Landing structure of unmanned air-ground aircraft

Abstract

The landing structure of the unmanned air-ground aircraft comprises an installation support, two supporting devices, an installation hole, a limiting groove and a streamline fairing, the two supporting devices are symmetrically arranged and arranged on the two sides of the bottom end of the installation support, and the installation hole is formed in the installation hole. The supporting device comprises a first supporting plate, a second supporting plate, a servo motor, a mounting part and two supporting legs, the two supporting legs are symmetrically arranged, one end of each supporting leg is fixedly connected to the first supporting plate, and the other end of each supporting leg is rotationally connected to the interior of the mounting part. The supporting device can be freely folded and unfolded, the streamline fairing is installed, the folded supporting device is effectively shielded, therefore, wind resistance during flight is reduced, the flight speed of the aircraft can be increased, and meanwhile the risk that the supporting plate is hung by branches or other foreign matter in the flight process is avoided through the design of the fairing.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft landing structures, in particular to a landing structure for an unmanned ground-to-air aircraft. Background Art

[0002] Unmanned ground-to-air vehicles need to land safely after performing their missions. However, unmanned ground-to-air vehicles are easily affected by environmental factors (such as wind, terrain, etc.) during landing, and often hit the ground, resulting in landing failure or equipment damage. In addition, the landing structure of the aircraft will generate wind resistance and easily get caught by foreign objects such as branches, thus affecting the flight of the aircraft. Therefore, a landing structure for unmanned ground-to-air vehicles is urgently needed to solve the above problems. Utility Model Content

[0003] The purpose of the utility model is to provide a landing structure for an unmanned ground-to-air vehicle to solve the problems raised in the above-mentioned background technology.

[0004] To achieve the above-mentioned purpose, the utility model provides the following technical solutions: a landing structure of an unmanned ground-to-air aircraft, comprising a mounting bracket, a supporting device, a mounting hole, a limiting groove and a streamlined fairing, wherein two supporting devices are symmetrically arranged, and the two supporting devices are arranged on both sides of the bottom end of the mounting bracket, the supporting device comprises a first supporting plate, a second supporting plate, a servo motor, a mounting piece and a leg, the two legs are symmetrically arranged, and one end of the leg is fixedly connected to the first supporting plate, and the other end of the leg is rotatably connected to the inside of the mounting piece, the driving end of the servo motor is fixedly connected to one end of one of the legs close to the mounting piece, a plurality of hydraulic rods are evenly fixedly installed on the bottom end of the first supporting plate, a shock absorbing spring is nested on the outer side of the hydraulic rod, and two limiting sliding rods are symmetrically fixedly connected to the top end of the second supporting plate, and the top end of the limiting sliding rod is threadedly connected to a limiting nut.

[0005] Preferably, one end of the supporting leg close to the mounting member is fixedly connected to a limiting block, and the limiting block is located on a side of the mounting member away from the servo motor.

[0006] Preferably, the limiting sliding rod is slidably connected to the first supporting plate, and the bottom end of the limiting nut is in close contact with the top end of the first supporting plate.

[0007] Preferably, the servo motor is fixedly mounted on the bottom end of the mounting bracket, and the mounting piece is fixedly mounted on the bottom end of the mounting bracket.

[0008] Preferably, four limiting grooves are provided, and the limiting grooves are evenly and symmetrically opened on both sides of the bottom end of the mounting bracket, and the limiting blocks are movably clamped on the inner sides of the limiting grooves.

[0009] Preferably, the mounting holes are evenly arranged, and the mounting holes are symmetrically and evenly penetrated through the two ends of the top end of the mounting bracket, and the mounting holes are located at the two ends of the supporting device.

[0010] Preferably, the streamlined fairing is fixedly connected to one end of the bottom end of the mounting bracket, and the streamlined fairing is located between the mounting hole and the supporting device.

[0011] Preferably, the bottom end of the hydraulic rod is in close contact with the top end of the second support plate, the top end of the shock absorbing spring is in close contact with the bottom end of the first support plate, and the bottom end of the shock absorbing spring is in close contact with the top end of the second support plate.

[0012] Compared with the prior art, the beneficial effects of the utility model are as follows:

[0013] The utility model can flexibly deploy the support device through the servo motor during landing, so as to provide stable landing support for the aircraft. The combined design of the hydraulic rod and the shock-absorbing spring achieves a shock-absorbing and buffering effect during landing of the aircraft. During flight, the support device can be retracted at the bottom of the mounting bracket to reduce the impact on flight performance. By installing a streamlined fairing, the retracted support device can be effectively shielded, thereby reducing wind resistance during flight and helping to increase the flight speed of the aircraft. At the same time, the design of the fairing also avoids the risk of the support plate being caught by tree branches or other foreign objects during flight. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the main three-dimensional structure of the utility model;

[0015] Figure 2 This is a schematic diagram of the second state structure of the main body in the utility model;

[0016] Figure 3 This is a schematic diagram of the main body bottom structure in the utility model;

[0017] Figure 4 It is a schematic diagram of the structure of the support device in the utility model;

[0018] Figure 5 It is a schematic diagram of the disassembled structure of the supporting device in the utility model.

[0019] In the figure: 1-mounting bracket, 2-support device, 3-mounting hole, 4-limiting groove, 5-first support plate, 6-second support plate, 7-servo motor, 8-mounting part, 9-leg, 10-hydraulic rod, 11-shock-absorbing spring, 12-limiting nut, 13-limiting slide rod, 14-limiting block, 15-streamlined fairing. DETAILED DESCRIPTION

[0020] 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.

[0021] See also Figure 1-5 The utility model provides an embodiment: a landing structure of an unmanned ground-to-air vehicle, comprising a mounting bracket 1, a supporting device 2, a mounting hole 3, a limiting groove 4 and a streamlined fairing 15, wherein two supporting devices 2 are symmetrically arranged, and the two supporting devices 2 are arranged on both sides of the bottom end of the mounting bracket 1, the supporting device 2 comprises a first supporting plate 5, a second supporting plate 6, a servo motor 7, a mounting member 8 and a leg 9, the servo motor 7 is fixedly mounted on the bottom end of the mounting bracket 1, the mounting member 8 is fixedly mounted on the bottom end of the mounting bracket 1, two legs 9 are symmetrically arranged, and one end of the leg 9 is fixedly connected to the first supporting plate 5, and the other end of the leg 9 is rotatably connected to the inside of the mounting member 8, the driving end of the servo motor 7 is fixedly connected to one end of one of the legs 9 close to the mounting member 8, a plurality of hydraulic rods 10 are evenly fixedly installed on the bottom end of the first supporting plate 5, and a shock absorbing spring 11 is nested on the outer side of the hydraulic rod 10, and two limiting slide bars 13 are symmetrically fixedly connected to the top end of the second supporting plate 6, and the top end of the limiting slide bar 13 is threadedly connected with a limiting nut 12.

[0022] One end of the leg 9 close to the mounting member 8 is fixedly connected to the limit block 14, and the limit block 14 is located on the side of the mounting member 8 away from the servo motor 7. There are four limit slots 4, and the limit slots 4 are evenly and symmetrically opened on both sides of the bottom end of the mounting bracket 1, and the limit block 14 is movably connected to the inner side of the limit slot 4. When the aircraft lands, the support device 2 rotates outward and unfolds, and at the same time the limit block 14 rotates to the inside of the limit slot 4. When the top of the limit block 14 is close to the inner top of the limit slot 4, the support device 2 is fully unfolded.

[0023] The limiting slide bar 13 is slidably connected to the first support plate 5, and the bottom end of the limiting nut 12 is close to the top end of the first support plate 5. When the aircraft lands, the first support plate 5 vibrates up and down under the impact of landing. The first support plate 5 slides on the limiting slide bar 13 and is prevented from sliding out of the limiting slide bar 13 by the limiting nut 12.

[0024] The mounting holes 3 are evenly arranged, and the mounting holes 3 are symmetrically and evenly opened at both ends of the top of the mounting bracket 1, and the mounting holes 3 are located at both ends of the supporting device 2. The mounting bracket 1 is fixedly installed at the bottom of the aircraft through the mounting holes 3, which can adapt to different aircraft.

[0025] The streamlined fairing 15 is fixedly connected to one end of the bottom of the mounting bracket 1, and the streamlined fairing 15 is located between the mounting hole 3 and the supporting device 2. The streamlined fairing 15 is arranged at the front end of the supporting device 2 to reduce the wind resistance that may be caused by the supporting device 2, and reduce the probability of the supporting device 2 mounting items.

[0026] The bottom end of the hydraulic rod 10 is in close contact with the top end of the second support plate 6, the top end of the shock-absorbing spring 11 is in close contact with the bottom end of the first support plate 5, and the bottom end of the shock-absorbing spring 11 is in close contact with the top end of the second support plate 6. The hydraulic rod 10 and the shock-absorbing spring 11 achieve a shock-absorbing effect, thereby improving the cushioning effect of the aircraft landing and reducing the impact.

[0027] Working principle: During use, first use bolts to fix the mounting bracket 1 to the bottom end of the aircraft through the mounting hole 3, and the end of the mounting bracket 1 close to the streamlined fairing 15 is located at the front end of the aircraft, and then the servo motor 7 and the controller inside the aircraft are electrically connected by wire. When the aircraft is flying, the two support devices 2 are both retracted at the bottom end of the mounting bracket 1, and the streamlined fairing 15 is used to shield the retracted support devices 2 to reduce wind resistance and increase the flight speed of the aircraft. When the aircraft is flying, the streamlined fairing 15 can prevent the first support plate 5 or the second support plate 6 from hanging on tree branches or other foreign objects. When the aircraft needs to land, the remote controller is used to control the aircraft to lower its altitude. When the aircraft is lowered to a safe landing distance, the remote controller is used to control the aircraft controller. , the controller controls the servo motor 7 to rotate, and the driving end of the servo motor 7 drives the support leg 9 to rotate. The rotation of the support leg 9 drives the first support plate 5 to rotate toward the outside of the bottom end of the mounting bracket 1, and the rotation of the first support plate 5 drives the second support plate 6 to rotate. At the same time, the rotation of the support leg 9 drives the limit block 14 to rotate until the limit block 14 rotates to the inside of the limit slot 4. At this time, the top of the limit block 14 is against the inner top of the limit slot 4. When the second support plate 6 contacts the ground, under the impact of gravity of the aircraft, the first support plate 5 squeezes the shock-absorbing spring 11 downward to shrink. At the same time, the hydraulic rod 10 shrinks and absorbs pressure and converts it into heat energy to achieve buffering. When the shock-absorbing spring 11 rebounds, it pushes the first support plate 5 to move upward, and at the same time drives the hydraulic rod 10 to extend to consume kinetic energy again to reduce vibration, thereby achieving a safe landing of the aircraft.

[0028] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A landing structure for an unmanned ground-to-air vehicle, comprising a mounting bracket (1), a supporting device (2), a mounting hole (3), a limiting groove (4) and a streamlined fairing (15), characterized in that: The supporting device (2) is symmetrically provided with two, and the two supporting devices (2) are arranged on both sides of the bottom end of the mounting bracket (1), the supporting device (2) comprises a first supporting plate (5), a second supporting plate (6), a servo motor (7), a mounting member (8) and a leg (9), the two legs (9) are symmetrically provided with one, and one end of the leg (9) is fixedly connected to the first supporting plate (5), and the other end of the leg (9) is rotatably connected to the inside of the mounting member (8), the driving end of the servo motor (7) is fixedly connected to one end of one of the legs (9) close to the mounting member (8), a plurality of hydraulic rods (10) are evenly fixedly installed at the bottom end of the first supporting plate (5), and a shock absorbing spring (11) is embedded on the outer side of the hydraulic rod (10), and the top end of the second supporting plate (6) is symmetrically fixedly connected with two limit slide bars (13), and the top end of the limit slide bar (13) is threadedly connected with a limit nut (12).

2. The landing structure of an unmanned ground-to-air vehicle according to claim 1, characterized in that: One end of the support leg (9) close to the mounting member (8) is fixedly connected to a limit block (14), and the limit block (14) is located on a side of the mounting member (8) away from the servo motor (7).

3. The landing structure of an unmanned ground-to-air vehicle according to claim 1, characterized in that: The limiting sliding rod (13) is slidably connected to the first supporting plate (5), and the bottom end of the limiting nut (12) is in close contact with the top end of the first supporting plate (5).

4. The landing structure of an unmanned ground-to-air vehicle according to claim 1, characterized in that: The servo motor (7) is fixedly mounted on the bottom end of the mounting bracket (1), and the mounting member (8) is fixedly mounted on the bottom end of the mounting bracket (1).

5. The landing structure of an unmanned ground-to-air vehicle according to claim 2, characterized in that: There are four limit grooves (4), and the limit grooves (4) are evenly and symmetrically arranged on both sides of the bottom end of the mounting bracket (1), and the limit block (14) is movably clamped on the inner side of the limit groove (4).

6. The landing structure of an unmanned ground-to-air vehicle according to claim 1, characterized in that: The mounting holes (3) are evenly arranged, and the mounting holes (3) are symmetrically and evenly penetrated at both ends of the top end of the mounting bracket (1), and the mounting holes (3) are located at both ends of the supporting device (2).

7. The landing structure of an unmanned ground-to-air vehicle according to claim 1, characterized in that: The streamlined fairing (15) is fixedly connected to one end of the bottom of the mounting bracket (1), and the streamlined fairing (15) is located between the mounting hole (3) and the supporting device (2).

8. The landing structure of an unmanned ground-to-air vehicle according to claim 2, characterized in that: The bottom end of the hydraulic rod (10) is in close contact with the top end of the second support plate (6), the top end of the shock absorbing spring (11) is in close contact with the bottom end of the first support plate (5), and the bottom end of the shock absorbing spring (11) is in close contact with the top end of the second support plate (6).

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