Simulation test device for aircraft rudder transmission mechanism

Abstract

The utility model discloses a simulation test device for an aircraft rudder transmission mechanism, and belongs to the technical field of simulation test. A simulation test device for an aircraft rudder transmission mechanism comprises an experiment module, an air inlet and an air outlet are formed in the two sides of the experiment module respectively, sealing rings used for sealing are fixed to the air inlet and the air outlet respectively, a mounting base is arranged in the experiment module, a rudder transmission structure is arranged on the mounting base, and the rudder transmission structure is connected with the experiment module. A testing control surface is rotatably arranged on the rudder transmission structure, a rail is detachably mounted at the bottom of the testing control surface, a second sliding block is slidably arranged in the rail, and a power cabin is in threaded connection with the bottom of the experiment cabin. Through the integrated arrangement of the driving device and the experiment module, the sealing performance of the experiment module is enhanced, the accuracy of test data is improved, in addition, through the arrangement of a thread at the bottom of the power module, the disassembly of the power module is more convenient, and the later maintenance and repair are more convenient.

Description

Technical Field

[0001] The utility model relates to the technical field of simulation testing, and more specifically to a simulation testing device for an aircraft rudder transmission mechanism. Background Art

[0002] The rudder transmission structure of an aircraft refers to a series of mechanical devices that convert the instructions from the pilot or the autopilot system into the movement of the control surfaces. These include the rudder, elevator, ailerons and spoilers, etc. They control the attitude and direction of the aircraft, making the rudder transmission structure crucial to the aircraft's maneuverability and flight performance. Therefore, during the development and production of aircraft, the rudder transmission mechanism needs to be rigorously tested.

[0003] A Chinese invention patent with publication number CN106644466A discloses a simulation test device for an aircraft rudder transmission mechanism, including a test cavity, an inlet static pressure cavity, an outlet static pressure cavity, a base, a tested servo, etc., which forms a tower structure through a sealed membrane box, and is non-vacuum-insulated with the test cavity to realize the stretchable operation and bending deformation state of the loading connecting rod.

[0004] However, in the above arrangement, the sealing performance of the opening at the bottom of the experimental chamber needs to be improved, and long-term experimental operation may cause damage to the sealed ink cartridge. In view of this, a simulation test device for an aircraft rudder transmission mechanism is proposed. Utility Model Content

[0005] 1. Technical issues to be solved

[0006] The purpose of the utility model is to provide a simulation test device for an aircraft rudder transmission mechanism to solve the problems raised in the above background technology.

[0007] 2. Technical solution

[0008] A simulation test device for an aircraft rudder transmission mechanism comprises an experimental cabin, wherein an air inlet and an air outlet are respectively provided on both sides of the experimental cabin, and sealing rings for sealing are fixed to the air inlet and the air outlet; a mounting seat is arranged in the experimental cabin, a rudder transmission structure is arranged on the mounting seat, a test rudder surface is rotatably arranged on the rudder transmission structure, a track is detachably installed at the bottom of the test rudder surface, a second sliding block is slidably arranged in the track, a power cabin is threadedly connected to the bottom of the experimental cabin, a motor is arranged in the power cabin, and the motor is used to drive the test rudder surface to rotate for simulation testing.

[0009] Preferably, a first bevel gear is fixedly installed on the output end of the motor, a second bevel gear is meshedly connected to the first bevel gear, a connecting rod is fixedly installed on the second bevel gear, one end of the connecting rod is fixedly connected to the second bevel gear, a first gear is fixedly installed on the other end of the connecting rod, the first gear is meshedly connected to the second gear, the second gear is meshedly connected to the rack, a hinge block is fixedly installed on the top of the rack, and the hinge block is fixedly connected to the second slider, so that the test rudder surface can be driven to rotate when the motor is started.

[0010] Preferably, a first bracket is fixedly installed in the experimental cabin, the connecting rod is rotatably installed on the first bracket, and the second gear is rotatably installed on the first bracket.

[0011] Preferably, a second bracket is fixedly installed in the experimental cabin, a first slider is slidably provided on the second bracket, and the first slider is fixedly installed on one side of the rack.

[0012] Preferably, the first sliding block and the second sliding block are both arranged in a T-shape.

[0013] Preferably, the height of the gas inlet should be higher than that of the gas outlet to facilitate the discharge and exhaust of the simulated test gas.

[0014] Preferably, the top of the power cabin is threaded, which is used for installation or disassembly of the power cabin and the experimental cabin.

[0015] 3. Beneficial effects

[0016] Compared with the prior art, the advantages of the present invention are:

[0017] 1. The integrated setting of the drive device and the experimental chamber enhances the sealing of the experimental chamber and improves the accuracy of the test data;

[0018] 2. The threaded setting at the bottom of the power compartment makes the disassembly of the power compartment easier and more convenient for subsequent maintenance and repair. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a three-dimensional structural schematic diagram of the utility model;

[0020] Figure 2 It is a schematic diagram of the connection relationship of the transmission components of the slider of the utility model;

[0021] Figure 3 It is a cross-sectional view of the water tank of the utility model;

[0022] Figure 4 This is a state diagram of the seamless steel pipe of the utility model about to enter the water tank for cooling.

[0023] Description of the numbers in the figure:

[0024] 1. Experimental cabin, 2. Air inlet, 3. Air outlet, 4. Sealing ring, 5. Mounting seat, 6. Rudder transmission structure, 7. Test rudder surface, 8. Power cabin, 9. Motor, 10. First bevel gear, 11. Second bevel gear, 12. First gear, 13. Second gear, 14. First bracket, 15. Second bracket, 16. Rack, 17. First slider, 18. Second slider, 19. Articulated block, 20. Track, 21. Thread, 22. Connecting rod. DETAILED DESCRIPTION

[0025] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present invention.

[0026] In the description of the present invention, "plurality" means two or more than two, unless otherwise clearly and specifically defined.

[0027] Example:

[0028] This embodiment provides a simulation test device for an aircraft rudder transmission mechanism, referring to Figure 1-Figure 4 , including an experimental cabin 1, with an air inlet 2 and an air outlet 3 respectively opened on both sides of the experimental cabin 1, wherein the height of the air inlet 2 should be higher than the height of the air outlet 3 to facilitate the discharge and exhaust of the simulated test gas.

[0029] Furthermore, sealing rings 4 for sealing are fixed at the air inlet 2 and the air outlet 3. The sealing rings 4 are used to ensure that the air inlet pipe or the air outlet pipe arranged at the air inlet 2 and the air outlet 3 remain in a sealed state, so as to ensure the sealing state of the experimental cabin 1 and the accuracy of the experimental data. In addition, a mounting seat 5 is arranged in the experimental cabin 1, and a rudder transmission structure 6 is arranged on the mounting seat 5. The rudder transmission structure 6 and the mounting seat 5 should be detachably fixed and installed. A test rudder surface 7 is rotatably arranged on the rudder transmission structure 6, and a track 20 is detachably installed at the bottom of the test rudder surface 7. A second slider 18 is slidably arranged in the track 20. The bottom thread 21 of the experimental cabin 1 is connected to the power cabin 8, and correspondingly, a screw groove matching the thread 21 of the power cabin 8 is opened on the experimental cabin 1.

[0030] In a further embodiment, the motor 9 is fixedly installed in the power compartment 8, and a first bevel gear 10 is fixedly installed on the output end of the motor 9, and a second bevel gear 11 is meshedly connected to the first bevel gear 10, and the second bevel gear 11 and the first bevel gear 10 are staggered. A connecting rod 22 is fixedly installed on the side of the second bevel gear 11 where no teeth are provided, and one end of the connecting rod 22 is fixedly connected to the second bevel gear 11, and a first gear 12 is fixedly installed on the other end of the connecting rod 22, and a second gear 13 is meshedly connected to the first gear 12, and a rack 16 is meshedly connected to the second gear 13, and a hinge block 19 is fixedly installed on the top of the rack 16, and the hinge block 19 is fixedly connected to the second slider 18, so that when the motor 9 is started, it can drive the test rudder 7 to rotate, wherein the second slider 18 is arranged in a T shape.

[0031] In a further embodiment, a first bracket 14 and a second bracket 15 are fixedly installed in the experimental cabin 1, wherein the first bracket 14 is used to rotatably install the connecting rod 22 and the second gear 13, and a first slider 17 is slidably arranged on the second bracket 15, and the first slider 17 is fixedly installed on one side of the rack 16. The first slider 17 is arranged in a T-shape. The first slider 17 is used to limit the movement of the rack 16 in the horizontal direction to ensure the stability of the test control surface 7.

[0032] The working principle of the utility model is as follows: first, the air outlet 3 is closed, and the rudder transmission structure 6 to be tested is fixedly installed on the mounting seat 5 in the experimental cabin 1, and then the track 20 is installed at the bottom of the rudder surface rotatably installed on one side of the rudder transmission body, and the power cabin 8 is connected with the experimental cabin 1 by the thread 21, so that the first bevel gear 10 is meshed and connected with the second bevel gear 11, and then the gas required for the test is introduced at the air inlet 2, and the motor 9 is turned on to make the first bevel gear 10 drive the second bevel gear 11 to rotate, and then the first gear 12 drives the second gear 13 to rotate, and drives the rack 16 to move, so that the rack 16 drives the hinge block 19 to slide along the track 20 to drive the rudder surface to rotate along the rudder transmission structure 6, so as to conduct an experiment on the rudder transmission structure 6 in the experimental cabin 1, and a gas detection device should be set in the experimental cabin 1 to check whether the gas used in the previous experiment is completely discharged before introducing new experimental gas.

[0033] It should be noted that a door for opening the experimental cabin 1 should be provided on the top or side of the experimental cabin 1. After installing the power cabin 8, the position of the motor 9 should be adjusted at the door so that the first bevel gear 10 engages with the second bevel gear 11. When setting the door, a sealing device should be provided at the door to ensure that the entire experimental cabin 1 is in a closed state after the door is closed.

[0034] The above shows and describes the basic principle, main features and advantages of the utility model. Those skilled in the art should understand that the utility model is not limited by the above embodiments. The above embodiments and descriptions are only preferred examples of the utility model and are not used to limit the utility model. Without departing from the spirit and scope of the utility model, the utility model may have various changes and improvements, which fall within the scope of the utility model to be protected. The scope of protection of the utility model is defined by the attached claims and their equivalents.

Claims

1. A simulation test device for an aircraft rudder transmission mechanism, comprising a test chamber (1), characterized in that: An air inlet (2) and an air outlet (3) are respectively provided on both sides of the experimental cabin (1), and sealing rings (4) for sealing are fixed to the air inlet (2) and the air outlet (3). A mounting seat (5) is provided in the experimental cabin (1), and a rudder transmission structure (6) is provided on the mounting seat (5). A test rudder surface (7) is rotatably provided on the rudder transmission structure (6). A track (20) is detachably installed at the bottom of the test rudder surface (7), and a second slider (18) is slidably provided in the track (20). A power cabin (8) is connected to the bottom of the experimental cabin (1) via a thread (21), and a motor (9) is provided in the power cabin (8). The motor (9) is used to drive the test rudder surface (7) to rotate so as to perform a simulation test.

2. A simulation test device for an aircraft rudder transmission mechanism according to claim 1, characterized in that: A first bevel gear (10) is fixedly mounted on the output end of the motor (9), a second bevel gear (11) is meshedly connected to the first bevel gear (10), a connecting rod (22) is fixedly mounted on the second bevel gear (11), one end of the connecting rod (22) is fixedly connected to the second bevel gear (11), a first gear (12) is fixedly mounted on the other end of the connecting rod (22), a second gear (13) is meshedly connected to the first gear (12), a rack (16) is meshedly connected to the second gear (13), a hinge block (19) is fixedly mounted on the top of the rack (16), and the hinge block (19) is fixedly connected to the second slider (18), so that the motor (9) can drive the test rudder surface (7) to rotate when it is started.

3. A simulation test device for an aircraft rudder transmission mechanism according to claim 2, characterized in that: A first bracket (14) is fixedly mounted in the experimental chamber (1), the connecting rod (22) is rotatably mounted on the first bracket (14), and the second gear (13) is rotatably mounted on the first bracket (14).

4. A simulation test device for an aircraft rudder transmission mechanism according to claim 1, characterized in that: A second bracket (15) is fixedly installed in the experimental chamber (1), a first slider (17) is slidably arranged on the second bracket (15), and the first slider (17) is fixedly installed on one side of the rack (16).

5. A simulation test device for an aircraft rudder transmission mechanism according to claim 4, characterized in that: The first sliding block (17) and the second sliding block (18) are both arranged in a T-shape.

6. The simulation test device for an aircraft rudder transmission mechanism according to claim 1, characterized in that: The height of the gas inlet (2) should be higher than the height of the gas outlet (3) to facilitate the discharge and exhaust of the simulated test gas.

7. The simulation test device for an aircraft rudder transmission mechanism according to claim 1, characterized in that: The top of the power cabin (8) is provided with a thread (21), which is used for installing or disassembling the power cabin (8) and the experimental cabin (1).

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