Carbon fiber landing pad for vertical take-off and landing aircraft

Abstract

The carbon fiber landing frame comprises a square frame, frames are connected to the two sides of the square frame in a bolted mode, threaded shafts are arranged in the frames, the two ends of the threaded shafts are rotationally connected with the frames through bearings, one ends of the threaded shafts are fixedly connected with first bevel gears in a sleeved mode, and the other ends of the threaded shafts are fixedly connected with second bevel gears in a sleeved mode. According to the device, the driving motor rotates forwards and backwards to drive a bevel gear set and a threaded shaft to achieve the synergistic effect, folding and unfolding of the supporting legs are achieved, maneuverability is improved, and the supporting legs are stable and reliable in the folding and unfolding process through the matched design of a threaded sleeve and a sliding rod; the damping shock absorber is arranged to effectively absorb the impact force generated when the aircraft vertically lands, the landing buffer performance is greatly improved, the impact damage to the aircraft structure is reduced, the carbon fiber material is applied, the overall weight is reduced, the strength and durability of the device are enhanced, and the device is suitable for the flight environment with frequent take-off and landing.

Description

Technical Field

[0001] This utility model belongs to the technical field of vertical take-off and landing aircraft, and specifically relates to a carbon fiber landing gear for vertical take-off and landing aircraft. Background Technology

[0002] Vertical takeoff and landing (VTOL) aircraft have broad application prospects in fields such as unmanned aerial vehicles (UAVs) and urban air traffic due to their flexible takeoff and landing characteristics.

[0003] Currently, Chinese utility model patent CN207029527U discloses a drone tripod that solves the technical problem of inconvenient assembly and disassembly of drone tripods from the drone fuselage in the prior art. This drone tripod is inserted into the drone fuselage, and the insertion end of the tripod is equipped with an elastic fixing button. The elastic fixing button is connected to an elastic support component and can extend and retract radially along the insertion end. When the drone tripod is inserted into the drone fuselage, the elastic fixing button engages with the drone fuselage, enabling the assembly of the drone tripod. Pressing the elastic fixing button disengages the engagement, allowing for disassembly of the drone tripod. Moreover, it can be done directly by hand, making tripod assembly and disassembly convenient and quick. By incorporating this drone tripod, tripod assembly and disassembly can be performed very quickly, facilitating carrying and maintenance.

[0004] However, traditional vertical takeoff and landing (VTOL) aircraft landers typically employ a fixed structure, which cannot be retracted or extended during flight, affecting flight efficiency and potentially reducing maneuverability. Furthermore, the impact force during vertical landing is significant, and the lack of an effective cushioning structure can easily lead to structural damage or equipment vibration failure. To address these issues, we provide a carbon fiber lander for VTOL aircraft. Utility Model Content

[0005] The purpose of this invention is to provide a carbon fiber landing gear for vertical take-off and landing aircraft, in order to solve the problems mentioned in the background art, that traditional vertical take-off and landing aircraft landing gear usually adopts a fixed structure, which cannot be retracted during flight, and also lacks an effective cushioning structure.

[0006] The above-mentioned technical objective of this utility model is achieved through the following technical solution: a carbon fiber landing gear for a vertical take-off and landing aircraft, comprising a square frame, with frames bolted to both sides of the square frame, a threaded shaft provided inside the frame, both ends of the threaded shaft being rotatably connected to the frame via bearings, a first bevel gear fixedly sleeved at one end of the threaded shaft, a drive motor bolted to the back of the square frame, a second bevel gear fixedly sleeved at the output end of the drive motor, the surface of the first bevel gear meshing with the second bevel gear through teeth, a threaded sleeve threadedly connected to the surface of the threaded shaft, a slide rod fixedly connected to both the front and back of the threaded sleeve, through grooves adapted to the slide rods being opened on both the front and back of the frame, the surface of the slide rods being slidably connected to the through grooves, a support leg rotatably sleeved on the surface of the slide rods, a damping shock absorber rotatably connected inside the support leg via a pin, and the other end of the damping shock absorber being hinged to the frame.

[0007] Preferably, one end of the outrigger is fixedly connected to a sleeve, and a support rod is sleeved inside the sleeve.

[0008] Preferably, both ends of the support rod are fitted with rubber sleeves, and the surface of the rubber sleeves is provided with anti-slip texture.

[0009] Preferably, the top of the frame is provided with an installation mechanism, the installation mechanism includes an installation plate, the bottom of the installation plate is fitted with a fixing bolt, one end of the fixing bolt is threaded to the frame, and the installation bolt is fitted inside the installation plate.

[0010] In summary, this utility model has the following beneficial effects:

[0011] The device achieves the folding and unfolding of the outriggers by driving the forward and reverse rotation of the motor to drive the bevel gear set and the threaded shaft in synergy, thereby improving maneuverability. The design of the threaded sleeve and the sliding rod makes the outriggers retraction and extension process smooth and reliable. The damping shock absorber effectively absorbs the impact force when the aircraft lands vertically, greatly improving the landing cushioning performance and reducing impact damage to the aircraft structure. The application of carbon fiber materials not only reduces the overall weight, but also enhances the strength and durability of the device, making it suitable for flight environments with frequent take-offs and landings. Attached Figure Description

[0012] Figure 1 This is a three-dimensional structural schematic diagram of the present invention;

[0013] Figure 2 This is a partial structural cross-sectional view of the present invention;

[0014] Figure 3 This is a three-dimensional schematic diagram of a partial structure of this utility model.

[0015] Reference numerals: 1. Frame; 2. Frame; 3. Threaded shaft; 4. First bevel gear; 5. Drive motor; 6. Second bevel gear; 7. Threaded sleeve; 8. Slide rod; 9. Through groove; 10. Support leg; 11. Damping shock absorber; 12. Sleeve; 13. Support rod; 14. Rubber sleeve; 15. Mounting mechanism; 151. Mounting plate; 152. Fixing bolt; 153. Mounting bolt. Detailed Implementation

[0016] The present invention will be further described in detail below with reference to the accompanying drawings.

[0017] Example 1:

[0018] refer to Figure 1-3 A carbon fiber landing gear for vertical takeoff and landing (VTOL) aircraft includes a frame 1, with frames 2 bolted to both sides of the frame 1. A threaded shaft 3 is disposed inside the frame 2, with both ends of the threaded shaft 3 rotatably connected to the frame 2 via bearings. A first bevel gear 4 is fixedly sleeved at one end of the threaded shaft 3. A drive motor 5 is bolted to the back of the frame 1, and a second bevel gear 6 is fixedly sleeved at the output end of the drive motor 5. The surface of the first bevel gear 4 meshes with the second bevel gear 6 through its teeth. A threaded sleeve 7 is threadedly connected to the surface of the threaded shaft 3. The front and back of the sleeve 7 are fixedly connected to the slide rod 8. The front and back of the frame 2 are provided with through grooves 9 that are adapted to the slide rod 8. The surface of the slide rod 8 is slidably connected to the through groove 9. The surface of the slide rod 8 is rotatably sleeved with the support leg 10. The inside of the support leg 10 is rotatably connected to the damping shock absorber 11 through the pin. The other end of the damping shock absorber 11 is hinged to the frame 2. The square frame 1, the frame 2 and the support leg 10 are all made of carbon fiber material. The first bevel gear 4 and the second bevel gear 6 are both made of high-strength plastic, which makes it easier to reduce the weight of the device.

[0019] refer to Figure 1 One end of the outrigger 10 is fixedly connected to a sleeve 12, and a support rod 13 is sleeved inside the sleeve 12. The outrigger 10, sleeve 12 and support rod 13 are all made of carbon fiber material.

[0020] refer to Figure 1 Both ends of the support rod 13 are fitted with rubber sleeves 14. The surface of the rubber sleeves 14 is provided with anti-slip texture. By setting the rubber sleeves 14, the anti-slip function can be effectively achieved.

[0021] refer to Figure 3 The top of the frame 2 is provided with an installation mechanism 15, which includes an installation plate 151 made of carbon fiber material. The bottom of the installation plate 151 is fitted with a fixing bolt 152, one end of which is threaded to the frame 2. The inside of the installation plate 151 is fitted with an installation bolt 153. By setting the installation mechanism 15, it is easy to install the device to the aircraft.

[0022] Brief description of usage: The user can bolt the mounting plate 151 of the device to the bottom of the aircraft using mounting bolts 153. When the aircraft is in flight, the drive motor 5 can be started to rotate forward, driving the second bevel gear 6 to rotate. The second bevel gear 6 drives the threaded shaft 3 to rotate through the first bevel gear 4. At the same time, the threaded shaft 3 drives the threaded sleeve 7 to move in the direction of the first bevel gear 4, causing the threaded sleeve 7 to drive the slide rod 8 to slide inside the through groove 9. Then, the slide rod 8 drives the support leg 10 to move, causing the support leg 10 to pass through the damping shock absorber 1. The outrigger 10 is folded and rotated in coordination with the support rod 14, which facilitates its folding. During landing, the drive motor 5 is started and reversed to move the threaded sleeve 7 away from the first bevel gear 4. The threaded sleeve 7 moves the outrigger 10 through the slide rod 8, allowing the outrigger 10 to unfold and be supported by the damping shock absorber 11. At the same time, when the aircraft lands vertically, when the support rod 13 contacts the ground through the rubber sleeve 14, the weight of the aircraft compresses and resets the damping shock absorber 11 through the outrigger 10, which effectively provides cushioning protection for the aircraft landing.

[0023] This specific embodiment is merely an explanation of the present utility model and is not intended to limit the present utility model. After reading this specification, those skilled in the art can make modifications to this embodiment without contributing any inventive step, but as long as they are within the scope of the claims of the present utility model, they are protected by patent law.

Claims

1. A carbon fiber landing gear for a vertical takeoff and landing aircraft, comprising a rectangular frame (1), characterized in that: Both sides of the square frame (1) are bolted with frames (2). A threaded shaft (3) is installed inside the frame (2). Both ends of the threaded shaft (3) are rotatably connected to the frame (2) via bearings. A first bevel gear (4) is fixedly sleeved on one end of the threaded shaft (3). A drive motor (5) is bolted to the back of the square frame (1). A second bevel gear (6) is fixedly sleeved on the output end of the drive motor (5). The surface of the first bevel gear (4) meshes with the second bevel gear (6) through its teeth. The surface of the threaded shaft (3) is threaded with a threaded sleeve (7). The front and back sides of the threaded sleeve (7) are fixedly connected with a slide rod (8). The front and back sides of the frame (2) are provided with through grooves (9) that are adapted to the slide rod (8). The surface of the slide rod (8) is slidably connected to the through groove (9). The surface of the slide rod (8) is rotatably sleeved with a support leg (10). The inside of the support leg (10) is rotatably connected to a damping shock absorber (11) through a pin. The other end of the damping shock absorber (11) is hinged to the frame (2).

2. A carbon fiber landing gear for a vertical takeoff and landing aircraft according to claim 1, characterized in that: One end of the support leg (10) is fixedly connected to a sleeve (12), and a support rod (13) is sleeved inside the sleeve (12).

3. A carbon fiber landing gear for a vertical takeoff and landing aircraft according to claim 2, characterized in that: Both ends of the support rod (13) are fitted with rubber sleeves (14), and the surface of the rubber sleeves (14) is provided with anti-slip texture.

4. A carbon fiber landing gear for a vertical takeoff and landing aircraft according to claim 1, characterized in that: The top of the frame (2) is provided with an installation mechanism (15), the installation mechanism (15) includes an installation plate (151), the bottom of the installation plate (151) is fitted with a fixing bolt (152), one end of the fixing bolt (152) is threadedly connected to the frame (2), and the inside of the installation plate (151) is fitted with an installation bolt (153).

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