective cover one; 14. Protective cover two; 15. Cover. Detailed Implementation

[0022] This section will describe in detail the specific embodiments of the present utility model. The preferred embodiments of the present utility model are shown in the accompanying drawings. The purpose of the drawings is to supplement the textual description with graphics, so that people can intuitively and vividly understand each technical feature and the overall technical solution of the present utility model, but they should not be construed as limiting the scope of protection of the present utility model.

[0023] Reference Figure 1-4This utility model discloses an automatic running-in testing device for an aircraft ball screw actuator, comprising: a running-in testing device body 1 for automatically running-in testing the ball screw actuator, and a controller mounted on it. After parameter setting, automatic running-in is possible. Slide rails 2 are fixedly connected to both sides of the running-in testing device body 1, allowing sliders 3 to slide. Slider 3 is slidably connected to the inner wall of the slide rails 2, providing a position for the installation of the ball screw actuator. A housing 4 is fixedly connected to the upper surface of the running-in testing device body 1, protecting the internal bevel gear 6 and bevel gear 7. A servo motor 5 is fixedly connected to the outer surface of the housing 4, providing power for the rotation of bevel gear 6. A bevel gear 6 is fixedly connected to the output end of motor 5, causing the meshing bevel gear 7 to rotate. The outer surface of bevel gear 6 is meshed with bevel gear 7, allowing the rotating connecting rod 8 to rotate. The inner wall of bevel gear 7 is fixedly connected with the rotating connecting rod 8, which is used to connect multiple ball screw actuators in series via a flexible rotating shaft. A sliding seat 9 is fixedly connected to the outer surface of the main body 1 of the running-in test device, which is used to provide a position for the installation of the ball screw motor 10. The outer surface of the sliding seat 9 is fixedly connected with the ball screw motor 10. By rotating, the meshing camera 11 can be moved. The output end of the ball screw motor 10 is threadedly connected to the camera 11, which monitors the ball screw actuator during the running-in process.

[0024] The outer surface of the rotating connecting rod 8 is rotatably connected to the housing 4. The rotating connecting rod 8 is located above the slider 3. The bevel gear 6 and bevel gear 7 are located inside the housing 4. The upper surface of the housing 4 is detachably connected to a cover 15 for sealing the housing 4. The outer surface of the housing 4 is fixedly connected to a protective cover 13 to protect the internal servo motor 5. The servo motor 5 is located inside the protective cover 13. The outer surface of the sliding seat 9 is fixedly connected to a protective cover 14 to protect the internal lead screw motor 10. The lead screw motor 10 is located inside the protective cover 14. The inner side of the sliding seat 9 is fixedly connected to a guide rod 12 to guide the movement of the camera 11. The outer surface of the guide rod 12 is slidably connected to the camera 11. The camera 11 is located outside the slider 3. The lower surface of the camera 11 is slidably connected to the sliding seat 9. The lower surface of the running-in test device body 1 and the sliding seat 9 are provided with anti-slip pads. The outer surfaces of the protective cover 13 and the protective cover 14 are provided with ventilation holes.

[0025] Working principle: In use, multiple ball screw actuators are connected in series on the rotating connecting rod 8 via a flexible rotating shaft. The twelve ball screw actuators are fixed in a row by the slide rail 2 and the slider 3. Then, the servo motor 5 rotates the first bevel gear 6, causing the meshing second bevel gear 7 and the rotating connecting rod 8 on its inner wall to rotate, thus running in the ball screw actuators. The screw motor 10 on the sliding seat 9 rotates, allowing the threaded camera 11 to move and monitor the ball screw actuators during the running-in process, enabling timely detection of abnormalities.

[0026] The embodiments of the present utility model have been described in detail above with reference to the accompanying drawings. However, the present utility model is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present utility model.

Claims

1. An automatic break-in testing device for aircraft ball screw actuators, characterized in that, include: The break-in test device body (1) has slide rails (2) fixedly connected to both sides of the break-in test device body (1), and sliders (3) slidably connected to the inner wall of the slide rails (2). The upper surface of the break-in test device body (1) is fixedly connected to a housing (4), and a servo motor (5) is fixedly connected to the outer surface of the housing (4). The output end of the servo motor (5) is fixedly connected to a bevel gear one (6), and a bevel gear two (7) meshes with the outer surface of the bevel gear one (6). A rotating connecting rod (8) is fixedly connected to the inner wall of the bevel gear two (7). The outer surface of the break-in test device body (1) is fixedly connected to a sliding seat (9), and a lead screw motor (10) is fixedly connected to the outer surface of the sliding seat (9). The output end of the lead screw motor (10) is threadedly connected to a camera (11).

2. The automatic break-in testing device for aircraft ball screw actuators according to claim 1, characterized in that, The outer surface of the rotating connecting rod (8) is rotatably connected to the housing (4), and the position of the rotating connecting rod (8) is above the slider (3).

3. The automatic break-in testing device for aircraft ball screw actuators according to claim 1, characterized in that, The bevel gear one (6) and bevel gear two (7) are located inside the housing (4), and the upper surface of the housing (4) is detachably connected to a cover (15).

4. The automatic break-in testing device for aircraft ball screw actuators according to claim 1, characterized in that, The outer surface of the housing (4) is fixedly connected to a protective cover (13), and the servo motor (5) is located inside the protective cover (13).

5. The automatic break-in testing device for aircraft ball screw actuators according to claim 1, characterized in that, The outer surface of the sliding seat (9) is fixedly connected to a protective cover (14), and the position of the lead screw motor (10) is located inside the protective cover (14).

6. The automatic break-in testing device for aircraft ball screw actuators according to claim 1, characterized in that, A guide rod (12) is fixedly connected to the inner side of the sliding seat (9), and the outer surface of the guide rod (12) is slidably connected to the camera (11).

7. The automatic break-in testing device for aircraft ball screw actuators according to claim 1, characterized in that, The camera (11) is located outside the slider (3), and the lower surface of the camera (11) is slidably connected to the sliding seat (9).

8. The automatic break-in testing device for aircraft ball screw actuators according to claim 4, characterized in that, The lower surfaces of the main body (1) and sliding seat (9) of the break-in test device are provided with anti-slip pads, and the outer surfaces of the first protective cover (13) and the second protective cover (14) are provided with ventilation openings.

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