阅读说明：本技术 一种无人机起落架转轴安装结构及安装方法 (Unmanned aerial vehicle undercarriage rotating shaft mounting structure and mounting method ) 是由 田佳杰 冯熙 任杰 郑华 于 2020-05-15 设计创作，主要内容包括：一种无人机起落架转轴安装结构及安装方法,涉及飞机起落架领域,在起落架转轴安装到机体之间设置了安装耳片,在安装耳片外侧和起落架转轴对应位置设置了对应的限位面,并且在起落架转轴外侧的端帽上安装了螺丝固定结构进一步将起落架转轴限位,限制了起落架转轴的轴向移动和周向转动,本方案结构简单,安装所需操作空间小,不需要在转轴上打孔,不会影响起落架转轴的强度,可以很好地应用在小型飞机、无人机或其他飞行器上。(The utility model provides an unmanned aerial vehicle undercarriage pivot mounting structure and mounting method, relate to the aircraft undercarriage field, set up the installation auricle between undercarriage pivot installation organism, the corresponding spacing face has been set up with undercarriage pivot corresponding position in the installation auricle outside, and it is further spacing with the undercarriage pivot to have installed screw fixation structure on the end cap in the undercarriage pivot outside, the axial displacement and the circumferential direction of undercarriage pivot have been restricted, this scheme simple structure, the required operating space of installation is little, need not punch in the pivot, can not influence the intensity of undercarriage pivot, can use well in the small-size aircraft, unmanned aerial vehicle or other aircrafts.)

1. The utility model provides an unmanned aerial vehicle undercarriage pivot mounting structure which characterized in that: the mounting structure comprises an undercarriage rotating shaft (1), a mounting lug (2), a mounting bushing (3) and a screw fixing structure (4), wherein the mounting bushing (3) is arranged on the inner side of the mounting lug (2), a shaft body (101) of the undercarriage rotating shaft (1) penetrates through a mounting hole (201) of the mounting lug (2) and a sleeve hole (301) of the mounting bushing (3), a shaft limiting surface (5) is arranged on an end cap (102) of the undercarriage rotating shaft (1), the outer end of the mounting hole (201) of the mounting lug (2) is adapted to the position of the shaft limiting surface (5) and is provided with a lug limiting surface (6), and the screw fixing structure (4) is arranged on the end cap (102) of the undercarriage rotating shaft (1).

2. The unmanned aerial vehicle landing gear pivot mounting structure of claim 1, characterized in that: the screw fixing structure (4) comprises a bolt (401) and a nut (402), a screw rod (403) of the bolt (401) penetrates through an end cap (102) of the landing gear rotating shaft (1) and an outer end face or lug limiting face (13) of the mounting lug (2), and the nut (402) is fixed on the screw rod (403).

3. The unmanned aerial vehicle landing gear pivot mounting structure of claim 2, characterized in that: the screw fixing structure (4) further comprises a cotter pin (404), and a through hole (405) which is suitable for the cotter pin (404) is formed in the tail end of the screw rod (401) of the bolt (401).

4. An unmanned aerial vehicle landing gear pivot mounting structure of claim 2 or 3, characterized in that: the screw fixation structure further includes a washer (406).

5. The unmanned aerial vehicle landing gear pivot mounting structure of claim 1, characterized in that: and a gap adjusting gasket (7) is arranged between the mounting lug (2) and the mounting bush (3).

6. The unmanned aerial vehicle landing gear pivot mounting structure of claim 1, characterized in that: a joint bearing (8) is arranged in a sleeve hole (301) of the mounting bushing (3), an outer ring of the joint bearing (8) is fixed on the sleeve hole (301) of the mounting bushing (3), and a shaft body (101) of the undercarriage rotating shaft penetrates through the inner ring of the joint bearing (8).

7. The unmanned aerial vehicle landing gear pivot mounting structure of claim 1, characterized in that: and a transverse limiting groove A (9) is formed on the lug limiting surface (6) at the outer side of the mounting lug (2).

8. The unmanned aerial vehicle landing gear pivot mounting structure of claim 7, characterized in that: and a transverse limiting groove B (10) is arranged on the shaft limiting surface (5) of the end cap (102) of the landing gear rotating shaft (1).

9. The unmanned aerial vehicle landing gear pivot mounting structure of claim 8, characterized in that: the limiting groove A (9) and the limiting groove B (10) are correspondingly matched, and the screw fixing structure (4) penetrates through and is fixed on the matched limiting groove A (9) and the matched limiting groove B (10).

10. An unmanned aerial vehicle landing gear rotating shaft mounting method is based on the unmanned aerial vehicle landing gear rotating shaft mounting structure as claimed in any one of claims 1 to 9, and is characterized in that: the undercarriage rotating shaft (1) sequentially penetrates through a mounting hole (201) of a mounting lug (2) and a sleeve hole (301) of a mounting bushing (3) from the outer side, a shaft limiting face (5) of an end cap (102) of the undercarriage rotating shaft (1) and a lug limiting face (6) of the mounting lug (2) are correspondingly placed, and the undercarriage rotating shaft (1) is fixed by a screw fixing structure (4) on the end cap (102) of the undercarriage rotating shaft (1) so that the undercarriage rotating shaft (1) cannot axially move and circumferentially rotate.

Technical Field

The invention relates to the field of aircraft landing gears, in particular to an unmanned aerial vehicle landing gear rotating shaft mounting structure and a mounting method.

Background

Landing gear (underlanding) is an attachment device for supporting an aircraft under the aircraft for takeoff, landing or ground (or surface) taxiing and for ground (or surface) movement. The landing gear is the only part for supporting the whole airplane, so that the landing gear is an integral part of the airplane; without it, the aircraft cannot move on the ground. After the aircraft takes off, the landing gear may be selectively retracted depending on the aircraft performance. In order to meet the requirements of take-off, landing and running of the airplane and ground taxiing, the lowest end of the landing gear is provided with an airplane wheel with a pneumatic tire. In order to shorten the landing and running distance, the wheels are provided with brakes or automatic brake devices. In addition, the device also comprises a bearing part, a shock absorber (a common bearing strut is used as an outer cylinder of the shock absorber), a retraction mechanism, a front wheel shimmy damper, a turning control mechanism and the like.

The landing gear rotating shaft is an important force bearing part for installing the landing gear on an airplane body, and in order to limit axial movement and circumferential rotation of the rotating shaft, the existing airplane landing gear rotating shaft is installed in a mode of fixing the rotating shaft through a bolt type bolt. To small-size unmanned aerial vehicle, the pivot diameter is less and undercarriage installation operating space is very limited, and the mode of bolt formula bolt fastening pivot on the one hand needs to punch in the pivot and has greatly weakened undercarriage pivot intensity, and on the other hand installs the required operating space great.

Disclosure of Invention

The invention aims to: the utility model provides an unmanned aerial vehicle undercarriage pivot mounting structure and mounting method, set up the installation auricle between the organism is installed in the undercarriage pivot, set up corresponding spacing face in the installation auricle outside and undercarriage pivot corresponding position, and it is further spacing with the undercarriage pivot to have installed screw fixation structure on the end cap in the undercarriage pivot outside, the axial displacement and the circumferential direction of undercarriage pivot have been restricted, this scheme simple structure, the required operating space of installation is little, need not punch in the pivot, can use well in the small-size aircraft, unmanned aerial vehicle or other aircrafts, the problem is solved.

The technical scheme adopted by the invention is as follows:

the utility model provides an unmanned aerial vehicle undercarriage pivot mounting structure, mounting structure includes undercarriage pivot, installation auricle, installation bush and screw fixation structure, the installation bush sets up in installation auricle inboard, and the axis body of undercarriage pivot passes the mounting hole of installation auricle and the trepanning of installation bush, is provided with the spacing face of axle on the end cap of undercarriage pivot, the position that the outer end adaptation axle of the mounting hole of installation auricle was spacing face has the spacing face of auricle, screw fixation structure installs on the end cap of undercarriage pivot.

In order to better implement the scheme, further, the screw fixing structure comprises a bolt and a nut, a screw rod of the bolt penetrates through an end cap of the undercarriage rotating shaft and an external end face of the mounting lug or a lug limiting face, and the nut is fixed on the screw rod.

In order to better implement the scheme, further, the screw fixing structure further comprises a cotter pin, and a through hole adapted to the cotter pin is formed at the tail end of the screw rod of the bolt.

In order to better implement the scheme, further, the screw fixing structure further comprises a washer.

In order to better implement the scheme, a gap adjusting gasket is further arranged between the mounting lug and the mounting bushing.

In order to better realize the scheme, a joint bearing is further arranged in a sleeve hole of the mounting bush, an outer ring of the joint bearing is fixed on the sleeve hole of the mounting bush, and a shaft body of the undercarriage rotating shaft penetrates through an inner ring of the joint bearing.

In order to better implement the scheme, a transverse limiting groove a is further arranged on the lug limiting surface on the outer side of the mounting lug.

In order to better implement the scheme, further, a transverse limiting groove B is formed in the shaft limiting surface of the undercarriage rotating shaft end cap

In order to better realize the scheme, further, the limiting groove A and the limiting groove B are correspondingly matched, and the screw fixing structure penetrates through and is fixed on the matched limiting groove A and the matched limiting groove B.

The mounting method of the landing gear rotating shaft of the unmanned aerial vehicle is based on the landing gear rotating shaft mounting structure of the unmanned aerial vehicle, the landing gear rotating shaft sequentially penetrates through the mounting hole for mounting the lug and the sleeve hole for mounting the bushing from the outer side, the shaft limiting surface of the landing gear rotating shaft end cap and the lug limiting surface for mounting the lug are correspondingly placed, and the screw fixing structure is mounted on the landing gear rotating shaft end cap to fix the landing gear rotating shaft so that the landing gear rotating shaft cannot axially move and circumferentially rotate.

In order to overcome the defects of the prior art, under the condition of not changing the function and the performance of a landing gear rotating shaft, the scheme provides a landing gear rotating shaft mounting structure and a mounting method of an unmanned aerial vehicle, the hole in the center of the landing gear rotating shaft is eliminated for mounting a bolt, the problem that the strength of the landing gear rotating shaft is weakened because the landing gear rotating shaft of a small aircraft is small and the hole is formed in the landing gear rotating shaft for limiting the landing gear rotating shaft is solved, specifically, an end cap is added at one end of the landing gear rotating shaft, one end of a shaft body without the end cap is inwards sequentially arranged through a mounting hole for mounting a lug piece and a sleeve hole for mounting a bush in the mounting process, the landing gear rotating shaft is limited by the end cap, specifically, the end cap is generally made into a circular cut-off part to be a shaft limiting surface, and a lug piece limiting, the axle limiting surface and the lug limiting surface are mutually matched, when the undercarriage rotating shaft moves in a circumferential direction, the end cap of the undercarriage rotating shaft is limited, and further the circumferential direction of the undercarriage rotating shaft is limited, in addition, a limiting groove is arranged at the position where the end cap contacts with the outer side of the mounting lug, specifically, a limiting groove A arranged on the lug limiting surface and a limiting groove B arranged on the axle limiting surface are mutually matched to form a complete limiting groove, a screw fixing structure is arranged in the limiting groove, the screw fixing structure is a bolt and a nut, the screw rod of the bolt is inserted into the limiting groove formed by the limiting groove A and the limiting groove B, and then the nut is screwed on the tail end of the screw rod, so that the circumferential direction of the undercarriage rotating shaft can be further limited, the axial movement of the undercarriage rotating shaft can also be limited, in order to avoid the nut from sliding off, when the nut is further arranged on the screw rod, when the screw fixing structure is arranged outside the nut, the nut is screwed, the cotter pin is inserted into the through hole, and a washer can be added to avoid the nut damaging the components, meanwhile, the scheme can further arrange a gap adjusting gasket which can adjust the gap between the mounting lug and the mounting bush, and the joint bearing in the mounting bush sleeve hole also avoids the friction between the undercarriage rotating shaft and the mounting bush from damaging the mounting bush, the scheme has simple structure, small operation space required by mounting, and no need of punching on the rotating shaft, can use well on small-size aircraft, unmanned aerial vehicle or other aircraft, it is very limited to have solved the less and undercarriage installation operating space of small-size aircraft pivot diameter, and the mode of bolt formula bolt fastening pivot on the one hand needs punch in the pivot and has greatly weakened undercarriage pivot intensity, the great problem in the required operating space of on the other hand installation.

In summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:

1. according to the landing gear rotating shaft mounting structure of the unmanned aerial vehicle, the mounting lug is arranged between the landing gear rotating shaft and the landing gear rotating shaft mounting body, the corresponding limiting surface is arranged at the outer side of the mounting lug and at the position corresponding to the landing gear rotating shaft, and the screw fixing structure is arranged on the end cap at the outer side of the landing gear rotating shaft to further limit the landing gear rotating shaft, so that the axial movement and the circumferential rotation of the landing gear rotating shaft are limited, holes do not need to be drilled on the rotating shaft, the strength of the landing gear rotating shaft cannot be influenced, and the landing gear rotating shaft mounting structure can be well applied to;

2. according to the unmanned aerial vehicle undercarriage rotating shaft mounting structure, the mounting lug is arranged between the undercarriage rotating shaft and the body, the corresponding limiting surface is arranged at the position, corresponding to the undercarriage rotating shaft, outside the mounting lug, and the screw fixing structure is arranged on the end cap outside the undercarriage rotating shaft to further limit the undercarriage rotating shaft, so that the axial movement and circumferential rotation of the undercarriage rotating shaft are limited, the structure is simple, and the space required by mounting is small;

3. according to the unmanned aerial vehicle undercarriage rotating shaft mounting method, based on the unmanned aerial vehicle undercarriage rotating shaft mounting structure, the undercarriage rotating shaft is mounted on the aircraft adopting the mounting structure, the mounting steps are simple, and the structure after mounting can well limit the axial movement and circumferential rotation of the undercarriage rotating shaft.

Drawings

In order to more clearly illustrate the technical solution, the drawings needed to be used in the embodiments are briefly described below, and it should be understood that, for those skilled in the art, other related drawings can be obtained according to the drawings without creative efforts, wherein:

FIG. 1 is an overall installation configuration of the present invention;

FIG. 2 is a cross-sectional view of the overall structure of the present invention;

FIG. 3 is an exploded view of the overall structure of the present invention;

FIG. 4 is an exploded view of the integral screw retaining structure of the present invention;

FIG. 5 is a schematic view of the structure of the landing gear shaft of the present invention;

in the figure, 1-landing gear rotating shaft, 101-shaft body, 102-end cap, 2-mounting lug, 201-mounting hole, 3-mounting bushing, 301-trepanning hole, 4-screw fixing structure, 401-bolt, 402-nut, 403-screw, 404-split pin, 405-through hole, 406-gasket, 5-shaft limiting surface, 6-lug limiting surface, 7-gap adjusting gasket, 8-joint bearing, 9-limiting groove A and 10-limiting groove B.

Detailed Description

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and therefore should not be considered as a limitation to the scope of protection. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

The present invention will be described in detail with reference to fig. 1 to 5.