Aircraft damping device

Abstract

The utility model provides an aircraft damping device. The aircraft damping device comprises a supporting piece, a mounting assembly and an auxiliary assembly, lug plates are fixedly connected to the four corners of the supporting piece, the mounting assembly comprises a fixing piece, the fixing piece is located on the upper sides of the lug plates, a rotating piece is hinged to the surface of the fixing piece, clamping blocks are fixedly connected to the end of the rotating piece in an up-down symmetry mode, and the clamping blocks are fixedly connected to the fixing piece. Clamping grooves are vertically and symmetrically formed in the surface of the fixing piece, the clamping grooves are matched with the clamping blocks, supports are fixedly connected to the top and the bottom of the fixing piece, rod bodies are slidably connected to the interiors of the supports, plug pins are fixedly connected to the bottoms of the rod bodies, and the bottoms of the plug pins extend into the clamping grooves in the adjacent sides. The aircraft damping device provided by the utility model has the advantages that a user can be assisted in accurately fixing the flight control board, and meanwhile, the damping columns can be conveniently replaced and mounted.

Description

Technical Field

[0001] The utility model relates to the field of aircraft vibration reduction, in particular to an aircraft vibration reduction device. Background Art

[0002] Unmanned aerial vehicle, referred to as "UAV", is an unmanned aircraft controlled by radio remote control equipment and self-contained program control devices, or operated completely or intermittently autonomously by an onboard computer. An important component of a UAV is the flight control board. The installation quality of the flight control board can often affect the flight status of the UAV.

[0003] Traditional aircraft vibration reduction devices still have certain shortcomings during use: when fixing the flight control board on the drone, the vibration reduction column is generally inserted into the holes at the four corners of the flight control board, and then the vibration reduction column is inserted into the screw of the drone base, and the nut is screwed into the screw above the vibration reduction column to fix its position, but there are still some defects in this link. First, the vibration reduction column is not convenient to install into the hole of the flight control board. The user often needs to spend a lot of effort to squeeze the vibration reduction column into it, which is more troublesome. Second, the top of the vibration reduction column will be compressed when the nut on the screw is tightened. However, if the nuts at the four corners of the flight control board are not tightened to the same degree, causing the flight control board to be skewed, it may cause problems such as inaccurate flight attitude control of the drone.

[0004] Therefore, it is necessary to provide a new aircraft vibration reduction device to solve the above technical problems. Utility Model Content

[0005] The technical problem solved by the utility model is to provide an aircraft vibration reduction device which can assist a user in accurately fixing a flight control board and conveniently replace and install a vibration reduction column.

[0006] In order to solve the above technical problems, the utility model provides an aircraft vibration reduction device comprising: a support member, a mounting assembly and an auxiliary assembly, wherein the four corners of the support member are fixedly connected with ear plates, the mounting assembly comprises a fixing member, the fixing member is located on the upper side of the ear plate, a rotating member is hinged on the surface of the fixing member, a clamping block is fixedly connected to the end of the rotating member symmetrically up and down, a clamping groove is symmetrically opened on the surface of the fixing member, the clamping groove and the clamping block match each other, the top and bottom of the fixing member are fixedly connected with a bracket, a rod body is slidably connected inside the bracket, a latch is fixedly connected to the bottom of the rod body, and the bottom of the latch extends to the inside of the clamping groove on an adjacent side;

[0007] The front and rear side walls of the support are both symmetrically fixedly connected with convex plates, the auxiliary component includes a positioning rod, a groove is opened on the surface of the positioning rod, a scale bar is fixedly connected inside the groove, and a movable part is arranged on the outside of the positioning rod.

[0008] As a further solution of the utility model, a reset spring is arranged on the outside of the rod body between the bracket and the latch, and a positioning hole is opened on the surface of the block, and the positioning hole matches the latch.

[0009] Through the above technical solution, in the traditional structure, the vibration damping column needs to be inserted into the hole of the flight control board, and the operation is very troublesome. The user often needs to spend a lot of effort to squeeze the vibration damping column therein. In the device, the hole of the flight control board is fixedly connected to the connecting piece by installing bolts and installing nuts, and the vibration damping column does not need to be directly inserted into the hole of the flight control board. The user only needs to put the vibration damping column into the inside of the fixing piece and rotate the rotating piece to allow the card block to extend into the inside of the card slot and connect the pin with the positioning hole. This operation is more convenient for the user to install or replace the vibration damping structure of the flight control board, and the design is more user-friendly.

[0010] As a further solution of the utility model, a threaded rod is provided on the inner side of the four ear plates, the bottom of the threaded rod is fixedly connected to a limiting member, the limiting member is located on the lower side of the ear plate, the surface of the threaded rod is threadedly connected with a fastening nut, and the fastening nut abuts against the top surface of the ear plate.

[0011] Through the above technical solution, the threaded rod can be fixed to the ear plate by the cooperation of the fastening nut and the limit piece, and the flight control board and other accessories of the UAV can be installed on the threaded rod.

[0012] As a further solution of the utility model, a vibration-damping column is arranged on the outer side of the threaded rod, an annular groove is opened on the surface of the vibration-damping column, and the fixed part and the rotating part are both located on the outer side of the annular groove.

[0013] Through the above technical solution, the vibration-damping column is sleeved on the outer side of the threaded rod, and the vibration-damping column can reduce the vibration of the drone itself from being transmitted to the flight control board.

[0014] As a further solution of the utility model, a locking nut is threadedly connected to the surface of the threaded rod located on the upper side of the damping column, and a semicircular groove is opened on the surface of the movable part, and the diameter of the semicircular groove is larger than the diameter of the threaded rod.

[0015] Through the above technical solution, the user first fixes the flight control board and the connecting piece together, and uses the fixing piece and the rotating piece to fix the vibration damping column on the inner side thereof, and then inserts the four vibration damping columns into the threaded rods at the four corners, and screws in the locking bolts to limit the position of the vibration damping columns. During this operation, in order to prevent the flight control board from tilting due to inconsistent heights of the locking nuts at the four corners, the device is specially equipped with an auxiliary component. The user can rotate the movable part so that it is located on the side of the threaded rod above the locking nut. In this way, when the user tightens the locking nut, the movable part will change in height with it. At this time, it is only necessary to observe the scale values ​​corresponding to the movable parts at each position to ensure that the flight control board will not tilt to a large extent. The structural design facilitates the user to achieve correct installation.

[0016] As a further solution of the utility model, the four fixing members are fixedly connected to the outer surface of the rotating member with connecting members, mounting bolts are inserted into the connecting members, and mounting nuts are threadedly connected to the surfaces of the mounting bolts.

[0017] Through the above technical solution, in the device, the user can connect it to the hole at a corner of the flight control board through the connecting piece, the mounting bolt and the mounting nut.

[0018] As a further solution of the utility model, the front and rear side walls and the left and right side walls of the support member are fixedly connected with supporting feet, fixing bolts are inserted inside the supporting feet, and fixing nuts are threadedly connected to the surfaces of the fixing bolts.

[0019] Through the above technical solution, the support member can be fixed to the frame of the drone through the support feet, fixing bolts and fixing nuts.

[0020] Compared with the related art, the aircraft vibration reduction device provided by the utility model has the following beneficial effects:

[0021] 1. In the utility model, in the traditional structure, the vibration-damping column needs to be inserted into the hole of the flight control board, and the operation is very troublesome. The user often needs to spend a lot of effort to squeeze the vibration-damping column into it. In the device, the hole of the flight control board is fixedly connected to the connecting piece by the mounting bolt and the mounting nut, and the vibration-damping column does not need to be directly inserted into the hole of the flight control board. The user only needs to put the vibration-damping column into the inner side of the fixing piece, and rotate the rotating piece to allow the card block to extend into the inner side of the card slot and connect the pin with the positioning hole. This operation is more convenient for the user to install or replace the vibration-damping structure of the flight control board, and the design is more humane;

[0022] 2. In the utility model, the user first fixes the flight control board and the connecting piece together, and uses the fixing piece and the rotating piece to fix the vibration-damping column on the inner side thereof, and then inserts the four vibration-damping columns into the threaded rods at the four corners, and screws in the locking bolts to limit the positions of the vibration-damping columns. During this operation, in order to prevent the flight control board from being skewed due to inconsistent heights of the locking nuts at the four corners, the device is specially provided with an auxiliary component. The user can rotate the movable part so that it is located on one side of the threaded rod above the locking nut. In this way, when the user tightens the locking nut, the movable part will change in height with it. At this time, it is only necessary to observe the scale values ​​corresponding to the movable parts at each position to ensure that the flight control board will not tilt to a large extent. The structural design facilitates the user to achieve correct installation. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to facilitate understanding by those skilled in the art, the present invention is further described below in conjunction with the accompanying drawings.

[0024] Figure 1 It is a schematic diagram of the overall structure of an aircraft vibration reduction device in the utility model;

[0025] Figure 2 The schematic diagram of the local structure of an aircraft vibration reduction device in the utility model is as follows Figure 1 ;

[0026] Figure 3 The schematic diagram of the local structure of an aircraft vibration reduction device in the utility model is as follows Figure 2 ;

[0027] Figure 4 The figure is a schematic diagram of the structure at position A of an aircraft vibration reduction device in the utility model.

[0028] Description of main symbols:

[0029] 1. Support member; 2. Support foot; 3. Fixing nut; 4. Fixing bolt; 5. Mounting assembly; 6. Auxiliary assembly; 7. Threaded rod; 8. Locking nut; 9. Positioning rod; 10. Scale bar; 11. Limiting member; 12. Fastening nut; 13. Semicircular groove; 14. Ear plate; 15. Connecting member; 16. Vibration damping column; 17. Annular groove; 18. Block; 19. Rotating member; 20. Fixed member; 21. Slot; 22. Latch; 23. Bracket; 24. Rod body; 25. Reset spring; 26. Movable member. DETAILED DESCRIPTION

[0030] Please combine Figures 1 to 4 ,in, Figure 1 It is a schematic diagram of the overall structure of an aircraft vibration reduction device in the utility model; Figure 2 The schematic diagram of the local structure of an aircraft vibration reduction device in the utility model is as follows Figure 1 ; Figure 3The schematic diagram of the local structure of an aircraft vibration reduction device in the utility model is as follows Figure 2 ; Figure 4 The figure is a schematic diagram of the structure of the aircraft vibration reduction device in the utility model. The aircraft vibration reduction device includes:

[0031] Support member 1, mounting assembly 5 and auxiliary assembly 6, the four corners of the support member 1 are fixedly connected with ear plates 14, the mounting assembly 5 includes a fixing member 20, the fixing member 20 is located on the upper side of the ear plate 14, a rotating member 19 is hinged on the surface of the fixing member 20, the end of the rotating member 19 is symmetrically fixedly connected with a card block 18, the surface of the fixing member 20 is symmetrically opened with a card slot 21, the card slot 21 matches the card block 18, the top and bottom of the fixing member 20 are fixedly connected with a bracket 23, the inside of the bracket 23 is slidably connected with a rod body 24, the bottom of the rod body 24 is fixedly connected with a latch 22, and the bottom of the latch 22 extends to the inside of the card slot 21 on the adjacent side;

[0032] The front and rear side walls of the support member 1 are both symmetrically fixed with convex plates. The auxiliary component 6 includes a positioning rod 9 with a groove on its surface. A scale bar 10 is fixedly connected to the inside of the groove. A movable part 26 is arranged on the outside of the positioning rod 9.

[0033] like Figure 1-4 As shown, a return spring 25 is arranged outside the rod body 24 between the bracket 23 and the latch 22 , and a positioning hole is opened on the surface of the block 18 , and the positioning hole matches the latch 22 .

[0034] In the traditional structure, the vibration damping column 16 needs to be inserted into the hole of the flight control board, and the operation is very troublesome. The user often needs to spend a lot of effort to squeeze the vibration damping column 16 therein. In the device, the hole of the flight control board is fixedly connected to the connecting member 15 by installing bolts and installing nuts, and the vibration damping column 16 does not need to be directly inserted into the hole of the flight control board. The user only needs to put the vibration damping column 16 into the inner side of the fixing member 20, and rotate the rotating member 19 to allow the block 18 to extend into the inner side of the slot 21 and connect the pin 22 with the positioning hole. This operation is more convenient for the user to install or replace the vibration damping structure of the flight control board, and the design is more user-friendly.

[0035] like Figure 1-4 As shown, a threaded rod 7 is provided on the inner side of each of the four ear plates 14 , and a limit member 11 is fixedly connected to the bottom of the threaded rod 7 . The limit member 11 is located on the lower side of the ear plate 14 , and a fastening nut 12 is threadedly connected to the surface of the threaded rod 7 , and the fastening nut 12 abuts against the top surface of the ear plate 14 .

[0036] The threaded rod 7 can be fixed to the ear plate 14 by the cooperation of the fastening nut 12 and the limiting member 11 , and the flight control board and other accessories of the UAV can be installed on the threaded rod 7 .

[0037] like Figure 1-4 As shown, a vibration-damping column 16 is disposed on the outer side of the threaded rod 7 , an annular groove 17 is formed on the surface of the vibration-damping column 16 , and the fixing member 20 and the rotating member 19 are both located on the outer side of the annular groove 17 .

[0038] The vibration-damping column 16 is sleeved on the outer side of the threaded rod 7 , and the vibration-damping column 16 can reduce the vibration of the drone itself from being transmitted to the flight control board.

[0039] like Figure 1-4 As shown, a locking nut 8 is threadedly connected to the surface of the threaded rod 7 located on the upper side of the vibration-damping column 16 , and a semicircular groove 13 is opened on the surface of the movable part 26 , and the diameter of the semicircular groove 13 is larger than the diameter of the threaded rod 7 .

[0040] The user first fixes the flight control board and the connecting piece 15 together, and uses the fixing piece 20 and the rotating piece 19 to fix the vibration-damping column 16 on its inner side, and then inserts the four vibration-damping columns 16 into the threaded rods 7 at the four corners, and screws in the locking bolts to limit the position of the vibration-damping columns 16. During this operation, in order to prevent the flight control board from being skewed due to inconsistent heights of the locking nuts 8 at the four corners, the device is specially provided with an auxiliary component 6. The user can rotate the movable part 26 so that it is located on the side of the threaded rod 7 above the locking nut 8. In this way, when the user tightens the locking nut 8, the movable part 26 will change in height with it. At this time, it is only necessary to observe the scale values ​​corresponding to the movable part 26 at each position to ensure that the flight control board will not tilt to a large extent. The structural design facilitates the user to achieve correct installation.

[0041] like Figure 1-4 As shown, the four fixing members 20 are fixedly connected to the outer surfaces of the rotating member 19 with the connecting members 15, the connecting members 15 are internally inserted with mounting bolts, and the surfaces of the mounting bolts are threadedly connected with mounting nuts.

[0042] In the device, the user can connect it to a hole at a corner of the flight control board through the connecting piece 15, the mounting bolts and the mounting nuts.

[0043] like Figure 1-4 As shown, the front and rear side walls and the left and right side walls of the support member 1 are fixedly connected with support legs 2, the inside of the support legs 2 is inserted with fixing bolts 4, and the surface of the fixing bolts 4 is threadedly connected with fixing nuts 3.

[0044] The support member 1 can be fixed to the frame of the drone through the support legs 2, the fixing bolts 4 and the fixing nuts 3.

[0045] The working principle of an aircraft vibration reduction device provided by the utility model is as follows:

[0046] Step 1: In the traditional structure, the vibration-damping column 16 needs to be inserted into the hole of the flight control board, and the operation is very troublesome. The user often needs to spend a lot of effort to squeeze the vibration-damping column 16 into it. In the device, the hole of the flight control board is fixedly connected to the connecting member 15 by the mounting bolt and the mounting nut, and the vibration-damping column 16 does not need to be directly inserted into the hole of the flight control board. The user only needs to put the vibration-damping column 16 into the inner side of the fixing member 20, and rotate the rotating member 19, so that the card block 18 extends into the inner side of the card slot 21 and the pin 22 is plugged into the positioning hole. This operation is more convenient for the user to install or replace the vibration-damping structure of the flight control board, and the design is more humane;

[0047] The second step: the user first fixes the flight control board and the connecting piece 15 together, and uses the fixing piece 20 and the rotating piece 19 to fix the vibration-damping column 16 on its inner side, and then inserts the four vibration-damping columns 16 into the threaded rods 7 at the four corners, and screws in the locking bolts to limit the position of the vibration-damping columns 16. During this operation, in order to prevent the flight control board from being skewed due to inconsistent heights of the locking nuts 8 at the four corners, the device is specially equipped with an auxiliary component 6. The user can rotate the movable part 26 so that it is located on the side of the threaded rod 7 above the locking nut 8. In this way, when the user tightens the locking nut 8, the movable part 26 will change in height with it. At this time, you only need to observe the scale values ​​corresponding to the movable part 26 at each position to ensure that the flight control board will not tilt to a large extent. The structural design facilitates the user to achieve correct installation.

[0048] It should be noted that the equipment structure and drawings of the utility model mainly describe the principle of the utility model. In terms of the technology of the design principle, the settings of the power mechanism, power supply system and control system of the device are not fully described. On the premise that the technical personnel in this field understand the principle of the above utility model, the details of the power mechanism, power supply system and control system can be clearly known. The control method of the application document is automatic control through a controller, and the control circuit of the controller can be realized by simple programming by the technical personnel in this field;

[0049] The standard parts used therein can all be purchased from the market and can be customized according to the instructions and drawings. The specific connection methods of each part adopt conventional means such as mature bolts, rivets, welding, etc. in the prior art. The machinery, parts and equipment all adopt conventional models in the prior art, and the structures and principles of the components known to technical personnel in this field can be known by these technical personnel through technical manuals or through conventional experimental methods.

[0050] Although the embodiments of the present invention have been shown and described, it is understood by those skilled in the art that various changes, modifications, substitutions and variations or direct or indirect applications may be made to these embodiments without departing from the principles and spirit of the present invention. In other related technical fields, the scope of the present invention is defined by the attached claims and their equivalents, which are equally included in the scope of patent protection of the present invention.

Claims

1. An aircraft vibration reduction device, characterized in that: The invention comprises a support member (1), a mounting assembly (5) and an auxiliary assembly (6), wherein the four corners of the support member (1) are fixedly connected with ear plates (14), the mounting assembly (5) comprises a fixing member (20), the fixing member (20) is located on the upper side of the ear plate (14), a rotating member (19) is hingedly connected to the surface of the fixing member (20), the end of the rotating member (19) is symmetrically fixedly connected with a clamping block (18) in the upper and lower directions, a clamping groove (21) is symmetrically opened on the surface of the fixing member (20), the clamping groove (21) matches the clamping block (18), the top and bottom of the fixing member (20) are fixedly connected with a bracket (23), the bracket (23) is slidably connected with a rod body (24), the bottom of the rod body (24) is fixedly connected with a latch (22), and the bottom of the latch (22) extends to the inside of the clamping groove (21) on the adjacent side; The front and rear side walls of the support member (1) are both symmetrically fixedly connected with convex plates, the auxiliary component (6) comprises a positioning rod (9), a groove is provided on the surface of the positioning rod (9), a scale bar (10) is fixedly connected inside the groove, and a movable part (26) is arranged on the outside of the positioning rod (9).

2. The aircraft vibration reduction device according to claim 1, characterized in that: A return spring (25) is arranged on the outside of the rod body (24) between the bracket (23) and the latch (22), and a positioning hole is opened on the surface of the clamping block (18), and the positioning hole matches the latch (22).

3. The aircraft vibration reduction device according to claim 1, characterized in that: A threaded rod (7) is provided on the inner side of each of the four ear plates (14); a limit piece (11) is fixedly connected to the bottom of the threaded rod (7); the limit piece (11) is located on the lower side of the ear plate (14); a fastening nut (12) is threadedly connected to the surface of the threaded rod (7); and the fastening nut (12) abuts against the top surface of the ear plate (14).

4. The aircraft vibration reduction device according to claim 3, characterized in that: A vibration-damping column (16) is arranged on the outside of the threaded rod (7), an annular groove (17) is provided on the surface of the vibration-damping column (16), and the fixing member (20) and the rotating member (19) are both located on the outside of the annular groove (17).

5. The aircraft vibration reduction device according to claim 4, characterized in that: A locking nut (8) is threadedly connected to the surface of the threaded rod (7) located on the upper side of the vibration-damping column (16), and a semicircular groove (13) is provided on the surface of the movable part (26). The diameter of the semicircular groove (13) is larger than the diameter of the threaded rod (7).

6. The aircraft vibration reduction device according to claim 1, characterized in that: The four fixing members (20) are fixedly connected to connecting members (15) relative to the outer surface of the rotating member (19), and mounting bolts are inserted into the connecting members (15), and mounting nuts are threadedly connected to the surfaces of the mounting bolts.

7. The aircraft vibration reduction device according to claim 1, characterized in that: The front and rear side walls and the left and right side walls of the support member (1) are fixedly connected with support feet (2), the support feet (2) are internally inserted with fixing bolts (4), and the surfaces of the fixing bolts (4) are threadedly connected with fixing nuts (3).

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