Damping assembly for fuselage structure of take-off and landing aircraft
Through the coordinated design of a multi-stage shock absorption system and spring-loaded engagement components, the problem of resonance in takeoff and landing aircraft under high-frequency and high-intensity impacts has been solved, achieving effective shock absorption protection and convenient maintenance.
Patent Information
- Application Number
- CN202521109609.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2025-06-03
- Publication Date
- 2026-02-27
- Estimated Expiration
- 2035-06-03
AI Technical Summary
Existing shock absorption components for takeoff and landing aircraft fuselage structures are prone to resonance under high-frequency, high-intensity impacts, leading to shock absorption failure and ineffective protection of the fuselage structure.
It adopts a multi-stage shock absorption system, including a linkage structure of rotating rod, driven rod, sliding block and limiting block, combined with spring and locking components. Through multi-stage buffering and sealing design, it absorbs impact force and provides quick and easy disassembly.
It achieves efficient absorption and dispersion of impact force, protects the core components of the drone, and improves the convenience of maintenance and replacement as well as the shock absorption effect.
Smart Images
Figure CN223949402U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to the field of aircraft, especially landing aircraft fuselage structure damping assembly. BACKGROUND
[0002] The landing aircraft fuselage structure damping assembly is very important, usually consists of shock absorber, buffer material etc., the shock absorber adopts spring, can effectively absorb impact force in the moment of aircraft taking off and landing, reduces the damage to the fuselage, and the buffer material is generally located at the connecting part of the fuselage and landing gear etc., such as rubber, foam etc., can further buffer the vibration, reduces the noise.
[0003] The existing landing aircraft fuselage structure damping assembly is mainly spring shock absorber, utilizes the elastic deformation of spring to absorb vibration energy, simple structure, relatively low cost, but the damping effect is relatively limited, some aircrafts still adopt damping pad, is made of rubber, silica gel etc., is installed at the connecting part of the fuselage and landing gear etc., can effectively isolate vibration, reduces the noise and abrasion.
[0004] The existing landing aircraft fuselage structure damping assembly is generally spring damping assembly, and the spring damping assembly relies on elastic deformation to absorb impact energy, when high-frequency, high-strength impact force is generated in the moment of aircraft taking off and landing, the inherent frequency of spring itself is easy to approach the impact frequency, causes resonance, leads to damping failure, and the landing aircraft fuselage structure damping assembly is provided to solve the above problems. UTILITY MODEL CONTENTS
[0005] In order to make up for the above shortcomings, the utility model provides a landing aircraft fuselage structure damping assembly, aiming at improving the problem of limited damping in the prior art.
[0006] In order to achieve the above purpose, the utility model adopts the following technical scheme:
[0007] The landing aircraft fuselage structure damping assembly, including the base, the top of the base is rotatably connected with the rotating rod, the other end of the rotating rod is rotatably connected with the moving rod, the outer wall of the moving rod is rotatably connected with the driven rod, the other end of the driven rod is rotatably connected with the supporting plate, the other end of the moving rod is fixedly connected with the sliding block, the outer wall of the sliding block is slidably connected with the limiting block, and the top of the supporting plate is provided with the clamping assembly.
[0008] As a further description of the above technical scheme:
[0009] The clamping assembly includes the fixed plate, the bottom of the fixed plate is rotatably connected with the buckle body, the outer wall of the buckle body is rotatably connected with the pull rod, the outer portion of the pull rod is provided with the follow-up rod, the outer portion of the pull rod is provided with the spring, the bottom of the follow-up rod is fixedly connected with the fixed rod, and the outer wall of the supporting plate is fixedly connected with the mounting plate.
[0010] As a further description of the above technical solutions:
[0011] The outer wall of the fixed plate is fixedly connected with a power box, and the top of the power box is fixedly connected with an aircraft body;
[0012] As a further description of the above technical solutions:
[0013] The top of the aircraft body is fixedly connected with a plurality of fixed blocks, and the inner wall of the fixed block is rotatably connected with a propeller;
[0014] As a further description of the above technical solutions:
[0015] The top of the base is fixedly connected with a moving block one, and the bottom of the supporting plate is fixedly connected with a moving block two;
[0016] As a further description of the above technical solutions:
[0017] The outer wall of the fixed rod is movably connected to the inner wall of the mounting plate, and the inner wall of the spring is sleeved on the outer wall of the follow-up rod;
[0018] As a further description of the above technical solutions:
[0019] The top of the moving block one is slidably connected in the inner part of the limiting block, and the bottom of the moving block two is slidably connected in the inner part of the limiting block;
[0020] As a further description of the above technical solutions:
[0021] The top of the supporting plate is in contact with the bottom of the power box, and the inner part of the limiting block is a sealed structure.
[0022] The utility model has the advantages of the following:
[0023] 1、The utility model discloses an unmanned aerial vehicle shock-absorbing device, which comprises a base, a supporting plate, a power box, an aircraft body, a fixed block, a propeller, a moving block one, a moving block two, a fixed rod, a spring, a follow-up rod, a mounting plate, a limiting block, a driving rod, a sliding block, a driving rod and a limiting block.
[0024] 2、The utility model discloses an unmanned aerial vehicle shock-absorbing device, which comprises a base, a supporting plate, a power box, an aircraft body, a fixed block, a propeller, a moving block one, a moving block two, a fixed rod, a spring, a follow-up rod, a mounting plate, a limiting block, a driving rod, a sliding block, a driving rod and a limiting block. BRIEF DESCRIPTION OF DRAWINGS
[0025] Figure 1 A three-dimensional schematic view of a shock absorption assembly of a body structure of a take-off and landing aircraft according to the present application is shown in the figure;
[0026] Figure 2 A structural schematic view of a support plate of a shock absorption assembly of a body structure of a take-off and landing aircraft according to the present application is shown in the figure;
[0027] Figure 3 A structural schematic view of a limiting block of a shock absorption assembly of a body structure of a take-off and landing aircraft according to the present application is shown in the figure;
[0028] Figure 4 A Figure 2 An enlarged view of A in the figure.
[0029] Legend:
[0030] 1, base; 2, rotating rod; 3, driven rod; 4, limiting block; 5, sliding block; 6, moving rod; 7, support plate; 8, aircraft body; 9, propeller; 10, power box; 11, fixed plate; 12, buckle body; 13, pull rod; 14, spring; 15, follow-up rod; 16, fixed rod; 17, mounting plate; 18, moving block one; 19, moving block two; 20, fixed block. DETAILED DESCRIPTION
[0031] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.
[0032] Reference Figure 1 and Figure 3The utility model provides an embodiment: the shock absorption subassembly of the fuselage structure of a kind of take-off and landing aircraft, including base 1, the top of base 1 is rotatably connected with rotating rod 2, base 1 moves and drives rotating rod 2 to rotate, the other end of rotating rod 2 is rotatably connected with moving rod 6, rotating rod 2 rotates and drives moving rod 6 to move, the outer wall of moving rod 6 is rotatably connected with driven rod 3, moving rod 6 moves and drives driven rod 3 to rotate, the other end of driven rod 3 is rotatably connected with support plate 7, the other end of moving rod 6 is fixedly connected with sliding block 5, the outer wall of sliding block 5 is slidably connected with limiting block 4, the outer wall of sliding block 5 is closely attached in the sliding slot of the inner wall of limiting block 4, form stable sliding guide, the top of base 1 is fixedly connected with moving block one 18, the top of moving block one 18 is slidably connected in the inside of limiting block 4, the bottom of support plate 7 is fixedly connected with moving block two 19, the bottom of moving block two 19 is slidably connected in the inside of limiting block 4, the inside of limiting block 4 is sealed structure, limiting block 4 inside adopts stepped sealing structure, and dynamic sealing environment is formed with moving block one 18, moving block two 19 by multiple rubber sealing rings, when the impact force is generated when aircraft takes off and lands, support plate 7 drives moving block two 19 to move downwards, extrudes the sealed space in limiting block 4, realizes efficient shock absorption, and moving block one 18 on base 1 plays reverse support effect, and with moving block two 19 forms the damping buffer mechanism of up-down linkage;
[0033] Referring to Figure 2 And Figure 4 The top of support plate 7 is provided with a clamping assembly, the clamping assembly comprises a fixed plate 11, the bottom of the fixed plate 11 is rotatably connected with a buckle body 12, the outer wall of the buckle body 12 is rotatably connected with a pull rod 13, the buckle body 12 drives the pull rod 13 to rotate, the outer portion of the pull rod 13 is provided with a follower rod 15, the outer portion of the pull rod 13 is sleeved with a spring 14, the inner wall of the spring 14 is sleeved with the outer wall of the follower rod 15, one end of the spring 14 abuts against the bottom of the pull rod 13, and the other end is in close contact with the top of the follower rod 15, the spring 14 is twisted and deformed under the action of the pull rod 13, the elastic potential energy of the spring 14 is converted into axial thrust, the follower rod 15 is pushed to move axially along the pull rod 13, the bottom of the follower rod 15 is fixedly connected with a fixed rod 16, the outer wall of the support plate 7 is fixedly connected with a mounting plate 17, the top of the support plate 7 is in contact with the bottom of the power box 10, the outer wall of the fixed rod 16 is movably connected with the inner wall of the mounting plate 17, the fixed rod 16 is quickly inserted into the positioning hole of the mounting plate 17, the power box 10 is quickly locked, the outer wall of the fixed plate 11 is fixedly connected with the power box 10, and the fixed blocks 20 on the top of the aircraft body 8 are symmetrically distributed, each fixed block 20 is internally provided with a high-precision bearing, so that the propeller 9 can be kept stable during high-speed rotation and vibration transmission to the fuselage is reduced.
[0034] Working principle: the staff starts the unmanned aerial vehicle through the power box 10, the top of the aircraft body 8 has a plurality of fixed blocks 20, the motor drives the fixed blocks 20 to run at high speed, drives the propeller 9 to rotate synchronously, when the unmanned aerial vehicle lands, the gravity of the fuselage acts on the power box 10, so that it extrudes the supporting plate 7 downward, the supporting plate 7 pushes the driven rod 3 to move, at the same time drives the moving block two 19 to move downward, the driven rod 3 drives the moving rod 6 to move horizontally, pushes the sliding block 5 to slide in the limiting block 4, the displacement of the moving rod 6 drives the rotating rod 2 to rotate, forms multistage damping buffer, the limiting block 4 adopts the fully enclosed design, can effectively absorb and disperse the impact force generated when landing, so as to protect the core components of the unmanned aerial vehicle from being damaged, the air pressure damping structure has the problem of sealing aging, needs to be replaced after a period of use, the staff pulls the buckle body 12, the buckle body 12 drives the pull rod 13 to move, the spring 14 sleeved outside the pull rod 13 and the follower rod 15 is compressed immediately, provides buffer and power assistance for operation, the follower rod 15 moves downward under the traction of the pull rod 13, the fixed rod 16 fixed at the bottom thereof gradually separates from the limiting hole of the mounting plate 17, so that the supporting plate 7 can be replaced easily.
[0035] Finally, it should be pointed out that: the above only for preferred embodiments of the utility model, and does not limit the utility model, although the utility model is described in detail with reference to the foregoing embodiments, for the person skilled in the art, it still can modify the technical scheme recorded in the foregoing each embodiment, or equivalent replacement to part of technical features, any modification, equivalent replacement, improvement etc. made within the spirit and principles of the utility model, should be included in the protection scope of the utility model.
Claims
1. A vibration damping assembly for a lift-flier body structure comprising a base (1), characterised in that: The top of base (1) is rotatably connected with rotating rod (2), the other end of rotating rod (2) is rotatably connected with moving rod (6), the outer wall of moving rod (6) is rotatably connected with driven rod (3), the other end of driven rod (3) is rotatably connected with support plate (7), the other end of moving rod (6) is fixedly connected with sliding block (5), the outer wall of sliding block (5) is slidably connected with limiting block (4), the top of support plate (7) is provided with clamping assembly.
2. The VTOL aircraft fuselage structure shock mitigation assembly according to claim 1, wherein: The clamping assembly includes fixed plate (11), the bottom of fixed plate (11) is rotatably connected with buckle body (12), the outer wall of buckle body (12) is rotatably connected with pull rod (13), the outside of pull rod (13) is provided with follow-up rod (15), the outside of pull rod (13) is sleeved with spring (14), the bottom of follow-up rod (15) is fixedly connected with fixed rod (16), the outer wall of support plate (7) is fixedly connected with mounting plate (17).
3. The VTOL aircraft fuselage structure shock mitigation assembly according to claim 2, wherein: The outer wall of fixed plate (11) is fixedly connected with power box (10), the top of power box (10) is fixedly connected with aircraft body (8).
4. The VTOL aircraft fuselage structure shock mitigation assembly according to claim 3, wherein: The top of aircraft body (8) is fixedly connected with a plurality of fixed blocks (20), the inner wall of fixed block (20) is rotatably connected with propeller (9).
5. The VTOL aircraft fuselage structure shock mitigation assembly according to claim 1, wherein: The top of base (1) is fixedly connected with moving block one (18), the bottom of support plate (7) is fixedly connected with moving block two (19).
6. The VTOL aircraft fuselage structure shock mitigation assembly according to Claim 2, wherein: The outer wall of fixed rod (16) is movably connected with the inner wall of mounting plate (17), the inner wall of spring (14) is sleeved with the outer wall of follow-up rod (15).
7. The VTOL aircraft fuselage structure damping assembly according to claim 5, wherein: The top of moving block one (18) is slidably connected in the inside of limiting block (4), the bottom of moving block two (19) is slidably connected in the inside of limiting block (4).
8. The VTOL aircraft fuselage structure shock mitigation assembly according to claim 3, wherein: The top of support plate (7) is in contact with the bottom of power box (10), the inside of limiting block (4) is a sealed structure.