CN210191808U

CN210191808U - Aircraft with buffering undercarriage

Info

Publication number: CN210191808U
Application number: CN201920862326.3U
Authority: CN
Inventors: Xu Sun; 孙旭; Peng Wu; 吴鹏; Shuang Wu; 吴双
Original assignee: Chengdu Nei Sheng Technology Co Ltd
Current assignee: Chengdu Nei Sheng Technology Co Ltd
Priority date: 2019-06-10
Filing date: 2019-06-10
Publication date: 2020-03-27
Anticipated expiration: 2029-06-10

Abstract

The utility model discloses an aircraft that possesses buffering undercarriage, including unmanned aerial vehicle, the equal fixedly connected with support in both sides around the unmanned aerial vehicle bottom, the equal fixedly connected with montant in both sides of support bottom, the bottom cover of montant is equipped with the sleeve pipe, the bottom fixedly connected with limiting plate of montant, the bottom of limiting plate is provided with first spring, the bottom of first spring and the bottom contact of cover intraductal chamber, fixedly connected with fixed plate between the bottom of two relative one sides of sleeve pipe around, the first link block of bottom fixedly connected with of fixed plate. The utility model discloses a cooperation that sets up unmanned aerial vehicle, support, sleeve pipe, second spring, bottom plate, montant, limiting plate, first spring, fixed plate, second connecting block, first connecting block, rubber shock pad, opening, pivot and rubber support piece is used, has solved the problem that current partial aircraft undercarriage does not possess buffer function, and this aircraft possesses buffer function's advantage.

Description

Aircraft with buffering undercarriage

Technical Field

The utility model relates to an aircraft technical field specifically is an aircraft that possesses buffering undercarriage.

Background

An aircraft is an apparatus that flies in or out of the atmosphere. Aircraft fall into 3 categories: aircraft, spacecraft, rockets, and missiles. Flying in the atmosphere is referred to as an aircraft, such as a balloon, airship, airplane, etc. They fly by the static buoyancy of air or the aerodynamic force generated by the relative movement of air. Flying in space is called a spacecraft, such as an artificial earth satellite, a manned spacecraft, a space probe, a space shuttle and the like. They obtain the necessary speed to enter space under the drive of carrier rocket, then make orbit motion similar to celestial body by means of inertia, and are the apparatus flyer which is made by human body, can fly off ground, can fly in space and can be controlled by human body and can fly in the atmosphere or space outside the atmosphere. Flying in the atmosphere is called aircraft and flying in space is called spacecraft.

Along with the continuous development progress of society, the use of aircraft is more extensive, and wherein unmanned aerial vehicle also is one kind of aircraft, for convenient unmanned aerial vehicle goes up and down, consequently unmanned aerial vehicle's bottom all can install the undercarriage additional, but current for the unmanned aerial vehicle undercarriage do not possess the function of shock attenuation buffering, the impact force that brings when descending can accelerate unmanned aerial vehicle's damage.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an aircraft that possesses buffering undercarriage possesses buffer function's advantage, has solved current partial aircraft undercarriage and has not possessed buffer function's problem.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an aircraft that possesses buffering undercarriage, includes unmanned aerial vehicle, the equal fixedly connected with support in both sides around the unmanned aerial vehicle bottom, the equal fixedly connected with montant in both sides of support bottom, the bottom cover of montant is equipped with the sleeve pipe, the bottom fixedly connected with limiting plate of montant, the bottom of limiting plate is provided with first spring, the bottom of first spring and the bottom contact of sleeve pipe inner chamber, fixedly connected with fixed plate between the bottom of two relative one sides of sleeve pipe around, the first connecting block of bottom fixedly connected with of fixed plate, the bottom swing joint of first connecting block has the second connecting block, the bottom fixedly connected with bottom plate of second connecting block, the equal fixedly connected with second spring in both sides around the bottom plate top, the top and the sleeve pipe fixed connection of second spring.

Preferably, the top of the sleeve is provided with an opening, and the opening is matched with the vertical rod for use.

Preferably, the bottom of the bottom plate is fixedly connected with a rubber shock pad, and an inner cavity of the rubber shock pad is fixedly connected with a rubber supporting block.

Preferably, both sides of the second connecting block are fixedly connected with a shaft pin, and one end of the shaft pin penetrates through the first connecting block and is movably connected with the first connecting block.

Preferably, the limiting plate is positioned in the inner cavity of the cannula, and the surface of the limiting plate is in contact with the inner wall of the cannula.

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

1. the utility model discloses a cooperation that sets up unmanned aerial vehicle, support, sleeve pipe, second spring, bottom plate, montant, limiting plate, first spring, fixed plate, second connecting block, first connecting block, rubber shock pad, opening, pivot and rubber support piece is used, has solved the problem that current partial aircraft undercarriage does not possess buffer function, and this aircraft possesses buffer function's advantage, is worth promoting.

2. The utility model discloses a set up rubber shock pad and rubber supporting shoe, increased the shock attenuation effect of this aircraft undercarriage, through setting up the opening, make things convenient for sleeve pipe and montant cooperation to use, through setting up the pivot, make things convenient for first connecting block and second connecting block swing joint, through setting up the limiting plate, can avoid the sleeve pipe to break away from the surface of montant.

Drawings

FIG. 1 is a schematic structural view of the present invention;

FIG. 2 is a sectional view of the present invention in partial structure;

FIG. 3 is a right side view of the partial structure of the present invention;

fig. 4 is a sectional view of the sleeve of the present invention;

fig. 5 is a cross-sectional view of the rubber shock pad of the present invention.

In the figure: 1 unmanned aerial vehicle, 2 supports, 3 sleeve pipes, 4 second springs, 5 bottom plates, 6 montants, 7 limiting plates, 8 first springs, 9 fixed plates, 10 second connecting blocks, 11 first connecting blocks, 12 rubber shock pads, 13 openings, 14 pivot, 15 rubber supporting blocks.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element to be referred must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted", "provided", "connected", and the like are to be construed broadly, such as "connected", which may be 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 meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

The utility model provides an unmanned aerial vehicle 1, support 2, sleeve pipe 3, second spring 4, bottom plate 5, montant 6, limiting plate 7, first spring 8, fixed plate 9, second connecting block 10, first connecting block 11, rubber shock pad 12, opening 13, pivot 14 and parts such as rubber supporting shoe 15 are general standard or the part that technical staff in the field knows, and its structure and principle all can learn through the technical manual or learn through conventional experimental method for technical staff in the field.

Referring to fig. 1-5, an aircraft with a buffering undercarriage comprises an unmanned aerial vehicle 1, wherein a support 2 is fixedly connected to the front side and the rear side of the bottom of the unmanned aerial vehicle 1, a vertical rod 6 is fixedly connected to both sides of the bottom of the support 2, a sleeve 3 is sleeved at the bottom of the vertical rod 6, a limiting plate 7 is fixedly connected to the bottom of the vertical rod 6, a first spring 8 is arranged at the bottom of the limiting plate 7, the bottom of the first spring 8 is in contact with the bottom of an inner cavity of the sleeve 3, a fixing plate 9 is fixedly connected between the bottoms of the opposite sides of the front sleeve 3 and the rear sleeve 3, a first connecting block 11 is fixedly connected to the bottom of the fixing plate 9, a second connecting block 10 is movably connected to the bottom of the first connecting block 11, a bottom plate 5 is fixedly connected to the bottom of the second connecting block 10, second springs 4;

the top of the sleeve 3 is provided with an opening 13, the opening 13 is matched with the vertical rod 6 for use, the bottom of the bottom plate 5 is fixedly connected with a rubber shock absorption pad 12, an inner cavity of the rubber shock absorption pad 12 is fixedly connected with a rubber supporting block 15, two sides of the second connecting block 10 are both fixedly connected with a shaft pin 14, one end of the shaft pin 14 penetrates through the first connecting block 11 and is movably connected with the first connecting block 11, the limiting plate 7 is positioned in the inner cavity of the sleeve 3, and the surface of the limiting plate 7 is in contact with the inner wall of the sleeve 3;

through setting up rubber shock pad 12 and rubber support block 15, increased the shock attenuation effect of this aircraft undercarriage, through setting up opening 13, make things convenient for sleeve pipe 3 and montant 6 cooperation to use, through setting up pivot 14, make things convenient for first connecting block 11 and second connecting block 10 swing joint, through setting up limiting plate 7, can avoid sleeve pipe 3 to break away from the surface of montant 6.

During the use, unmanned aerial vehicle 1 contacts the back with ground when descending, the impact force that causes drives limiting plate 7 through montant 6 and descends and extrude first spring 8, first spring 8 plays the effect of shock attenuation buffering, simultaneously because the earth's surface unevenness, the unsmooth impact force interact when unmanned aerial vehicle 1 descends of ground can promote the both ends of bottom plate 5 and remove, bottom plate 5 is the slight rotary motion in situ around first connecting block 11 through second connecting block 10, bottom plate 5 extrudes the in-process of second spring 4, second spring 4 plays the effect of shock attenuation buffering.

In summary, the following steps: this aircraft that possesses buffering undercarriage, through the cooperation that sets up unmanned aerial vehicle 1, support 2, sleeve pipe 3, second spring 4, bottom plate 5, montant 6, limiting plate 7, first spring 8, fixed plate 9, second connecting block 10, first connecting block 11, rubber shock pad 12, opening 13, pivot 14 and rubber supporting shoe 15, solved current partial aircraft undercarriage and did not possess the problem of buffer function.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. An aircraft that possesses buffering undercarriage, includes unmanned aerial vehicle (1), its characterized in that: the front side and the rear side of the bottom of the unmanned aerial vehicle (1) are both fixedly connected with a support (2), both sides of the bottom of the support (2) are both fixedly connected with a vertical rod (6), the bottom of the vertical rod (6) is sleeved with a sleeve (3), the bottom of the vertical rod (6) is fixedly connected with a limiting plate (7), the bottom of the limiting plate (7) is provided with a first spring (8), the bottom of the first spring (8) is contacted with the bottom of the inner cavity of the sleeve (3), a fixing plate (9) is fixedly connected between the bottoms of the opposite sides of the front sleeve and the rear sleeve (3), the bottom of the fixing plate (9) is fixedly connected with a first connecting block (11), the bottom of the first connecting block (11) is movably connected with a second connecting block (10), the bottom of the second connecting block (10) is fixedly connected with a bottom plate (5), and both sides of the top of the bottom, the top of the second spring (4) is fixedly connected with the sleeve (3).

2. The aircraft of claim 1, wherein the landing gear comprises: an opening (13) is formed in the top of the sleeve (3), and the opening (13) is matched with the vertical rod (6) for use.

3. The aircraft of claim 1, wherein the landing gear comprises: the bottom of the bottom plate (5) is fixedly connected with a rubber shock absorption pad (12), and an inner cavity of the rubber shock absorption pad (12) is fixedly connected with a rubber supporting block (15).

4. The aircraft of claim 1, wherein the landing gear comprises: the two sides of the second connecting block (10) are fixedly connected with shaft pins (14), and one ends of the shaft pins (14) penetrate through the first connecting block (11) and are movably connected with the first connecting block (11).

5. The aircraft of claim 1, wherein the landing gear comprises: the limiting plate (7) is positioned in the inner cavity of the sleeve (3), and the surface of the limiting plate (7) is in contact with the inner wall of the sleeve (3).