Steering engine performance testing equipment

Abstract

The utility model discloses steering engine performance testing equipment, which relates to the technical field of steering engine testing equipment and comprises a base, a centering disc is arranged in the middle of the top end of the base, a rudder cylinder is arranged at the top of the centering disc, a rudder wing is arranged in the rudder cylinder, and a fixing ring is clamped at the top of the rudder cylinder. A portal frame is fixedly mounted at the top of the base, a lifting electric cylinder is fixedly connected to one side of the top of the portal frame, a pressing electric cylinder is fixedly connected to one side of the top of the portal frame, and a lifting assembly is arranged at the telescopic end of the lifting electric cylinder. According to the utility model, the lifting assembly, the rudder tube, the lifting assembly and the photoelectric sensor are arranged in a matched manner, so that the time required for quickly opening the four rudder wings of the steering engine can be automatically measured, the opening time of the four rudder wings can be synchronously measured, the device has the characteristics of accurate, reliable and efficient measurement, the problem of time and labor waste of manual testing is avoided, and the testing efficiency is improved. And convenience is brought to the test of the rudder wing.

Description

Technical Field

[0001] This utility model relates to the technical field of servo motor testing equipment, and in particular to a servo motor performance testing equipment. Background Technology

[0002] A servo motor is an actuator in a flight control system that manipulates the rotation of aircraft control surfaces. It is classified into electric servos, hydraulic servos, and electro-hydraulic servos. The servo wing refers to the control surface used to control the direction and position of moving devices such as aircraft or robots. Specifically, on an aircraft, a servo motor controls the movement of control surfaces such as ailerons and elevators to achieve actions such as roll and pitch. A servo motor typically has four retractable winglets; normally, the winglets retract into the control tube, and during operation, they deploy instantaneously. To meet the overall performance requirements of the servo motor, the deployment time of the winglets needs to be accurately measured during the production process; therefore, servo motor performance testing equipment is required to test its performance.

[0003] The existing measurement method is as follows: manually retract the rudder wing, tie the rudder wing to the outside of the rudder tube with a rubber band so that the rudder wing is inside the rudder tube, prepare a high-speed camera, and quickly remove the rubber band during measurement while the high-speed camera captures the opening process of the rudder wing to obtain the rudder wing opening time.

[0004] The aforementioned measurement method is inconvenient to operate, requiring manual release of the rubber bands while simultaneously recording video. This necessitates at least two people working together. Furthermore, the synchronicity of the four servo wings' opening during manual release cannot be guaranteed, reducing test accuracy. Additionally, the circular distribution of the four servo wings necessitates four high-speed cameras to simultaneously measure their opening time, making the process cumbersome. Therefore, it is necessary to propose a servo motor performance testing device to address these issues. Utility Model Content

[0005] The purpose of this invention is to provide a servo motor performance testing device to solve the problems mentioned in the background art, such as the inconvenience of operation, the need to manually release the rubber band while filming, the requirement of at least two people operating simultaneously, the inability to guarantee the synchronicity of the opening of the four servo wings when manually releasing the rubber band, which reduces the accuracy of the test, and the fact that the four servo wings are circumferentially distributed, requiring four high-speed cameras to measure the opening time of the four servo wings simultaneously, making the process cumbersome.

[0006] To achieve the above objectives, the present invention provides the following technical solution: a servo motor performance testing device, including a base, a centering plate is provided at the center of the top of the base, a servo tube is placed on the top of the centering plate, a servo wing is provided inside the servo tube, and a fixing ring is snapped into the top of the servo tube.

[0007] A gantry frame is fixedly installed on the top of the base. A lifting electric cylinder is fixedly connected to one side of the top of the gantry frame, and a pressing electric cylinder is fixedly connected to one side of the top of the gantry frame. A lifting component is provided at the telescopic end of the lifting electric cylinder, and a pressure plate is fixedly connected to the telescopic end of the pressing electric cylinder.

[0008] A sensor bracket is provided on the top of the base. The sensor bracket includes a sensor bracket base plate, a damping hinge, and a sensor bracket arm. The bottom of the sensor bracket base plate is fixedly connected to the top of the base, and the top of the sensor bracket base plate is rotatably connected to the bottom of the sensor bracket arm through the damping hinge. Photoelectric sensors are fixedly installed on the side of the sensor bracket base plate and the side of the sensor bracket arm.

[0009] Preferably, a positioning plate is provided on the top of the base, and a vertical groove is provided on the outside of the rudder barrel, with the positioning plate engaging with the vertical groove.

[0010] Preferably, the fixing ring is cylindrical, and the inner diameter of the fixing ring is matched with the inner diameter of the rudder barrel.

[0011] Preferably, the lifting assembly includes a lifting ring and a linear bearing. The top of the lifting ring is fixedly connected to the telescopic end of the lifting electric cylinder, and the interiors of both ends of the lifting ring are respectively connected to the external sliders of the linear bearing.

[0012] A lifting groove is provided on the outside of the bottom end of the fixed ring, and the lifting groove fits into the lifting ring.

[0013] Preferably, the number of sensor brackets is four, and the four sensor brackets are circumferentially distributed on the top of the base.

[0014] The technical effects and advantages of this utility model are as follows:

[0015] 1. By coordinating the lifting components, rudder barrel, lifting components, and photoelectric sensors, the system automatically measures the time required for the four rudder wings of the servo to rapidly open, and simultaneously measures the opening time of the four rudder wings. It features accurate, reliable, and efficient measurement, avoiding the time-consuming and laborious problem of manual testing, and bringing convenience to rudder wing testing.

[0016] 2. By setting up a sensor bracket and a photoelectric sensor, the position of the photoelectric sensor can be adjusted through the sensor bracket, which can realize the measurement of the rudder wing opening time of servos of the same type within a certain size range, thus improving the practicality of the device. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the servo motor performance testing equipment of this utility model.

[0018] Figure 2This is a schematic diagram showing the installation positions of the centering plate and the positioning plate in this utility model.

[0019] Figure 3 This is a schematic diagram of the lifting component in this utility model.

[0020] Figure 4 This is a schematic diagram of the structure of the fixed ring fixing the rudder in this utility model.

[0021] Figure 5 This is a schematic diagram of the sensor bracket and sensor in this utility model.

[0022] In the diagram: 1. Base; 2. Gantry frame; 3. Lifting assembly; 3.1. Lifting ring; 3.2. Linear bearing; 4. Fixing ring; 5. Pressure plate; 6. Lifting electric cylinder; 7. Clamping electric cylinder; 8. Rudder barrel; 8.1. Rudder wing; 8.2. Vertical slot; 9. Sensor bracket; 9.1. Sensor bracket base plate; 9.2. Damping hinge; 9.3. Sensor bracket arm; 10. Photoelectric sensor; 11. Centering plate; 12. Positioning plate. Detailed Implementation

[0023] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0024] This utility model provides, for example Figures 1-5 The illustrated servo motor performance testing device includes a base 1, a centering plate 11 at the center of the top of the base 1, a servo cylinder 8 on top of the centering plate 11, a servo wing 8.1 inside the servo cylinder 8, and a retaining ring 4 engaged at the top of the servo cylinder 8. A positioning plate 12 is provided on the top of the base 1, and a vertical groove 8.2 is formed on the outside of the servo cylinder 8. The positioning plate 12 is engaged with the vertical groove 8.2. The retaining ring 4 is cylindrical, and its inner diameter matches the inner diameter of the servo cylinder 8. The retaining ring 4 can be used to press down the servo wing 8.1 inside the servo cylinder 8, the centering plate 11 can be used to position the servo cylinder 8, and the positioning plate 12 engaged in the vertical groove 8.2 can be used to limit the movement of the servo cylinder 8.

[0025] Additionally, a gantry frame 2 is fixedly installed on the top of the base 1. A lifting electric cylinder 6 is fixedly connected to one side of the top of the gantry frame 2, and a pressing electric cylinder 7 is also fixedly connected to one side of the top of the gantry frame 2. A lifting assembly 3 is provided at the telescopic end of the lifting electric cylinder 6, and a pressure plate 5 is fixedly connected to the telescopic end of the pressing electric cylinder 7. The lifting assembly 3 includes a lifting ring 3.1 and a linear bearing 3.2. The top of the lifting ring 3.1 is fixedly connected to the telescopic end of the lifting electric cylinder 6, and the interiors of both ends of the lifting ring 3.1 are respectively connected to the external sliders of the linear bearing 3.2. A lifting groove is provided on the exterior of the bottom end of the fixed ring 4, and the lifting groove fits against the lifting ring 3.1. When the pressing electric cylinder 7 is opened, the pressure plate 5 moves downward, pressing the rudder barrel 8. Then, the lifting electric cylinder 6 is opened, causing the lifting ring 3.1 to move upward. The lifting ring 3.1 moves upward through the lifting groove, causing the fixed ring 4 to move upward, facilitating the deployment of the rudder wing 8.1 inside the rudder barrel 8.

[0026] Finally, a sensor bracket 9 is installed on the top of the base 1. The sensor bracket 9 includes a sensor bracket base plate 9.1, a damping hinge 9.2, and a sensor bracket arm 9.3. The bottom of the sensor bracket base plate 9.1 is fixedly connected to the top of the base 1, and the top of the sensor bracket base plate 9.1 is rotatably connected to the bottom of the sensor bracket arm 9.3 through the damping hinge 9.2. Photoelectric sensors 10 are fixedly installed on the sides of both the sensor bracket base plate 9.1 and the sensor bracket arm 9.3. There are four sensor brackets 9, which are circumferentially distributed on the top of the base 1. The rudder opening time can be measured by the time difference sensed by two photoelectric sensors 10. All data during the test is transmitted to a computer, and detailed test results can be obtained through software processing. At the same time, the position of the photoelectric sensors 10 can be adjusted through the sensor brackets 9, which can realize the measurement of the rudder opening time of rudders 8.1 of the same type and within a certain size range, thus improving the practicality of the device.

[0027] Working principle: Before measurement, the rudder wing 8.1 retracted into the rudder tube 8 is pressed down by the fixing ring 4. Then, the rudder tube 8 with the fixing ring 4 is placed on the base 1. The lifting groove of the outer circle of the fixing ring 4 fits with the lifting ring 3.1. The centering plate 11 positions the rudder tube 8 at the center of the base 1. The radial positioning of the rudder tube 8 is achieved by the positioning plate 12 being clamped in the vertical groove 8.2 of the outer circle of the rudder tube 8. After the rudder tube 8 is positioned, the rudder wing 8.1 is exactly aligned with the groove of the photoelectric sensor 10. After adjusting the position of the photoelectric sensor 10, the clamping electric cylinder 7 is activated. The extension rod of the clamping electric cylinder 7 descends, causing the pressure plate 5 to press against the rudder tube 8. The lifting electric cylinder 6 is activated, causing the lifting ring 3.1 and the fixed ring 4 to rise synchronously. The rudder wing 8.1 opens instantaneously. Each rudder wing 8.1 passes through the corresponding upper and lower photoelectric sensors 10 sequentially from opening to closing. The rudder wing opening time is measured by the time difference sensed by the two photoelectric sensors 10. All data during the test is transmitted to the computer, and detailed test results can be obtained after software processing.

Claims

1. A steering gear performance testing apparatus comprising a base (1), characterised in that: The middle part of the top end of the base (1) is provided with a centering disc (11), the top of the centering disc (11) is placed with a rudder cylinder (8), the inside of the rudder cylinder (8) is provided with a rudder wing (8.1), and the top of the rudder cylinder (8) is clamped with a fixing ring (4); The top of the base (1) is fixedly installed with a gantry (2), one side of the top of the gantry (2) is fixedly connected with a lifting electric cylinder (6), and one side of the top of the gantry (2) is fixedly connected with a pressing electric cylinder (7), the telescopic end of the lifting electric cylinder (6) is provided with a lifting assembly (3), and the telescopic end of the pressing electric cylinder (7) is fixedly connected with a pressing disc (5); The top of the base (1) is provided with a sensor support (9), the sensor support (9) comprises a sensor support bottom plate (9.1), a damping hinge (9.2) and a sensor support arm (9.3), the bottom of the sensor support bottom plate (9.1) is fixedly connected with the top of the base (1), and the top of the sensor support bottom plate (9.1) is rotatably connected with the bottom of the sensor support arm (9.3) through the damping hinge (9.2), and the side surface of the sensor support bottom plate (9.1) and the side surface of the sensor support arm (9.3) are both fixedly installed with a photoelectric sensor (10).

2. The rudder performance testing device according to claim 1, characterized in that: The top of the base (1) is provided with a positioning plate (12), the outside of the rudder cylinder (8) is provided with a vertical groove (8.2), and the positioning plate (12) is clamped between the vertical groove (8.2).

3. The rudder performance testing device according to claim 1, characterized in that: The fixing ring (4) is a circular ring cylinder, and the inner circle diameter of the fixing ring (4) is matched with the inner circle diameter of the rudder cylinder (8).

4. The rudder performance testing device according to claim 1, characterized in that: The lifting assembly (3) comprises a lifting ring (3.1) and a linear bearing (3.2), the top of the lifting ring (3.1) is fixedly connected with the telescopic end of the lifting electric cylinder (6), and the inner parts of the two ends of the lifting ring (3.1) are respectively connected with the outer sliding blocks of the linear bearings (3.2); The bottom end of the fixing ring (4) is provided with a lifting groove on the outside, and the lifting groove is matched with the lifting ring (3.1).

5. The rudder performance testing device according to claim 1, characterized in that: The number of the sensor supports (9) is four, and the four sensor supports (9) are circumferentially distributed on the top of the base (1).

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