CN214493321U

CN214493321U - Aircraft casing

Info

Publication number: CN214493321U
Application number: CN202120324479.XU
Authority: CN
Inventors: 丁晓锋; 胡源; 张海燕; 高鹏飞; 王党跃
Original assignee: Luoyang Qirui Machinery Technology Co ltd
Current assignee: Luoyang Qirui Machinery Technology Co ltd
Priority date: 2021-02-04
Filing date: 2021-02-04
Publication date: 2021-10-26
Anticipated expiration: 2031-02-04

Abstract

The utility model discloses an aircraft casing relates to aircraft technical field, which comprises a housin body, the casing body comprises up end, casing main part and lower terminal surface, a plurality of first round holes have all been seted up on up end and the lower terminal surface, first recess, second recess and third recess have down been seted up in proper order from last in the first section of casing main part, the fourth recess has been seted up in the second section of casing main part, a plurality of second round holes have all been seted up in first recess, second recess, third recess and the fourth recess, multiunit third round hole, multiunit have been seted up at the middle part of casing main part the third round hole all is located the downside of third recess, a plurality of through-holes have been seted up to the bottom of casing main part, and is a plurality of the through-hole all is located the downside of fourth recess. The utility model has simple structure, less requirement of processing procedures, convenient processing, improved production efficiency and suitability for batch production; can make the combination between each part tighter, and the installation and the dismantlement are convenient.

Description

Aircraft casing

Technical Field

The utility model relates to an aircraft technical field, concretely relates to aircraft casing.

Background

An aircraft is an instrumental flying object made by humans, capable of flying off the ground, flying in space and controlled by humans, flying in the atmosphere or in the extraterrestrial space (space). Aircraft fall into 3 categories: aircraft, spacecraft, rockets, and missiles. Flying in the atmosphere is called aircraft and flying in space is called spacecraft.

The existing aircraft shell is complex in structure, inconvenient to process and inconvenient to install and disassemble each part.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide an aircraft casing solves at least one problem that proposes in the above-mentioned background art.

In order to solve the technical problem, the utility model adopts the following technical scheme:

the utility model provides an aircraft casing, includes the casing body, the casing body comprises up end, casing main part and lower terminal surface, a plurality of first round holes have all been seted up on up end and the lower terminal surface, first recess, second recess and third recess have down been seted up in proper order from last first section of casing main part, the fourth recess has been seted up to the second half of casing main part, a plurality of second round holes have all been seted up in first recess, second recess, third recess and the fourth recess, multiunit third round hole, multiunit have been seted up at the middle part of casing main part the third round hole all is located the downside of third recess, a plurality of through-holes have been seted up to the bottom of casing main part, and is a plurality of the through-hole all is located the downside of fourth recess.

Optionally, the casing body is long-tube-shaped.

Optionally, the upper end surface is located at the top end of the shell body, and the lower end surface is located at the bottom end of the shell body.

Optionally, the first round holes are distributed in an annular array around the axis of the shell body.

Optionally, the plurality of groups of third round holes are distributed in an annular array around the axial lead of the shell body, and the number of the third round holes in each group is ten.

Optionally, the through holes are distributed in an annular array around the axis of the shell body, and a plurality of second round holes are formed in two sides of each through hole.

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

1. the utility model has simple structure, less requirement of processing procedures, convenient processing, improved production efficiency and suitability for batch production; can make the combination between each part tighter, and the installation and the dismantlement are convenient.

2. The utility model is provided with the upper end face, which is convenient for installing the antenna housing; the auxiliary hanger is convenient to install by arranging the first groove; the third groove is arranged, so that the front hanger is convenient to mount; the fourth groove is arranged, so that the hanging is convenient after the installation; the through hole is arranged, so that the control surface is convenient to install; the tail cabin is convenient to install by arranging the lower end face; through being provided with the third round hole, the rib is easy to assemble.

Drawings

Fig. 1 is a schematic view of the present invention.

Fig. 2 is a left side view of the present invention.

Fig. 3 is a perspective view of the present invention.

In the figure: 1. an upper end surface; 2. a housing main body; 3. a lower end face; 4. a first circular hole; 5. a first groove; 6. a second groove; 7. a third groove; 8. a fourth groove; 9. a second circular hole; 10. a third circular hole; 11. and a through hole.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Referring to fig. 1-3, the present invention provides the following technical solutions:

an aircraft shell comprises a shell body, wherein 30CrMnSiA stainless steel is selected as a material, the shell body is composed of an upper end face 1, a shell main body 2 and a lower end face 3, the shell body is in a long tube shape, the upper end face 1 is positioned at the top end of the shell main body 2, an antenna housing is convenient to mount, the lower end face 3 is positioned at the bottom end of the shell main body 2, a tail cabin is convenient to mount, a plurality of first round holes 4 are formed in the upper end face 1 and the lower end face 3, and the plurality of first round holes 4 are distributed in an annular array around the axial lead of the shell body; the upper half section of the shell body 2 is sequentially provided with a first groove 5, a second groove 6 and a third groove 7 from top to bottom, and the first groove 5 is arranged, so that the auxiliary hanging is convenient to install; the third groove 7 is arranged, so that the front hanger is convenient to mount; the lower half section of the shell main body 2 is provided with a fourth groove 8, the shell is hung after being conveniently installed, the first groove 5, the second groove 6, the third groove 7 and the fourth groove 8 are internally provided with a plurality of second round holes 9, the middle part of the shell main body 2 is provided with a plurality of groups of third round holes 10 which are convenient for installing wing ribs, the plurality of groups of third round holes 10 are all positioned at the lower side of the third groove 7, the plurality of groups of third round holes 10 are distributed in an annular array around the axial lead of the shell body, the number of each group of third round holes 10 is ten, the bottom end of the shell main body 2 is provided with a plurality of through holes 11 which are convenient for installing a control surface, the plurality of through holes 11 are all positioned at the lower side of the fourth groove 8, the plurality of through holes 11 are distributed in an annular array around the axial lead of the shell body, and two sides of each through hole 11 are provided with a plurality of second round holes 9; the structure is simple, the requirement on processing procedures is less, the processing is convenient, the production efficiency is improved, and the method is suitable for batch production; can make the combination between each part tighter, and the installation and the dismantlement are convenient.

Reference throughout this specification to "one embodiment," "another embodiment," "an embodiment," "a preferred embodiment," or the like, means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment described generally in this application. The appearances of the same phrase in various places in the specification are not necessarily all referring to the same embodiment. Further, when a particular feature, structure, or characteristic is described in connection with any embodiment, it is submitted that it is within the scope of the invention to effect such feature, structure, or characteristic in connection with other embodiments.

Although the invention has been described herein with reference to a number of illustrative embodiments thereof, it should be understood that numerous other modifications and embodiments can be devised by those skilled in the art that will fall within the spirit and scope of the principles of this invention. More specifically, various variations and modifications are possible in the component parts and/or arrangements of the subject combination arrangement within the scope of the disclosure, the drawings and the appended claims. In addition to variations and modifications in the component parts and/or arrangements, other uses will also be apparent to those skilled in the art.

Claims

1. An aircraft casing comprising a casing body, characterized in that: the shell body consists of an upper end surface (1), a shell main body (2) and a lower end surface (3), a plurality of first round holes (4) are respectively arranged on the upper end surface (1) and the lower end surface (3), the upper half section of the shell body (2) is sequentially provided with a first groove (5), a second groove (6) and a third groove (7) from top to bottom, a fourth groove (8) is arranged at the lower half section of the shell body (2), a plurality of second round holes (9) are arranged in the first groove (5), the second groove (6), the third groove (7) and the fourth groove (8), a plurality of groups of third round holes (10) are arranged in the middle of the shell body (2), the plurality of groups of third round holes (10) are all positioned at the lower side of the third groove (7), a plurality of through-holes (11) have been seted up to the bottom of casing main part (2), and is a plurality of through-hole (11) all are located the downside of fourth recess (8).

2. The aircraft housing of claim 1, wherein:

the shell body is in a long tube shape.

3. The aircraft housing of claim 1, wherein:

the upper end face (1) is located at the top end of the shell body (2), and the lower end face (3) is located at the bottom end of the shell body (2).

4. The aircraft housing of claim 1, wherein:

the first round holes (4) are distributed in an annular array around the axial lead of the shell body.

5. The aircraft housing of claim 1, wherein:

the multiple groups of third round holes (10) are distributed in an annular array around the axial lead of the shell body, and the number of the third round holes (10) in each group is ten.

6. The aircraft housing of claim 1, wherein:

the through holes (11) are distributed in an annular array around the axis of the shell body, and a plurality of second round holes (9) are formed in two sides of each through hole (11).