Take-off and landing aircraft with take-off and landing damping frame structure
By designing a combined structure of sliding column and return spring on the aircraft, the buffering of the aircraft is achieved, which solves the impact problem during vertical landing, and facilitates the disassembly of the blades through the design of telescopic springs and limit rods, extends the component life And reduces space.
Patent Information
- Application Number
- CN202421747448.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-23
- Publication Date
- 2024-12-27
- Estimated Expiration
- 2034-07-23
AI Technical Summary
Existing aircraft are difficult to effectively buffer when landing vertically, resulting in large impacts during landing and damage to structures or components.
A take-off and landing aircraft with a landing and shock absorbing frame structure is designed. It adopts a combination of a sliding column and a return spring. The sliding column drives the square slider to slide in the square opening, and uses the return spring to provide cushioning force to reduce impact, and uses the telescopic spring to It enables easy disassembly of the blades with limiting rods.
It significantly reduces damage and wear of aircraft structures and components, extends service life, and is conveniently disassembled and stored in non-working conditions.
Smart Images
Figure CN222247760U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the field of flying equipment, in particular to a take-off and landing aircraft with a take-off and landing shock-absorbing frame structure. Background Art
[0002] Flying equipment is a device that flies in the atmosphere or in outer space (space), including aircraft, spacecraft, rockets and missiles. Such aircraft are usually used to carry camera modules or other precision instruments for operations such as mapping, monitoring or scientific research. During the vertical landing of the aircraft, the impact force generated by the inertia of the fuselage will cause vibration to the fuselage and internal equipment, and the landing shock absorber structure can effectively alleviate this impact.
[0003] In the prior art, some aircraft are difficult to cushion, which may cause the aircraft to be subjected to a greater impact during landing, resulting in damage to the aircraft structure or components. In this case, the aircraft's bottom structure, landing gear, tires, etc. may be subjected to impact forces exceeding the designed bearing capacity. Therefore, a take-off and landing aircraft with a landing shock absorber structure is proposed to solve the above problem. Utility Model Content
[0004] In order to make up for the above shortcomings, the utility model provides a take-off and landing aircraft with a take-off and landing shock absorbing frame structure, aiming to improve the problem in the prior art that some aircraft are difficult to buffer, which easily causes the aircraft to be subjected to a large impact when landing.
[0005] In order to achieve the above purpose, the utility model adopts the following technical solutions:
[0006] A take-off and landing aircraft with a landing shock-absorbing frame structure includes an unmanned aerial vehicle body, wherein the four bottom corners of the unmanned aerial vehicle body are fixedly connected to support columns, the interior of the support columns is slidably connected to sliding columns, square openings are provided on the left and right sides of the interior of the support columns, square sliders are slidably connected to the inner walls of the square openings, the tops of the sliding columns are fixedly connected to return springs, the bottoms of two of the sliding columns are fixedly connected to tripods, the exterior of the unmanned aerial vehicle body is fixedly connected to a plurality of connecting columns, and the tops of the connecting columns are fixedly connected to disassembly components for disassembling the aircraft's blades.
[0007] As a further description of the above technical solution:
[0008] The disassembly assembly includes a fixing seat, an inner cavity is provided inside the fixing seat, a telescopic spring is arranged inside the inner cavity, buttons are slidably connected to the front and rear sides of the inner wall of the inner cavity, through holes are provided on the left and right inner walls of the fixing seat, the inner walls of the through holes are slidably connected to limit rods, a clamping block is detachably connected to the outside of the fixing seat, a connecting block is fixedly connected to the top of the clamping block, a paddle seat is fixedly connected to the top of the connecting block, and paddle blades are fixedly connected to the left and right sides of the paddle seat
[0009] As a further description of the above technical solution:
[0010] The adjacent sides of the two square sliding blocks are fixedly connected to the left and right sides of the sliding column.
[0011] As a further description of the above technical solution:
[0012] The outer parts of the two buttons are slidably connected to the front and rear sides of the fixing seat, and the adjacent sides of the two limit rods are fixedly connected to the left and right sides of the button.
[0013] As a further description of the above technical solution:
[0014] The bottom of the fixing seat is fixedly connected to the top of the connecting column.
[0015] As a further description of the above technical solution:
[0016] The top of the reset spring is fixedly connected to the bottom of the drone body, and the front and rear sides of the telescopic spring are fixedly connected to the adjacent sides of the two buttons.
[0017] As a further description of the above technical solution:
[0018] The front and rear sides of the bottom of the tripod are both fixedly connected with connecting frames.
[0019] As a further description of the above technical solution:
[0020] The far sides of the plurality of connecting frames are respectively fixedly connected with fixing frames, and the far sides of the plurality of fixing frames are respectively fixedly connected with wheels.
[0021] The utility model has the following beneficial effects:
[0022] 1. In the utility model, the sliding column structure drives the return spring structure to work, thereby achieving the effect of buffering the aircraft, thereby significantly reducing the damage and wear of the aircraft structure and related components, and extending the service life of these components.
[0023] 2. In the utility model, the button drives the spring to buckle the block to the fixed seat structure, so that the blades of the aircraft can be disassembled, so that the drone can be easily disassembled when not in operation, reducing the occupied space and facilitating carrying and storage. BRIEF DESCRIPTION OF THE DRAWINGS
[0024] Figure 1 This is a three-dimensional schematic diagram of a take-off and landing aircraft with a take-off and landing shock-absorbing frame structure proposed by the utility model;
[0025] Figure 2 This is a schematic diagram of the structure inside the support column of the take-off and landing aircraft with a take-off and landing shock-absorbing frame structure proposed by the utility model;
[0026] Figure 3 This is a schematic diagram of the structure inside the fixing seat of the take-off and landing aircraft with a take-off and landing shock-absorbing frame structure proposed by the utility model.
[0027] Legend:
[0028] 1. UAV body; 2. Support column; 3. Sliding column; 4. Tripod; 5. Connecting frame; 6. Fixed frame; 7. Connecting column; 8. Fixed seat; 9. Inner cavity; 10. Telescopic spring; 11. Button; 12. Through hole; 13. Limit rod; 14. Block; 15. Connecting block; 16. Paddle seat; 17. Paddle blade; 18. Square opening; 19. Square slider; 20. Reset spring. DETAILED DESCRIPTION
[0029] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.
[0030] Reference Figure 1-Figure 3The utility model provides an embodiment: a take-off and landing aircraft with a take-off and landing shock-absorbing frame structure, including an unmanned aircraft body 1, which is made of lightweight and high-strength material, and is designed with a guide rail inside to facilitate the smooth up and down movement of a sliding column 3. The four corners of the bottom of the unmanned aircraft body 1 are fixedly connected to support columns 2, and the inside of the support column 2 is slidably connected to the sliding column 3. The bottom of the support column 2 may have a waterproof sealing design to adapt to a humid environment. The reset spring 20 is located at the top of the sliding column 3. The left and right sides of the inside of the support column 2 are provided with a square opening 18. The inner wall of the square opening 18 is slidably connected to a square slider 19. When the aircraft takes off and lands, the sliding column 3 can move inside the support column 2, and the reset spring 20 provides cushioning and resilience, effectively reducing landing impact. The top of the sliding column 3 is fixedly connected with a return spring 20. The bottoms of the two sliding columns 3 are fixedly connected with a tripod 4. The end of the tripod 4 may be equipped with an anti-skid pad or a small fixing claw to adapt to different terrains as a structural connector between the drone body 1 and the disassembly component. The outside of the drone body 1 is fixedly connected with a plurality of connecting columns 7. This design allows for quick replacement of the blades 17. The disassembly component may include an unlocking mechanism driven by a small motor. The instructions are transmitted through the connecting column 7 to achieve quick release and fixation of the blades 17. The top of the connecting column 7 is fixedly connected with a disassembly component for disassembling the blades 17 of the aircraft.
[0031] Reference Figure 1-Figure 3 The disassembly assembly is an important part of the aircraft, which is used to conveniently disassemble and replace the blades 17 of the aircraft. The disassembly assembly includes a fixing seat 8, which is fixed on the aircraft for connecting and supporting other disassembly assemblies. An inner cavity 9 is provided inside the fixing seat 8, and a telescopic spring 10 is provided inside the inner cavity 9. The spring can apply appropriate force to the blades 17 and can buffer vibration and impact. The inner wall of the inner cavity 9 is slidably connected with buttons 11 on both sides. The buttons 11 are installed on both sides of the inner wall of the inner cavity 9 and are used to push Or pull to disassemble the assembly, the left and right inner walls of the fixed seat 8 are provided with through holes 12, the through holes 12 are provided on the left and right inner walls of the fixed seat 8, the inner walls of the through holes 12 are slidably connected to the limit rods 13, the inner walls of the through holes 12 are slidably connected to the limit rods 13, the design of the limit rods 13 can limit the moving range of the button 11, the card block 14 is detachably connected to the outside of the fixed seat 8, and the top of the card block 14 is fixedly connected to the connecting block 15, the connecting block 15 is fixedly connected to the paddle seat 16, and the left and right sides of the paddle seat 16 are fixedly connected to the paddle blades 17.
[0032] Reference Figure 1-Figure 3The adjacent sides of the two square sliders 19 are fixedly connected to the left and right sides of the sliding column 3, so that the stable connection of the sliding column 3 can be ensured. The outer sides of the two buttons 11 are slidably connected to the front and rear sides of the fixing seat 8, so that the operation of the disassembly assembly is more flexible. The adjacent sides of the two limit rods 13 are fixedly connected to the left and right sides of the button 11, which are used to limit the moving range of the button 11 to ensure the safe use of the disassembly assembly. The bottom of the fixing seat 8 is fixedly connected to the top of the connecting column 7 to support the connection between the disassembly assembly and the entire aircraft. The top of the reset spring 20 is fixedly connected to the bottom of the unmanned aerial vehicle body 1. Such a design can ensure the reset and stability of the disassembly assembly. The front and rear sides of the telescopic spring 10 are fixedly connected to the adjacent sides of the two buttons 11 to provide support and flexibility when the blades 17 are replaced. The front and rear sides of the bottom of the tripod 4 are fixedly connected with a connecting frame 5, and the remote sides of the multiple connecting frames 5 are respectively fixedly connected with a fixing frame 6, and the remote sides of the multiple fixing frames 6 are respectively fixedly connected with wheels. The design of these connecting frames 5 and fixing frames 6 can provide stable support and walking ability for the aircraft.
[0033] Working principle: First, the drone body 1 contacts the ground when landing, causing the drone body 1 to vibrate, and the square slider 19 is squeezed by the sliding column 3. The square slider 19 slides inside the square opening 18, so that the sliding column 3 squeezes the return spring 20 to shrink, thereby reducing the shock of the drone body and achieving the effect of buffering the aircraft, thereby significantly reducing the damage and wear of the aircraft structure and related components, and extending the service life of these components.
[0034] Secondly, the button 11 is fixed inside the limit rod 13, and the limit rod 13 drives the telescopic spring 10 to be compressed. The external sliding through hole 12 of the limit rod 13 shrinks the removable card block 14 outside the fixed seat 8. Pressing the button 11 drives the telescopic spring 10 to be compressed, so that the button 11 drives the limit rod 13 to slide back and forth, so that the bottom of the card block 14 is limited and stuck on the outside of the fixed seat 8, and the limit rod 13 expands the fixed card block 14 outward. After releasing the button 11, the button 11 drives the telescopic spring 10 to slide back and forth under the stress of the telescopic spring 10, thereby realizing the disassembly of the blades 17 of the aircraft, so that the drone can be easily disassembled when not in working state, reducing the occupied space and facilitating carrying and storage.
[0035] Finally, it should be noted that the above is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or make equivalent substitutions for some of the technical features therein. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.
Claims
1. A take-off and landing aircraft with a take-off and landing shock-absorbing frame structure, comprising an unmanned vehicle body (1), characterized in that: The four corners of the bottom of the unmanned aerial vehicle (1) are fixedly connected to support columns (2), the interior of the support columns (2) is slidably connected to a sliding column (3), the interior of the support columns (2) is provided with square openings (18) on both left and right sides, the inner wall of the square opening (18) is slidably connected to a square sliding block (19), the top of the sliding column (3) is fixedly connected to a return spring (20), the bottoms of the two sliding columns (3) are fixedly connected to a tripod (4), the exterior of the unmanned aerial vehicle (1) is fixedly connected to a plurality of connecting columns (7), and the top of the connecting columns (7) is fixedly connected to a disassembly assembly for disassembling the propeller blades (17) of the aircraft.
2. The take-off and landing aircraft with a take-off and landing shock-absorbing frame structure according to claim 1, characterized in that: The disassembly assembly comprises a fixing seat (8), an inner cavity (9) is provided inside the fixing seat (8), a telescopic spring (10) is arranged inside the inner cavity (9), buttons (11) are slidably connected to the front and rear inner walls of the inner cavity (9), through holes (12) are provided on the left and right inner walls of the fixing seat (8), the inner walls of the through holes (12) are slidably connected to limit rods (13), a clamping block (14) is detachably connected to the outside of the fixing seat (8), a connecting block (15) is fixedly connected to the top of the clamping block (14), a paddle seat (16) is fixedly connected to the top of the connecting block (15), and paddle blades (17) are fixedly connected to the left and right sides of the paddle seat (16).
3. The take-off and landing aircraft with a take-off and landing shock-absorbing frame structure according to claim 1, characterized in that: The adjacent sides of the two square sliding blocks (19) are fixedly connected to the left and right sides of the sliding column (3).
4. The take-off and landing aircraft with a take-off and landing shock-absorbing frame structure according to claim 2, characterized in that: The outsides of the two buttons (11) are slidably connected to the front and rear sides of the fixing seat (8), and the adjacent sides of the two limit rods (13) are fixedly connected to the left and right sides of the button (11).
5. The take-off and landing aircraft with a take-off and landing shock-absorbing frame structure according to claim 2, characterized in that: The bottom of the fixing seat (8) is fixedly connected to the top of the connecting column (7).
6. The take-off and landing aircraft with a take-off and landing shock-absorbing frame structure according to claim 2, characterized in that: The top of the return spring (20) is fixedly connected to the bottom of the drone body (1), and the front and rear sides of the telescopic spring (10) are fixedly connected to adjacent sides of the two buttons (11).
7. The take-off and landing aircraft with a take-off and landing shock-absorbing frame structure according to claim 1, characterized in that: The front and rear sides of the bottom of the tripod (4) are both fixedly connected to connecting frames (5).
8. The take-off and landing aircraft with a take-off and landing shock-absorbing frame structure according to claim 7, characterized in that: The far sides of the plurality of connecting frames (5) are respectively fixedly connected to fixing frames (6), and the far sides of the plurality of fixing frames (6) are respectively fixedly connected to wheels.