CN214648981U

CN214648981U - Stable form aircraft combination casing

Info

Publication number: CN214648981U
Application number: CN202120991984.XU
Authority: CN
Inventors: 张春; 李军
Original assignee: Chengdu Zhengshan Machinery Manufacturing Co ltd
Current assignee: Chengdu Zhengshan Machinery Manufacturing Co ltd
Priority date: 2021-05-11
Filing date: 2021-05-11
Publication date: 2021-11-09
Anticipated expiration: 2031-05-11

Abstract

The utility model discloses a stable form aircraft combination casing, including back casing, procapsid and middle casing, middle casing is located between back casing, the procapsid, the bottom symmetry of back casing is equipped with the fixed block, the fixed block has seted up the spacing groove on keeping away from the tip of back casing, the bottom symmetry of procapsid is equipped with the stabilizing block, the draw-in groove has been seted up to the side of stabilizing block, the surface of stabilizing block is equipped with the stopper, the bottom of stabilizing block is equipped with buffer gear, buffer gear includes two fixed columns, two springs, two sliders and buffer board, the fixed column runs through spring and slider, the slider is located the buffer board; rear housing, procapsid and middle casing composite set, the fixed block runs through the firm piece, and the stopper is connected with firm piece block joint, and the one end of stopper runs through the fixed block, and rear housing, procapsid are connected stably, are convenient for install rear housing, procapsid through screw fastening.

Description

Stable form aircraft combination casing

Technical Field

The utility model belongs to the technical field of aerospace equipment accessories, concretely relates to stable form aircraft combination casing.

Background

The aircraft shell is screwed and fastened through the bolt in the combination, the aircraft is suitable for the aspect of aerospace, when the aircraft is combined, the aircraft needs more tools to clamp the shell, the shell can be damaged in friction, and the aircraft is not simple, convenient and flexible to install.

The existing aircraft shell combination has the problems that a tool is needed to clamp a shell, the shell can be damaged in friction, and in addition, the installation is not simple, convenient and flexible enough, so that a stable aircraft combination shell is provided.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a stable form aircraft combination casing to the aircraft casing combination of proposing in solving above-mentioned background art can damage the casing in the friction, installs not enough simple and convenient nimble problem.

In order to achieve the above object, the utility model provides a following technical scheme: the utility model provides a stable form aircraft combination casing, includes back casing, procapsid and middle casing, middle casing is located between back casing, the procapsid, the bottom symmetry of back casing is equipped with the fixed block, the fixed block has been kept away from and has been seted up the spacing groove on the tip of back casing, the bottom symmetry of procapsid is equipped with the steady piece, the draw-in groove has been seted up to the side of steady piece, the surface of steady piece is equipped with the stopper, the bottom of steady piece is equipped with buffer gear, buffer gear includes two fixed columns, two springs, two sliders and buffer board, the fixed column runs through spring and slider, the slider is located the buffer board.

Preferably, the fixed block is of an L-shaped structure, the stabilizing block is square, and one end of the fixed block is matched with the clamping groove.

Preferably, the limiting block is of a T-shaped structure, a sliding groove is formed in the surface of the stabilizing block and is matched with the sliding groove, a pull ring is arranged at the middle position of the limiting block, the sliding groove is communicated with the clamping groove, and one end of the limiting block is matched with the limiting groove.

Preferably, the stabilizing block and the bottom of the front shell are in the same horizontal plane, and the stabilizing block and the front shell as well as the fixing block and the rear shell are connected through welding.

Preferably, the bottom of the stabilizing block is provided with a rectangular groove, one end of the fixing column is screwed with the stabilizing block through threads, the surface of the buffer board is provided with a through hole, and the fixing column is matched with the through hole.

Preferably, one end of the spring is connected with the stabilizing block, the other end of the spring is connected with the sliding block, the sliding block is of an L-shaped structure, and the sliding block is connected with the fixed column in a sliding mode.

Preferably, the relative internal surface of firm piece all sets up the constant head tank of rectangle, constant head tank and rectangular channel intercommunication, be equipped with two locating pieces on the buffer board, the one end of locating piece is located the constant head tank.

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

1. through fixed block, firm piece and the stopper that sets up, back casing, procapsid and middle casing aggregate erection, the fixed block runs through firm piece, and the stopper is connected with firm piece block joint, and the one end of stopper runs through the fixed block, and back casing, procapsid connection are stable, are convenient for install back casing, procapsid through screw fastening, make casing aggregate erection's convenient.

2. Through buffer board, spring, fixed column and the steady piece that sets up, the procapsid is installed on equipment or organism, and when the procapsid and equipment or organism laminating, the spring is in the contraction state, and the spring produces elasticity, and the spring plays the shock attenuation cushioning effect, makes the procapsid keep stable state.

Drawings

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

FIG. 2 is a schematic view of the three-dimensional structure of the stabilizing block of the present invention;

fig. 3 is a schematic view of the fixing block of the present invention;

FIG. 4 is a schematic sectional view of the stabilizing block of the present invention;

in the figure: 1. a rear housing; 2. a front housing; 3. a fixed block; 4. a stabilizing block; 5. a limiting block; 6. a chute; 7. a card slot; 8. a limiting groove; 9. fixing a column; 10. a spring; 11. a buffer plate; 12. a slider; 13. and (5) positioning the 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.

Examples

Referring to fig. 1 to 4, the present invention provides a technical solution: a stable aircraft combined shell comprises a rear shell 1, a front shell 2 and a middle shell, wherein the middle shell is positioned between the rear shell 1 and the front shell 2, the bottom of the rear shell 1 is symmetrically provided with fixed blocks 3, the end part of each fixed block 3, far away from the rear shell 1, is provided with a limiting groove 8, the bottom of the front shell 2 is symmetrically provided with a stable block 4, the side surface of each stable block 4 is provided with a clamping groove 7, the surface of each stable block 4 is provided with a limiting block 5, the bottom of each stable block 4 is provided with a buffer mechanism, the buffer mechanism comprises two fixed columns 9, two springs 10, two sliders 12 and a buffer plate 11, the fixed columns 9 penetrate the springs 10 and the sliders 12, the sliders 12 are positioned on the buffer plate 11, when the rear shell 1, the front shell 2 and the middle shell are assembled, the fixed blocks 3 penetrate the stable blocks 4, one ends of the limiting blocks 5 penetrate the fixed blocks 3, the rear shell 1 and the front shell 2 are connected firmly, after the front shell 2 is installed and fixed, the spring 10 is in a contracted state, the spring 10 generates elastic force, and the spring 10 has a damping and buffering effect.

In this embodiment, fixed block 3 is "L" type structure, firm piece 4 is square shape, the one end and the draw-in groove 7 cooperation of fixed block 3, stopper 5 is "T" type structure, spout 6 has been seted up on firm 4's surface, stopper 5 and the cooperation of spout 6, the intermediate position of stopper 5 is equipped with the pull ring, spout 6 and draw-in groove 7 intercommunication, stopper 5's one end and spacing groove 8 cooperation, firm 4 is in same horizontal plane with procapsid 2's bottom, firm 4 and procapsid 2 and fixed block 3 all pass through welded connection with back casing 1, during procapsid 2 and middle casing composite set, fixed block 3 runs through firm 4, fixed block 3 is run through to stopper 5's one end, back casing 1, procapsid 2 is connected firmly.

In this embodiment, the rectangular channel has been seted up to firm 4 bottom, the one end of fixed column 9 closes soon with firm 4 and is connected through the screw thread, the through-hole has been seted up on buffer board 11's surface, fixed column 9 and through-hole cooperation, the one end of spring 10 is connected with firm 4 and the other end is connected with slider 12, slider 12 is "L" type structure, slider 12 and fixed column 9 sliding connection, the constant head tank of rectangle has all been seted up on firm 4 relative internal surface, constant head tank and rectangular channel intercommunication, be equipped with two locating piece 13 on the buffer board 11, the one end of locating piece 13 is located the constant head tank, 2 fixed backs in the installation of procapsid, spring 10 is in the contraction state, spring 10 produces elasticity, spring 10 has the shock attenuation cushioning effect.

The utility model discloses a theory of operation and use flow:

when the aircraft shell is combined, the rear shell 1, the front shell 2 and the middle shell are combined and installed, the middle shell is positioned between the rear shell 1 and the front shell 2, when the rear shell 1 and the front shell 2 are correspondingly and stably fixed, the fixed block 3 penetrates through the stable block 4, the limiting block 5 slides, the limiting block 5 is connected with the stable block 4 in a clamping manner, one end of the limiting block 5 penetrates through the fixed block 3, and the rear shell 1 and the front shell 2 are stably connected, so that the rear shell 1 and the front shell 2 are conveniently and fixedly installed through screws;

when procapsid 2 is installed fixedly, procapsid 2 is installed on equipment or organism, buffer board 11 and equipment or organism laminating, when procapsid 2 and equipment or organism laminating, buffer board 11 slides, and spring 10 is in the shrink state, and spring 10 produces elasticity, and spring 10 plays the shock attenuation cushioning effect, makes procapsid 2 keep stable state.

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. A stable form aircraft combination casing, includes back casing (1), procapsid (2) and middle casing, middle casing is located between back casing (1), procapsid (2), its characterized in that: the bottom symmetry of back casing (1) is equipped with fixed block (3), spacing groove (8) have been seted up on the tip that back casing (1) was kept away from in fixed block (3), the bottom symmetry of procapsid (2) is equipped with firm piece (4), draw-in groove (7) have been seted up to the side of firm piece (4), the surface of firm piece (4) is equipped with stopper (5), the bottom of firm piece (4) is equipped with buffer gear, buffer gear includes two fixed columns (9), two springs (10), two sliders (12) and buffer board (11), spring (10) and slider (12) are run through to fixed column (9), slider (12) are located buffer board (11).

2. The stabilized aircraft combination shell of claim 1, wherein: the fixing block (3) is of an L-shaped structure, the stabilizing block (4) is square, and one end of the fixing block (3) is matched with the clamping groove (7).

3. The stabilized aircraft combination shell of claim 1, wherein: stopper (5) are "T" type structure, spout (6) have been seted up on the surface of stabilizing block (4), stopper (5) and spout (6) cooperation, the intermediate position of stopper (5) is equipped with the pull ring, spout (6) and draw-in groove (7) intercommunication, the one end and the spacing groove (8) cooperation of stopper (5).

4. The stabilized aircraft combination shell of claim 1, wherein: the bottom of the stabilizing block (4) and the bottom of the front shell (2) are located on the same horizontal plane, and the stabilizing block (4) is connected with the front shell (2) and the fixing block (3) is connected with the rear shell (1) through welding.

5. The stabilized aircraft combination shell of claim 1, wherein: the bottom of the stabilizing block (4) is provided with a rectangular groove, one end of the fixing column (9) is connected with the stabilizing block (4) in a screwing mode through threads, the surface of the buffer plate (11) is provided with a through hole, and the fixing column (9) is matched with the through hole.

6. The stabilized aircraft combination shell of claim 1, wherein: one end of the spring (10) is connected with the stabilizing block (4) and the other end of the spring is connected with the sliding block (12), the sliding block (12) is of an L-shaped structure, and the sliding block (12) is in sliding connection with the fixing column (9).

7. The stabilized aircraft combination shell of claim 5, wherein: rectangular positioning grooves are formed in the opposite inner surfaces of the stabilizing blocks (4), the positioning grooves are communicated with the rectangular grooves, two positioning blocks (13) are arranged on the buffer plate (11), and one ends of the positioning blocks (13) are located in the positioning grooves.