Undercarriage structure of ducted unmanned aerial vehicle

Abstract

The utility model discloses an undercarriage structure of a ducted unmanned aerial vehicle. The unmanned aerial vehicle comprises a vehicle body, landing gear bodies are arranged on the vehicle body, the landing gear bodies are arranged on the front side and the rear side of the vehicle body and fixedly connected with the vehicle body, landing wheels are installed at the left end and the right end of each landing gear body, the two landing gear bodies are fixedly connected through connecting beams, and the connecting beams are arranged on the left side and the right side of the vehicle body. The unmanned aerial vehicle landing device has the advantages that the stability of the posture of an unmanned aerial vehicle in the automatic landing process is effectively improved, meanwhile, the ground touching bounce amplitude of an undercarriage is reduced, and the automatic landing point precision is improved; the structural strength and the structural stability of the unmanned aerial vehicle are improved; local stress concentration is reduced; and the anti-breaking effect is achieved.

Description

TECHNICAL FIELD

[0001] The utility model relates to the unmanned plane landing gear related technical field, especially point to a kind of landing gear structure of ducted fan unmanned plane. BACKGROUND

[0002] Unmanned aircraft is called "unmanned plane" for short, and its English abbreviation is "UAV". It is a kind of unmanned aircraft that is controlled by wireless remote control equipment and self-provided program control device, or is completely or intermittently operated by vehicle-mounted computer.

[0003] Compared with the rotor unmanned plane, the ducted fan unmanned plane has the advantages of small size, regular external shape, easy to carry, store and transport, and suitable for cluster operation, because the lift fan is embedded in the fuselage.

[0004] The existing ducted fan unmanned plane has poor stability during landing, and the landing gear has large bounce amplitude when touching the ground, and is prone to deformation under pressure.

[0005] In summary, there is a need for a ducted fan unmanned plane landing gear structure that can improve landing stability and improve structural strength. INVENTION CONTENTS

[0006] The utility model discloses in order to overcome the prior art unmanned plane in landing process stability is not high, landing gear bounce amplitude when touching the ground is big, and the landing gear is prone to deformation under pressure, provide a kind of ducted fan unmanned plane landing gear structure that can improve landing stability and improve structural strength.

[0007] In order to achieve the above purpose, the utility model adopts the following technical scheme:

[0008] A landing gear structure of ducted fan unmanned plane, comprising a machine body, the machine body is provided with a landing gear body, the landing gear body is placed on the front and rear sides of the machine body and is fixedly connected with the machine body, the left and right ends of the landing gear body are both installed with landing wheels, two landing gear bodies are fixedly connected through connecting beams, and the connecting beams are placed on the left and right sides of the machine body.

[0009] The landing gear on the front and rear sides is symmetrical to each other, and the landing wheels at the two ends of the landing gear are symmetrical to each other, which can effectively improve the stability of the unmanned plane attitude during automatic landing, reduce the bounce amplitude of the landing gear when touching the ground, and improve the automatic landing point accuracy. The two landing gears are connected and fixed by the connecting beams, which further improves the structural strength and stability of the unmanned plane.

[0010] As preferred, the landing gear body comprises a horizontal part, the horizontal part is fixedly connected with the machine body, both sides of the horizontal part are respectively provided with a first fold line part and a second fold line part, the first fold line part is arranged between the horizontal part and the second fold line part, one end of the first fold line part is connected with the horizontal part, the first fold line part is inclined to the side away from the machine body, the other end of the first fold line part is connected with the second fold line part, the second fold line part is inclined to the side away from the machine body, and the landing wheel is arranged on the second fold line part. Through the inclined design of the first fold line part and the second fold line part, the stability and strength of the landing gear are greatly improved, so that the stress received by the landing gear during the landing of the unmanned aerial vehicle can be dispersed to a wider area, and the local stress concentration is reduced. Through the design of the friction plate, the unmanned aerial vehicle sliding on the ground can be automatically decelerated.

[0011] As preferred, the obtuse angle between the first fold line part and the horizontal part is 140°-145°, and the obtuse angle between the second fold line part and the first fold line part is 145°-150°. The stability is good, the structural strength is high, the stress received by the unmanned aerial vehicle during landing is more easily dispersed to a wide area, and the local stress concentration is better reduced.

[0012] As preferred, the connection between the first fold line part and the horizontal part and the connection between the second fold line part and the first fold line part are both smoothly transitioned through a round corner. The stress concentration effect of the connection between the first fold line part and the horizontal part and the connection between the second fold line part and the first fold line part is reduced, and the effect of preventing breakage is achieved.

[0013] As preferred, the second fold line part is fixedly connected with an axle, the axle is fixedly connected with a first reinforcing sheet and a second reinforcing sheet, the first reinforcing sheet and the second reinforcing sheet are respectively fixed on the side walls on both sides of the second fold line part, a hub bearing is arranged on the axle, and the landing wheel is sleeved on the outside of the hub bearing. Through the design of the first reinforcing sheet and the second reinforcing sheet, the connection strength between the second fold line part and the axle is improved.

[0014] As preferred, one end of the connecting beam is fixedly connected with an axle on one of the landing gear bodies, the other end of the connecting beam is fixedly connected with an axle on the other landing gear body, a friction plate is further fixedly connected with the axle, the friction plate is arranged on the side of the landing wheel and in contact with the landing wheel, and the friction plate is fixedly connected with the connecting beam. Through the design of the friction plate, the unmanned aerial vehicle sliding on the ground can be automatically decelerated.

[0015] The utility model discloses a landing gear for unmanned aerial vehicle, which can effectively improve the stability of the unmanned aerial vehicle during automatic landing, reduce the bounce amplitude of the landing gear when touching the ground, improve the precision of the automatic landing point, improve the structural strength and stability of the unmanned aerial vehicle, reduce the local stress concentration, and prevent breakage. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 is a perspective view of the utility model;

[0017] Figure 2 is a front view of the utility model;

[0018] Figure 3 is Figure 2 the enlarged view of A in the middle.

[0019] In the figure: 1. machine body, 2. landing wheel, 3. connecting beam, 4. horizontal part, 5. fold line part one, 6. fold line part two, 7. wheel shaft, 8. reinforcing sheet one, 9. reinforcing sheet two, 10. wheel hub bearing, 11. friction plate. DETAILED DESCRIPTION

[0020] The utility model will be further described below in combination with the drawings and specific embodiments.

[0021] As Figure 1 , Figure 2 and Figure 3 The embodiment described in the ducted unmanned aerial vehicle landing gear structure, including machine body 1, machine body 1 is equipped with landing gear body, landing gear body is placed in the front and rear two sides of machine body 1 and is fixedly connected with it, the left and right ends of landing gear body are all installed with landing wheel 2, two landing gear bodies are fixedly connected through connecting beam 3, and connecting beam 3 is placed in the left and right sides of machine body 1.

[0022] Landing gear body includes horizontal part 4, and horizontal part 4 is fixedly connected with machine body 1, and the left and right sides of horizontal part 4 are all equipped with fold line part one 5 and fold line part two 6, fold line part one 5 is placed between horizontal part 4 and fold line part two 6, one end of fold line part one 5 is connected with horizontal part 4, fold line part one 5 is inclined to the side away from machine body 1, the other end of fold line part one 5 is connected with fold line part two 6, and fold line part two 6 is inclined to the side away from machine body 1, and landing wheel 2 is installed on fold line part two 6.

[0023] The obtuse angle between fold line part one 5 and horizontal part 4 is 144 °, and the obtuse angle between fold line part two 6 and fold line part one 5 is 149 °.

[0024] The connecting place of fold line part one 5 and horizontal part 4, the connecting place of fold line part two 6 and fold line part one 5 are all smoothly transitioned through round corners.

[0025] Fold line part two 6 is fixedly connected with wheel shaft 7, wheel shaft 7 is fixedly connected with reinforcing sheet one 8 and reinforcing sheet two 9, reinforcing sheet one 8 and reinforcing sheet two 9 are fixed on the side walls on the two sides of fold line part two 6 respectively, wheel hub bearing 10 is installed on wheel shaft 7, and landing wheel 2 is sleeved on the outside of wheel hub bearing 10.

[0026] One end of the connecting beam 3 is fixedly connected with an axle 7 on one landing gear body, the other end of the connecting beam 3 is fixedly connected with an axle 7 on the other landing gear body, a friction plate 11 is also fixedly connected with the axle 7, the friction plate 11 is arranged on the side of the landing wheel 2 and contacts the landing wheel 2, and the friction plate 11 and the connecting beam 3 are fixedly connected.

[0027] The two landing gears on the front and back sides are symmetrical to each other, and the two landing wheels 2 at the two ends of the landing gear are symmetrical to each other, so that the unmanned aerial vehicle body 1 is supported, the stability of the unmanned aerial vehicle attitude in the automatic landing process is effectively improved, the landing gear bounce amplitude when landing is reduced, and the automatic landing point precision is improved.

[0028] The two landing gears are connected and fixed through the connecting beam 3, the stability and strength of the landing gear are greatly improved through the angle design and the round corner design between the horizontal part 4, the first fold line part 5 and the second fold line part 6, the stress received by the landing gear when the unmanned aerial vehicle lands can be dispersed to a wider area, and the local stress concentration is reduced.

Claims

1. A structure of a landing gear of a ducted unmanned aerial vehicle, characterized in that, The utility model provides a kind of landing gear, including body (1), the body (1) is equipped with landing gear body, the landing gear body is placed in the front and rear sides of body (1) and is fixedly connected, the left and right ends of the landing gear body are equipped with landing wheel (2), and two landing gear bodies are fixedly connected by connecting beam (3), and the connecting beam (3) is placed in the left and right sides of body (1).

2. The structure of the landing gear of the ducted drone according to claim 1, characterized in that, The landing gear body includes horizontal part (4), the horizontal part (4) is fixedly connected with body (1), the left and right sides of the horizontal part (4) are equipped with fold line part one (5) and fold line part two (6), the fold line part one (5) is placed between horizontal part (4) and fold line part two (6), one end of the fold line part one (5) is connected with horizontal part (4), the fold line part one (5) is inclined towards the side away from body (1), the other end of the fold line part one (5) is connected with fold line part two (6), and the fold line part two (6) is inclined towards the side away from body (1), and the landing wheel (2) is installed on fold line part two (6).

3. The structure of claim 2, wherein, The obtuse angle between the fold line part one (5) and the horizontal part (4) is 140°-145°, and the obtuse angle between the fold line part two (6) and the fold line part one (5) is 145°-150°.

4. The structure of claim 2, wherein, The connection between the fold line part one (5) and the horizontal part (4) and the connection between the fold line part two (6) and the fold line part one (5) are smoothly transitioned by round corners.

5. The landing gear structure of a ducted drone according to any one of claims 2-4, characterized in that, The fold line part two (6) is fixedly connected with an axle (7), the axle (7) is fixedly connected with a reinforcing sheet one (8) and a reinforcing sheet two (9), the reinforcing sheet one (8) and the reinforcing sheet two (9) are fixed on the side walls on the left and right sides of the fold line part two (6) respectively, the axle (7) is installed with a hub bearing (10), and the landing wheel (2) is sleeved on the outside of the hub bearing (10).

6. The structure of the landing gear of the ducted drone according to claim 5, characterized in that, One end of the connecting beam (3) is fixedly connected with the axle (7) on one of the landing gear bodies, the other end of the connecting beam (3) is fixedly connected with the axle (7) on the other landing gear body, the axle (7) is further fixedly connected with a friction plate (11), the friction plate (11) is placed on the side of the landing wheel (2) and contacts the landing wheel (2), and the friction plate (11) is fixedly connected with the connecting beam (3).

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