Undercarriage special for unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, in particular to a special undercarriage for an unmanned aerial vehicle, which comprises a fuselage, a main support rod, an adjusting pipe hoop and a diagonal draw bar, an undercarriage connecting piece is arranged at one end of the main supporting rod, and the undercarriage connecting piece is connected with the fuselage; the adjusting pipe hoop is arranged on the main supporting rod; one ends of the two diagonal draw bars are connected with the adjusting pipe hoop, and the other ends of the two diagonal draw bars are connected with the machine body. According to the structure, the adjusting pipe hoops are arranged on the main supporting rods, the diagonal draw bars are connected through the adjusting pipe hoops, the diagonal draw bars are connected with the fuselage, the adaptability of the diagonal draw bars is high, if the fuselage changes, the diagonal draw bars can rotate, and the mounting angle is adaptively adjusted, so that the undercarriage which is high in adaptability and more stable in structure is formed; and the fuselage is connected through the diagonal draw bars, so that stress concentration generated by the fuselage and the undercarriage is reduced, and damage to parts on the fuselage in the landing process is reduced.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the technical field of unmanned plane, especially relate to a special undercarriage of unmanned plane. BACKGROUND

[0002] The global unmanned plane undercarriage market presents the sustained growth situation in recent years, and the continuous expansion of market scale highlights the sustained growth of unmanned plane undercarriage demand, and at present, the undercarriage of domestic unmanned plane is various, has the metal bending, the combination of carbon pipe and carbon pipe connecting piece and the plastic injection, and its main working principle is to support the unmanned plane body.But the stress concentration situation can be caused to the various undercarriage structures of existing various undercarriage structures, and the parts on the body can be damaged greatly in the landing process.

[0003] Therefore, in view of the problems of weak adaptability and stress concentration with the body in the prior art, an unmanned plane special undercarriage needs to be provided. CONTENT OF THE UTILITY MODEL

[0004] The utility model provides a special undercarriage of unmanned plane for solving the problems of weak adaptability and stress concentration with the body in the prior art.

[0005] The utility model realizes by the following technical scheme: including body, main support rod, adjusting pipe hoop, inclined pull rod;

[0006] One end of the main support rod is equipped with undercarriage connecting piece, and the undercarriage connecting piece is connected to the bottom of the body.

[0007] The adjusting pipe hoop is arranged on the main support rod.

[0008] One end of two inclined pull rods is connected to the adjusting pipe hoop, and the other end of the two inclined pull rods is detachably connected to the body.

[0009] In order to better realize the utility model, further optimization is made in the above structure, and the other end of the main support rod is provided with a rubber foot pad.

[0010] In order to better realize the utility model, further optimization is made in the above structure, and a locking screw is arranged on the adjusting pipe hoop.

[0011] In order to better realize the utility model, further optimization is made in the above structure, and a rotating shaft is arranged on the adjusting pipe hoop, and the rotating shaft is hinged to one end of the inclined pull rod.

[0012] In order to better realize the utility model, further optimization is made in the above structure, and a plurality of detachable inclined pull connecting pieces are arranged on the body, a pin shaft is arranged on the inclined pull connecting piece, and the pin shaft is connected to the other end of the inclined pull rod.

[0013] In order to better realize the utility model, further optimization is made in the above structure, the number of the inclined pull rod is same as the number of the pin shaft.

[0014] In order to better realize the utility model, further optimization is made in the above structure, the number of the main support rod is multiple.

[0015] In order to better realize the utility model, further optimization is made in the above structure, the landing gear connecting piece is a straight-through connecting fastener.

[0016] Compared with the prior art, the utility model has the following beneficial effects:

[0017] The utility model provides a landing gear special for unmanned plane, including fuselage, main support rod, adjusting pipe hoop, inclined pull rod, one end of main support rod is equipped with landing gear connecting piece, landing gear connecting piece connects fuselage, adjusting pipe hoop is equipped on main support rod, one end of two inclined pull rods is connected with adjusting pipe hoop, the other end of two inclined pull rods is connected with fuselage. The above structure, through setting adjusting pipe hoop on main support rod, connecting inclined pull rod through adjusting pipe hoop, connecting fuselage through inclined pull rod, the adaptability of inclined pull rod is strong, if fuselage changes, inclined pull rod can rotate, and the installation angle is adjusted adaptively, so that the landing gear with strong adaptability and more stable structure is formed, and the fuselage is connected through the inclined pull rod, so that the stress concentration of the fuselage and the landing gear is reduced, and the damage to the parts on the fuselage in the landing process is reduced. BRIEF DESCRIPTION OF DRAWINGS

[0018] In order to more clearly illustrate the technical scheme in the embodiment of the utility model or prior art, the following will briefly introduce the drawings needed to be used in the embodiment or prior art description, and obviously, the drawings in the following description are only some embodiments of the utility model, and other drawings can be obtained by the ordinary skilled in the art without creating creative labor.

[0019] Figure 1 It is the front view of the landing gear special for unmanned plane in the utility model,

[0020] Figure 2 It is the schematic view of pin shaft and landing gear connecting piece in the utility model.

[0021] In the drawing,

[0022] 1-fuselage;2-main support rod;3-adjusting pipe hoop;4-inclined pull rod;5-landing gear connecting piece;6-rubber foot pad;7-locking screw;8-rotating shaft;9-inclined pull connecting piece;10-pin shaft. DETAILED DESCRIPTION

[0023] In order to make the purpose, technical scheme and advantages of the utility model more clear, the technical scheme of the utility model will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the utility model, not all. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor belong to the scope protected by the utility model.

[0024] In the description of the utility model, it should be explained that, unless otherwise stated, the meaning of "multiple" is two or more than two;The orientation or position relationship indicated by the terms "upper", "lower", "left", "right", "inner", "outer", "front end", "rear end", "head", "tail" and the like is based on the orientation or position relationship shown in the drawings, which is only for the convenience of describing the utility model and simplifying the description, and does not indicate or imply that the indicated device or element must have a particular orientation, be constructed and operated in a particular orientation, therefore it cannot be understood as a limitation on the utility model. In addition, the terms "first", "second", "third" and the like are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0025] In the description of the utility model, it should be explained that, unless otherwise stated, the terms "mounting", "connection", "connection" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected;It can be mechanically connected, or it can be electrically connected;It can be directly connected, or it can be indirectly connected through an intermediate medium. For those skilled in the art, the specific meaning of the above terms in the utility model can be understood according to the specific circumstances.

[0026] Embodiment 1

[0027] A special landing gear for unmanned aerial vehicle, including fuselage 1, main support rod 2, adjusting pipe clamp 3, inclined rod 4;

[0028] One end of the main support rod 2 is provided with a landing gear connecting piece 5, and the bottom of the fuselage 1 is connected with the landing gear connecting piece 5;

[0029] The adjusting pipe clamp 3 is arranged on the main support rod 2;

[0030] One end of the two inclined rods 4 is connected with the adjusting pipe clamp 3, and the other end of the two inclined rods 4 is connected with the fuselage 1.

[0031] The above structure, by setting the adjusting pipe clamp 3 on the main support rod 2, connecting the inclined pull rod 4 through the adjusting pipe clamp 3, connecting the fuselage 1 through the inclined pull rod 4, setting two inclined pull rods 4 on one main support rod 2, each inclined pull rod 4 and the main support rod 2 and the fuselage 1 form a triangular structure, and the triangular structure has stability, so that the landing gear structure is more stable, and the fuselage 1 is connected through the inclined pull rod 4, so the setting provides support for the unmanned aerial vehicle by two inclined pull rods and the main support rod, avoiding the stress concentration on the fuselage caused by the single setting of the main support rod, reducing the damage to the parts on the fuselage 1 in the landing process; and only need to add the inclined pull rod 4 to improve the stability, the structure is simple and the weight is light. By setting the adjusting pipe clamp on the main support rod, connecting the inclined pull rod through the adjusting pipe clamp, connecting the fuselage through the inclined pull rod, the adaptability of the inclined pull rod is strong, if the fuselage changes, the inclined pull rod can rotate, the installation angle is adjusted adaptively, so that the landing gear with strong adaptability and more stable structure is formed; and the fuselage is connected through the inclined pull rod, so that the stress concentration of the fuselage and the landing gear is reduced, and the damage to the parts on the fuselage in the landing process is reduced.

[0032] The other end of the above-mentioned main support rod 2 is provided with a rubber foot pad 6. The rubber foot pad 6 can buffer the vibration generated when the unmanned aerial vehicle lands, improving the buffering capacity of the fuselage 1.

[0033] The above-mentioned adjusting pipe clamp 3 is provided with a locking screw 7. The above-mentioned adjusting pipe clamp 3 can be locked by the locking screw 7, and the adjusting pipe clamp 3 can move on the main support rod 2.

[0034] The above-mentioned adjusting pipe clamp 3 is provided with a rotating shaft 8, and the above-mentioned rotating shaft 8 is connected with one end of the above-mentioned inclined pull rod 4. The above-mentioned inclined pull rod 4 can rotate around the rotating shaft 8.

[0035] The above-mentioned fuselage 1 is provided with a plurality of detachable inclined pull connecting pieces 9, the above-mentioned inclined pull connecting pieces 9 are provided with a pin shaft 10, and the above-mentioned pin shaft 10 is connected with the other end of the above-mentioned inclined pull rod 4. A plurality of detachable inclined pull connecting pieces 9 are arranged on the fuselage 1, the pin shaft 10 is arranged on the inclined pull connecting piece 9, and the other end of the inclined pull rod is connected through the pin shaft 10, so that the inclined pull rod can rotate around the pin shaft 10, and the pin shaft can be detachably connected on the above-mentioned fuselage 1, that is, the inclined pull rod can move on the main support rod 2 and the fuselage 1.

[0036] The number of the above-mentioned inclined pull rod is the same as the number of the above-mentioned pin shaft. That is, one inclined pull rod corresponds to one pin shaft. The material of the inclined pull rod is carbon fiber plate, because the carbon fiber plate has the characteristics of high tensile strength and good toughness, that is, it does not deform and is not easy to break when bending, which not only ensures the rigidity of the landing gear in all directions, but also ensures the buffering of the landing gear to the fuselage 1 in all directions.

[0037] The number of the main support rods 2 is multiple. Preferably, the number of the main support rods 2 is set according to the stability requirement of the fuselage 1, and generally the number of the main support rods 2 is six, and the main support rods 2 are arranged at the end of the bottom surface of the fuselage 1.

[0038] The landing gear connecting piece 5 is a straight-through connecting fastener, that is, one end of the straight-through connecting fastener is welded on the fuselage 1, and the main support rod is clamped in the other end of the straight-through connecting fastener.

[0039] Specifically, the unmanned aerial vehicle special landing gear comprises a fuselage, a main support rod, an adjusting pipe clamp and a diagonal rod. One end of the main support rod is provided with a landing gear connecting piece 5, and the landing gear connecting piece 5 is connected to the fuselage. The adjusting pipe clamp is arranged on the main support rod. One end of each of the two diagonal rods is connected to the adjusting pipe clamp, and the other end of each of the two diagonal rods is connected to the fuselage. The material of the diagonal rod is carbon fiber plate. That is, the adjusting pipe clamp is arranged on the main support rod, each adjusting pipe clamp is connected to two diagonal rods, the diagonal rod is connected to the fuselage, the main support rod and the fuselage are connected through the diagonal rod, a stable triangle of the diagonal rod, the fuselage and the main support rod is formed, the stability of the whole landing gear is improved, the rigidity of the fuselage and the landing gear is reduced, and the damage to the parts on the fuselage in the landing process is reduced. The rubber foot pad 6 is arranged at the end of the main support rod, the vibration generated when the unmanned aerial vehicle lands is buffered, and the buffering capacity of the fuselage is improved. The material of the diagonal rod is carbon fiber plate. Because the carbon fiber plate has the characteristics of high tensile strength, good toughness, no deformation and not easy to break when bending, the rigidity of the landing gear in one direction is ensured, and the buffering of the landing gear to the fuselage in each direction is ensured. That is, the landing gear has the advantages of reliable structure, good buffering capacity, simple structure, light weight and the like.

[0040] The above merely illustrates the specific implementation of the present application, but the protection scope of the present application is not limited to this. Any skilled person in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A drone specific landing gear characterized by: The utility model relates to a kind of aircraft, including fuselage (1), main support pole (2), adjusting pipe hoop (3), inclined pull rod (4); One end of the main support pole (2) is provided with a landing gear connecting piece (5), and the landing gear connecting piece (5) is connected to the bottom of the fuselage (1). The adjusting pipe hoop (3) is arranged on the main support pole (2). One end of the two inclined pull rods (4) is connected to the adjusting pipe hoop (3), and the other end of the two inclined pull rods (4) is detachably connected to the fuselage (1).

2. The landing gear for drones according to claim 1, characterized in that: The other end of the main support pole (2) is provided with a rubber foot pad (6).

3. The landing gear according to claim 2, wherein: The adjusting pipe hoop (3) is provided with a locking screw (7).

4. The landing gear according to claim 3, wherein: The adjusting pipe hoop (3) is provided with a rotating shaft (8), and the rotating shaft (8) is hinged to one end of the inclined pull rod (4).

5. The landing gear for drones according to any one of claims 1-4, characterized in that: The fuselage (1) is provided with a plurality of detachable inclined pull connecting pieces (9), the inclined pull connecting piece (9) is provided with a pin shaft (10), and the pin shaft (10) is hinged to the other end of the inclined pull rod (4).

6. The landing gear for drones according to claim 5, characterized in that: The number of the main support pole (2) is multiple.

7. The landing gear according to claim 6, characterized in that The landing gear connecting piece (5) is a straight-through connecting fastener.

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