Testing device for airplane turbulent flow actuating system

Abstract

The utility model discloses a testing device for an airplane turbulent flow actuating system, and relates to the technical field of actuating system testing. The testing device for the airplane turbulent flow actuating system comprises a mounting groove, a testing device and a testing device, and the cross section of the mounting groove is C-shaped; the testing mechanism is arranged above the mounting groove, the testing mechanism comprises a rotating plate, hydraulic actuating cylinders and a hydraulic vibration exciter, the rotating plate is arranged above the mounting groove, three groups of holes are formed in the outer side of the rotating plate, the hydraulic actuating cylinders are fixedly mounted on the outer sides of the two groups of holes, and the hydraulic vibration exciter is fixedly mounted on the outer side of the one group of holes. Rubber pads on the outer sides of the telescopic rods are attached to the surface of a spoiler, starting of a hydraulic actuator cylinder is controlled, the free end of the hydraulic actuator cylinder stretches out and draws back, the two telescopic rods are driven to stretch out and draw back to push the spoiler, airflow resistance is simulated, configuration blocks hung on the spoiler are reduced, starting of a hydraulic vibration exciter is controlled, and the free end of the hydraulic vibration exciter stretches out and draws back. And a group of telescopic rods are driven to stretch to push the spoiler to vibrate.

Description

Technical Field

[0001] This utility model relates to the field of actuation system testing technology, and in particular to a testing device for aircraft turbulence actuation systems. Background Technology

[0002] An existing testing device for aircraft spoiler actuation systems has several drawbacks. Firstly, it is difficult to simulate airflow resistance. Secondly, it is difficult to apply counterweights to the spoiler, and the application of counterweights can easily damage the spoiler's surface coating, resulting in more harm than good, increased testing costs, and reduced effectiveness. Thirdly, it is difficult to simulate airflow at different directions and angles, and cannot simulate dynamic loads. It is only suitable for small-load testing, and it is difficult to simulate different environments, reducing the accuracy of test results. It also requires multiple tests, increasing the workload. 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 a testing device for aircraft turbulence actuation systems that can solve the problems of difficulty in simulating airflow resistance and difficulty in simulating airflow at different directions and angles.

[0004] To achieve the above objectives, this utility model provides the following technical solution: a testing device for aircraft turbulence actuation systems, comprising:

[0005] The mounting groove has a C-shaped cross-section;

[0006] The testing mechanism is located above the mounting slot. The testing mechanism includes a rotating plate, a hydraulic actuator, and a hydraulic vibrator. A rotating plate is located above the mounting slot. Three sets of openings are opened on the outer side of the rotating plate. A hydraulic actuator is fixedly installed on the outer side of two sets of openings, and a hydraulic vibrator is fixedly installed on the outer side of one set of openings.

[0007] The adjustment mechanism is located above the mounting slot and below the testing mechanism.

[0008] Preferably, the testing mechanism further includes a telescopic rod, a sliding block, a movable plate, and a guide ring. A telescopic rod is installed inside the opening. The free ends of two sets of hydraulic actuators are fixedly connected to the two sets of telescopic rods. The free end of one set of hydraulic vibrators is fixedly connected to one set of telescopic rods. A movable plate is installed above the mounting groove. Two sets of guide rings are fixedly installed on the top of the movable plate. A sliding block is slidably installed on the outside of the guide rings. The sliding block is fixedly installed on the top of the rotating plate.

[0009] Preferably, the adjusting mechanism includes a connecting plate, a rotating rod, a motor, a fixed plate, a support plate, a guide block, pulleys, and a positioning plate. Two sets of connecting plates are fixedly installed on the top of the moving plate. An installation opening is provided on the outer side of the connecting plate, and a rotating rod is rotatably installed in the installation opening. Two sets of rotating rods are fixedly installed on the outer side of the moving plate. A motor is fixedly installed on the outer side of one connecting plate, and a set of rotating rods is fixedly installed at the output end of the motor. Two sets of fixed plates are fixedly installed on the top of the mounting groove. A sliding groove is provided on the outer side of the fixed plate, and a guide block is slidably installed in the sliding groove. A support plate is fixedly installed on the outer side of the guide block. The support plate is fixedly installed on the bottom of the moving plate. Multiple sets of pulleys are fixedly installed on the bottom of the moving plate. An opening is provided on the top of the mounting groove, and a positioning plate is provided in the opening. The positioning plate is fixedly installed on the outer side of the moving plate.

[0010] Preferably, the positioning plate and the mounting groove have multiple sets of threaded holes on their outer sides, and a knob is installed in the threaded hole through the thread.

[0011] Preferably, the top of the sliding block has a threaded opening, and a positioning knob is installed in the threaded opening.

[0012] Preferably, a clamping plate is fixedly installed on the top inner side of the mounting groove, multiple sets of adjusting plates are provided on the bottom inner side of the mounting groove, and multiple sets of threaded openings are opened at the bottom of the mounting groove. Threaded rods are installed in the threaded openings and are rotatably installed on the bottom of the adjusting plates.

[0013] Preferably, rubber buffer pads are fixedly installed on the outer sides of the adjusting plate, clamping plate and telescopic rod.

[0014] Compared with the prior art, the beneficial effects of this utility model are:

[0015] (1) The test device for aircraft spoiler actuation system, through the coordinated use of rotating plate, hydraulic actuator cylinder, hydraulic vibrator, telescopic rod, sliding block, moving plate and guide ring, can control the start of hydraulic actuator cylinder by making the rubber pad on the outside of telescopic rod fit with the surface of spoiler, so that the free end of hydraulic actuator cylinder extends and retracts, driving two sets of telescopic rods to extend and retract to push spoiler, apply reverse force to spoiler, simulate airflow resistance, reduce the configuration block on spoiler, reduce damage to spoiler surface coating, save test costs, control the start of hydraulic vibrator, make the free end of hydraulic vibrator extend and retract, drive a set of telescopic rods to extend and retract to push spoiler vibration, simulate dynamic load, simulate test for different environments, and improve test effect.

[0016] (2) The test device for aircraft turbulence actuation system, through the cooperation of connecting plate, rotating rod, motor, fixed plate, support plate, guide block, pulley and positioning plate, can control the start of the motor to make the output end of the motor rotate to drive the rotating rod to rotate, so that the rotating plate can rotate to adjust the loading direction of the telescopic rod. The sliding block slides on the outside of the guide ring. The positioning knob is installed in the threaded hole to fix the angle of the rotating plate. It simulates airflow with different directions and angles to ensure that the loading direction is consistent with the airflow resistance direction, improves the accuracy of the test results, reduces multiple tests and reduces the workload. Attached Figure Description

[0017] The present invention will be further described below with reference to the accompanying drawings and embodiments:

[0018] Figure 1 This is a side view of the present invention;

[0019] Figure 2 This is the left side view of the present invention;

[0020] Figure 3 This is a cross-sectional view of the present invention.

[0021] Reference numerals: 1. Mounting slot; 2. Testing mechanism; 201. Rotating plate; 202. Hydraulic actuator; 203. Hydraulic vibrator; 204. Telescopic rod; 205. Sliding block; 206. Moving plate; 207. Guide ring; 3. Adjusting mechanism; 301. Connecting plate; 302. Rotating rod; 303. Motor; 304. Fixing plate; 305. Support plate; 306. Guide block; 307. Pulley; 308. Positioning plate; 4. Clamping plate; 5. Adjusting plate; 6. Threaded rod; 7. Knob; 8. Positioning knob. Detailed Implementation

[0022] Please see Figure 1-3 This utility model provides a technical solution: a testing device for an aircraft turbulence actuation system, comprising: a mounting groove 1, the mounting groove 1 having a C-shaped cross-section; a testing mechanism 2, located above the mounting groove 1, the testing mechanism 2 including a rotating plate 201, a hydraulic actuator 202, and a hydraulic vibrator 203, the rotating plate 201 being located above the mounting groove 1, the rotating plate 201 having three sets of openings on its outer side, the hydraulic actuator 202 being fixedly installed on the outer side of two sets of openings, and the hydraulic vibrator 203 being fixedly installed on the outer side of one set of openings; and an adjustment mechanism 3, located above the mounting groove 1 and below the testing mechanism 2, reducing the need for multiple tests and lowering the workload.

[0023] Furthermore, the testing mechanism 2 also includes a telescopic rod 204, a sliding block 205, a moving plate 206, and a guide ring 207. The telescopic rod 204 is installed inside the opening. The free ends of two sets of hydraulic actuators 202 are fixedly connected to the two sets of telescopic rods 204. The free end of one set of hydraulic vibrators 203 is fixedly connected to one set of telescopic rods 204. A moving plate 206 is installed above the mounting groove 1. Two sets of guide rings 207 are fixedly installed on the top of the moving plate 206. A sliding block 205 is slidably installed on the outer side of the guide rings 207. The sliding block 205 is fixedly installed on the top of the rotating plate 201. An opening is formed on the top of the sliding block 205. The device has a threaded opening with a positioning knob 8 installed on the internal thread. By making the rubber pad on the outside of the telescopic rod 204 fit against the surface of the spoiler, the device controls the activation of the hydraulic actuator 202, causing the free end of the hydraulic actuator 202 to extend and retract. This drives the two sets of telescopic rods 204 to extend and retract, pushing the spoiler and applying a reverse force to it. This simulates airflow resistance and reduces the need for mounting blocks on the spoiler. The device also controls the activation of the hydraulic vibrator 203, causing the free end of the hydraulic vibrator 203 to extend and retract. This drives the set of telescopic rods 204 to extend and retract, pushing the spoiler to vibrate and simulating dynamic loads. This allows for simulation testing in different environments and improves the testing results.

[0024] The adjusting mechanism 3 includes a connecting plate 301, a rotating rod 302, a motor 303, a fixed plate 304, a support plate 305, a guide block 306, a pulley 307, and a positioning plate 308. Two sets of connecting plates 301 are fixedly installed on the top of the moving plate 206. An installation opening is provided on the outer side of the connecting plate 301, and a rotating rod 302 is rotatably installed within the installation opening. The two sets of rotating rods 302 are fixedly installed on the outer side of the moving plate 201. A motor 303 is fixedly installed on the outer side of one set of connecting plates 301, and a set of rotating rods 302 is fixedly installed at the output end of the motor 303. Two sets of fixed plates 304 are fixedly installed on the top of the mounting groove 1. A sliding groove is provided on the outer side of the fixed plate 304, and a guide block 306 is slidably installed within the sliding groove. A support plate 305 is fixedly installed on the outer side of the guide block 306. The support plate 307 is fixedly installed on the moving plate 206. At the bottom of the movable plate 206, multiple sets of pulleys 307 are fixedly installed. The top of the mounting groove 1 has an opening, and a positioning plate 308 is installed inside the opening. The positioning plate 308 is fixedly installed on the outside of the movable plate 206. Multiple sets of threaded holes are opened on the outside of the positioning plate 308 and the mounting groove 1. A knob 7 is installed in the threaded hole. By controlling the start of the motor 303, the output end of the motor 303 rotates, driving the rotating rod 302 to rotate, so that the rotating plate 201 rotates to adjust the loading direction of the telescopic rod 204. The sliding block 205 slides on the outside of the guide ring 207. A positioning knob 8 is installed in the threaded hole to fix the angle of the rotating plate 201. The airflow at different angles is simulated to ensure that the loading direction is consistent with the airflow resistance direction, thereby improving the accuracy of the test results.

[0025] Furthermore, a clamping plate 4 is fixedly installed on the top inner side of the mounting groove 1, and multiple sets of adjusting plates 5 are provided on the bottom inner side of the mounting groove 1. Multiple sets of threaded openings are opened at the bottom of the mounting groove 1, and threaded rods 6 are installed in the threaded openings. The threaded rods 6 are rotatably installed on the bottom of the adjusting plates 5. Rubber buffer pads are fixedly installed on the outer sides of the adjusting plates 5, clamping plates 4 and telescopic rods 204 to reduce damage to the surface coating of the spoiler and save testing costs.

[0026] Working principle: By setting the wing inside the mounting slot 1, rotating the threaded rod 6 pushes the adjusting plate 5 upward, causing the rubber pad to fit against the outer side of the wing, thus fixing the device on the wing. Pushing the guide ring 207 causes the pulley 307 to rotate, the guide block 306 slides in the groove, and the guide ring 207 slides in the opening, moving the position of the moving plate 206. This facilitates testing of spoilers at different positions and reduces movement of the device. A knob 7 is threaded into the positioning plate 308 and the threaded hole of the mounting slot 1 to fix the position of the moving plate 206. Starting the motor 303 causes its output to rotate, driving the rotating rod 302 to rotate, thus rotating the rotating plate 201 to adjust the extension. The loading direction of the telescopic rod 204 is controlled by the sliding block 205 sliding on the outside of the guide ring 207 to guide the rotating plate 201. The positioning knob 8 is installed in the threaded hole to fix the angle of the rotating plate 201. The airflow at different directions and angles is simulated. By making the rubber pad on the outside of the telescopic rod 204 fit with the surface of the spoiler, the hydraulic actuator 202 is activated, causing the free end of the hydraulic actuator 202 to extend and retract, driving the two sets of telescopic rods 204 to extend and retract and push the spoiler, applying a reverse force to the spoiler to simulate airflow resistance. The activation of the hydraulic vibrator 203 is controlled, causing the free end of the hydraulic vibrator 203 to extend and retract, driving the set of telescopic rods 204 to extend and retract and push the spoiler to vibrate, simulating dynamic load.

[0027] 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. A testing device for aircraft turbulence actuation systems, characterized in that, include: Mounting groove (1), the cross section of which is C-shaped; The testing mechanism (2) is located above the mounting slot (1). The testing mechanism (2) includes a rotating plate (201), a hydraulic actuator (202), and a hydraulic vibrator (203). The rotating plate (201) is located above the mounting slot (1). Three sets of openings are provided on the outer side of the rotating plate (201). The hydraulic actuator (202) is fixedly installed on the outer side of two sets of openings, and the hydraulic vibrator (203) is fixedly installed on the outer side of one set of openings. The adjustment mechanism (3) is located above the mounting slot (1) and below the testing mechanism (2).

2. The testing device for an aircraft turbulence actuation system according to claim 1, characterized in that: The testing mechanism (2) also includes a telescopic rod (204), a sliding block (205), a moving plate (206), and a guide ring (207). The telescopic rod (204) is installed in the opening. The free ends of two sets of hydraulic actuators (202) are fixedly connected to the two sets of telescopic rods (204). The free ends of a set of hydraulic vibrators (203) are fixedly connected to a set of telescopic rods (204). A moving plate (206) is installed above the mounting groove (1). Two sets of guide rings (207) are fixedly installed on the top of the moving plate (206). A sliding block (205) is slidably installed on the outside of the guide ring (207). The sliding block (205) is fixedly installed on the top of the rotating plate (201).

3. The testing device for an aircraft turbulence actuation system according to claim 2, characterized in that: The adjusting mechanism (3) includes a connecting plate (301), a rotating rod (302), a motor (303), a fixed plate (304), a support plate (305), a guide block (306), a pulley (307), and a positioning plate (308). Two sets of connecting plates (301) are fixedly installed on the top of the moving plate (206). An installation hole is opened on the outer side of the connecting plate (301), and a rotating rod (302) is rotatably installed in the installation hole. The two sets of rotating rods (302) are fixedly installed on the outer side of the rotating plate (201). A motor (303) is fixedly installed on the outer side of one set of connecting plates (301). The motor (303) has... A set of rotating rods (302) is fixedly installed at the output end. Two sets of fixed plates (304) are fixedly installed at the top of the mounting groove (1). A sliding groove is provided on the outside of the fixed plate (304). A guide block (306) is slidably installed in the sliding groove. A support plate (305) is fixedly installed on the outside of the guide block (306). The support plate (305) is fixedly installed at the bottom of the moving plate (206). Multiple sets of pulleys (307) are fixedly installed at the bottom of the moving plate (206). An opening is provided at the top of the mounting groove (1). A positioning plate (308) is provided in the opening. The positioning plate (308) is fixedly installed on the outside of the moving plate (206).

4. The testing device for an aircraft turbulence actuation system according to claim 3, characterized in that: Multiple sets of threaded holes are provided on the outer side of the positioning plate (308) and the mounting groove (1), and a knob (7) is installed in the threaded hole.

5. The testing device for an aircraft turbulence actuation system according to claim 4, characterized in that: The top of the sliding block (205) is provided with a threaded opening, and a positioning knob (8) is installed in the threaded opening.

6. The testing device for an aircraft turbulence actuation system according to claim 5, characterized in that: A clamp (4) is fixedly installed on the top inner side of the mounting groove (1). Multiple sets of adjustment plates (5) are provided on the bottom inner side of the mounting groove (1). Multiple sets of threaded openings are opened at the bottom of the mounting groove (1). Threaded rods (6) are installed in the threaded openings. Threaded rods (6) are rotatably installed on the bottom of the adjustment plates (5).

7. A testing device for an aircraft turbulence actuation system according to claim 6, characterized in that: Rubber buffer pads are fixedly installed on the outer sides of the adjusting plate (5), clamping plate (4) and telescopic rod (204).

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