CN213057471U

CN213057471U - Effectual aluminium alloy for aircraft of antidetonation

Info

Publication number: CN213057471U
Application number: CN202021496282.6U
Authority: CN
Inventors: 付春峰
Original assignee: Shenyang Yingpai Industrial Co ltd
Current assignee: Shenyang Yingpai Industrial Co ltd
Priority date: 2020-07-24
Filing date: 2020-07-24
Publication date: 2021-04-27
Anticipated expiration: 2030-07-24

Abstract

The utility model discloses an effectual aluminium alloy of aircraft of antidetonation, the fruit pick-up device comprises a frame body, the equal fixedly connected with buffer layer in left and right sides, top and the bottom of framework inner wall and connecting plate, the relative one side fixedly connected with carriage of buffer layer and connecting plate, the equal fixedly connected with backup pad in left and right sides, top and the bottom of carriage inner wall, the relative one side fixedly connected with stay tube of backup pad, the inner wall fixedly connected with reinforcing plate of stay tube, the relative one side fixedly connected with bracing piece of reinforcing plate, the framework includes the underframe, the fixed surface of underframe is connected with the waterproof layer. The utility model discloses possess effectual advantage of antidetonation, solved current aluminium alloy for the aircraft in the in-process that uses, the aluminium alloy is when receiving outside impact force, and the aluminium alloy is out of shape the damage easily, has reduced the buffering antidetonation effect of aluminium alloy, influences the life of aluminium alloy, has reduced the problem of aluminium alloy working strength.

Description

Effectual aluminium alloy for aircraft of antidetonation

Technical Field

The utility model relates to an aircraft technical field specifically is an effectual aluminium alloy for aircraft of antidetonation.

Background

The aircraft is an apparatus flying in the atmosphere or the space outside the atmosphere, and is divided into three types: the aircraft, spacecraft, rocket and missile are named as aircraft flying in the atmosphere, such as balloon, airship, airplane and the like, fly by the aid of air static buoyancy or air power generated by relative movement of air, most of metal materials used by the aircraft are aluminum profiles, and the aluminum profiles become main key structural materials for manufacturing the aircraft by virtue of unique advantages of small density, moderate strength, easiness in processing and forming, strong corrosion resistance, rich resources, strong recyclability and the like.

The existing aluminum profile for the aircraft is easy to deform and damage when being subjected to external impact force in the using process, so that the buffering and anti-seismic effect of the aluminum profile is reduced, the service life of the aluminum profile is influenced, and the use strength of the aluminum profile is reduced.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an effectual aluminium alloy of aircraft of antidetonation possesses the effectual advantage of antidetonation, has solved the in-process that current aluminium alloy of aircraft is using, and the aluminium alloy is when receiving outside impact force, and the aluminium alloy warp the damage easily, has reduced the buffering antidetonation effect of aluminium alloy, influences the life of aluminium alloy, has reduced the problem of aluminium alloy use strength.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides an effectual aluminium alloy of anti-seismic for aircraft, includes the framework, the equal fixedly connected with buffer layer in left and right sides, top and the bottom of framework inner wall and connecting plate, the relative one side fixedly connected with carriage of buffer layer and connecting plate, the equal fixedly connected with backup pad in left and right sides, top and the bottom of carriage inner wall, the relative one side fixedly connected with stay tube of backup pad, the inner wall fixedly connected with reinforcing plate of stay tube, the relative one side fixedly connected with bracing piece of reinforcing plate, the framework includes the underframe, the fixed surface of underframe is connected with the waterproof layer, the fixed surface of waterproof layer is connected with the wearing layer.

Preferably, the inner wall of the bottom frame is fixedly connected with the opposite side of the buffer layer and the connecting plate, and the bottom frame is made of aluminum alloy.

Preferably, the waterproof layer is made of polypropylene paint, and the wear-resistant layer is made of nickel.

Preferably, the number of the reinforcing plates is several, and the reinforcing plates are uniformly distributed on the inner wall of the support tube.

Preferably, both sides of the frame body are fixedly connected with mounting plates, and the buffer layer is made of rubber.

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

1. the utility model discloses a framework, buffer layer, connecting plate, stay tube, backup pad, reinforcing plate, bracing piece, carriage, mounting panel, underframe, waterproof layer and wearing layer's cooperation is used, has solved current aircraft aluminium alloy in the in-process that uses, and the aluminium alloy is when receiving outside impact force, and the aluminium alloy is out of shape easily and damages, has reduced the buffering antidetonation effect of aluminium alloy, influences the life of aluminium alloy, has reduced the problem of aluminium alloy working strength.

The utility model discloses a set up the mounting panel, can be convenient for install the framework, through setting up the connecting plate, can be convenient for fix the carriage, through setting up the buffer layer, can be convenient for cushion the vibrations that reduce the framework to the impact that the framework received, through setting up the carriage, can be convenient for support the buffer layer, through setting up the backup pad, can be convenient for fix the stay tube, through setting up the stay tube, can be convenient for support the carriage and avoid it to warp when receiving the impact, use through the cooperation of reinforcing plate and bracing piece, can be convenient for support the stay tube, through setting up the waterproof layer, can be convenient for prevent that the framework from infiltrating and receiving the corruption, through setting up the wearing layer, the surface hardness that can be convenient for increase the framework prevents its wearing and tearing.

Drawings

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

FIG. 2 is a top cross-sectional partial schematic view of the present invention;

fig. 3 is a cross-sectional partial view of the frame body of the present invention.

In the figure: the anti-abrasion.

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 a parts such as framework 1, buffer layer 2, connecting plate 3, stay tube 4, backup pad 5, reinforcing plate 6, bracing piece 7, carriage 8, mounting panel 9, underframe 10, waterproof layer 11 and wearing layer 12 are the parts that universal standard spare or technical field personnel know, and its structure and principle all can learn through the technical manual or learn through conventional experimental method for technical field personnel in the field.

Referring to fig. 1-3, an aircraft aluminum profile with good anti-seismic effect comprises a frame body 1, wherein both sides of the frame body 1 are fixedly connected with mounting plates 9, the frame body 1 can be conveniently mounted by arranging the mounting plates 9, the left side, the right side, the top and the bottom of the inner wall of the frame body 1 are fixedly connected with a buffer layer 2 and a connecting plate 3, the buffer layer 2 is made of rubber, the supporting frame 8 can be conveniently fixed by arranging the connecting plate 3, the buffer layer 2 can be used for buffering the impact on the frame body 1 to reduce the vibration of the frame body 1, the supporting frame 8 is fixedly connected to the side, opposite to the buffer layer 2 and the connecting plate 3, the supporting frame 8 can be used for conveniently supporting the buffer layer 2, the left side, the right side, the top and the bottom of the inner wall of the supporting frame 8 are fixedly connected with supporting plates 5, and the supporting plates 5, the opposite side of the supporting plate 5 is fixedly connected with a supporting tube 4, the supporting frame 8 can be conveniently supported to avoid deformation when being impacted by arranging the supporting tube 4, the inner wall of the supporting tube 4 is fixedly connected with a plurality of reinforcing plates 6, the reinforcing plates 6 are uniformly distributed on the inner wall of the supporting tube 4, the opposite side of the reinforcing plates 6 is fixedly connected with a supporting rod 7, the supporting tube 4 can be conveniently supported by matching the reinforcing plates 6 with the supporting rod 7, the frame body 1 comprises a bottom frame 10, the inner wall of the bottom frame 10 is fixedly connected with the opposite side of the buffer layer 2 and the connecting plate 3, the bottom frame 10 is made of aluminum alloy, the surface of the bottom frame 10 is fixedly connected with a waterproof layer 11, the waterproof layer 11 is made of polypropylene coating, the waterproof layer 11 is arranged to conveniently prevent the frame body 1 from water seepage corrosion, and the surface of the waterproof layer 11 is fixedly connected with a, the material of wearing layer 12 is nickel, through setting up wearing layer 12, the hardness of surface that can be convenient for increase framework 1 prevents its wearing and tearing, through framework 1, buffer layer 2, connecting plate 3, stay tube 4, backup pad 5, reinforcing plate 6, bracing piece 7, carriage 8, mounting panel 9, underframe 10, waterproof layer 11 and wearing layer 12's cooperation is used, the in-process of current aluminium alloy for the aircraft using has been solved, the aluminium alloy is when receiving outside impact force, the aluminium alloy is the damage of warping easily, the buffering antidetonation effect of aluminium alloy has been reduced, influence the life of aluminium alloy, the problem of aluminium alloy use strength has been reduced.

During the use, through setting up mounting panel 9, can be convenient for install framework 1, through setting up connecting plate 3, can be convenient for fix carriage 8, through setting up buffer layer 2, can be convenient for cushion the impact that framework 1 received and reduce the vibrations of framework 1, through setting up carriage 8, can be convenient for support buffer layer 2, through setting up backup pad 5, can be convenient for fix stay tube 4, through setting up stay tube 4, can be convenient for support carriage 8 and avoid it to warp when receiving the impact, use through the cooperation of reinforcing plate 6 and bracing piece 7, can be convenient for support stay tube 4, through setting up waterproof layer 11, can be convenient for prevent that framework 1 infiltration from receiving the corruption, through setting up wearing layer 12, can be convenient for increase the surface hardness of framework 1 and prevent its wearing and tearing.

In summary, the following steps: this effectual aluminium alloy for aircraft of antidetonation, through framework 1, buffer layer 2, connecting plate 3, stay tube 4, backup pad 5, reinforcing plate 6, bracing piece 7, carriage 8, mounting panel 9, underframe 10, waterproof layer 11 and wearing layer 12's cooperation is used, the in-process of current aluminium alloy for aircraft in using has been solved, the aluminium alloy is when receiving outside impact force, the aluminium alloy is out of shape the damage easily, the buffering antidetonation effect of aluminium alloy has been reduced, influence the life of aluminium alloy, the problem of aluminium alloy use strength has been reduced.

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. The utility model provides an effectual aluminium alloy for aircraft of antidetonation, includes framework (1), its characterized in that: the utility model discloses a waterproof framework, including framework (1), the equal fixedly connected with buffer layer (2) in the left and right sides, top and the equal fixedly connected with backup pad (3) in bottom of framework (1) inner wall, buffer layer (2) and the relative one side fixedly connected with carriage (8) of connecting plate (3), the equal fixedly connected with backup pad (5) in left and right sides, top and the bottom of carriage (8) inner wall, the relative one side fixedly connected with stay tube (4) in backup pad (5), the inner wall fixedly connected with reinforcing plate (6) of stay tube (4), one side fixedly connected with bracing piece (7) that reinforcing plate (6) are relative, framework (1) includes underframe (10), the fixed surface of underframe (10) is connected with waterproof layer (11), the fixed surface of waterproof layer (11) is connected with wearing layer (12).

2. The aluminum profile for the aircraft with the good anti-seismic effect according to claim 1, is characterized in that: the inner wall of underframe (10) and buffer layer (2) and connecting plate (3) opposite one side fixed connection, the material of underframe (10) is the aluminum alloy.

3. The aluminum profile for the aircraft with the good anti-seismic effect according to claim 1, is characterized in that: the waterproof layer (11) is made of polypropylene paint, and the wear-resistant layer (12) is made of nickel.

4. The aluminum profile for the aircraft with the good anti-seismic effect according to claim 1, is characterized in that: the number of the reinforcing plates (6) is a plurality, and the reinforcing plates are uniformly distributed on the inner wall of the supporting pipe (4).

5. The aluminum profile for the aircraft with the good anti-seismic effect according to claim 1, is characterized in that: the equal fixedly connected with mounting panel (9) in both sides of framework (1), the material of buffer layer (2) is rubber.