CN218002343U

CN218002343U - Missile cavity body member for installing missile rudder wing

Info

Publication number: CN218002343U
Application number: CN202222057514.3U
Authority: CN
Inventors: 田春林
Original assignee: Yangzhou Dianmai Precision Technology Co ltd
Current assignee: Yangzhou Dianmai Precision Technology Co ltd
Priority date: 2022-08-05
Filing date: 2022-08-05
Publication date: 2022-12-09
Anticipated expiration: 2032-08-05

Abstract

A missile cavity body component for installing a missile rudder wing comprises a top plate, a bottom plate, an outer ring plate and an inner ring plate, wherein the top plate and the bottom plate are arranged at intervals up and down and are fixedly connected through the outer ring plate and the inner ring plate; and a plurality of profiling supporting columns which can be matched with the top plate to form a positioning and supporting structure are arranged on the outer wall of the outer ring plate. The utility model discloses a cavity on the interior crown plate supports the guided missile, avoids empting, need not personnel to hold by hand, carries out the ascending location of axis direction through profile modeling support column cooperation roof to the chamber major structure of playing, can avoid it to appear rocking in assembling process, easy to assemble, easy operation, work efficiency is high, and only needs alone can operate, has reduced the cost of labor.

Description

Missile cavity body member for installing missile rudder wing

Technical Field

The utility model relates to a guided missile erection equipment field, in particular to a missile cavity body component for installing guided missile rudder wing.

Background

In the prior art, the missile used by the existing armored vehicle is generally installed by manually installing the rudder wings on the missile, and the missile wings and the rudder wings are installed in alignment after the position of the missile is required to be adjusted in the installation process. It has work load big, and work efficiency is low, and need alone hold the guided missile main part, and alone installation rudder wing has increased the cost of labor, consequently, needs the bullet chamber body component that is used for installing the guided missile rudder wing to solve above-mentioned problem.

Therefore, in order to solve the above problems, it is necessary to design a missile cavity body member for installing a rudder wing of a missile.

SUMMERY OF THE UTILITY MODEL

In order to overcome the defects in the prior art, the utility model aims to provide a missile cavity main body component for installing a missile rudder wing.

In order to achieve the above objects and other related objects, the present invention provides a technical solution: a missile cavity body component for installing a missile rudder wing comprises a top plate, a bottom plate, an outer ring plate and an inner ring plate, wherein the top plate and the bottom plate are arranged at intervals up and down and are fixedly connected through the outer ring plate and the inner ring plate; and a plurality of profiling supporting columns which can be matched with the top plate to form a positioning supporting structure are arranged on the outer wall of the outer ring plate.

The preferable technical scheme is as follows: two positioning holes are formed in the end face of the bottom plate.

The preferable technical scheme is as follows: the number of the inner circular holes is four, and the inner circular holes are arranged on the peripheral wall of the inner ring plate at equal angles; the four outer circular holes are arranged on the peripheral wall of the outer ring plate at equal angles; the four inner circular holes and the four outer circular holes are correspondingly arranged one by one.

The preferable technical scheme is as follows: the top plate, the bottom plate, the outer ring plate and the inner ring plate are fixed into a whole through welding or are integrally processed.

Because of the application of the technical scheme, the utility model discloses the beneficial effect who has does:

the utility model provides a pair of a play chamber main part component for installing guided missile rudder wing supports the guided missile through the cavity on the interior crown plate, avoids empting, need not personnel and holds by hand, carries out ascending location of axis to play chamber major structure through profile modeling support column cooperation roof, can avoid it to appear rocking in the assembling process, easy to assemble, easy operation, work efficiency is high, and only needs alone can operate, has reduced the cost of labor.

Drawings

Fig. 1 is a view of the present invention.

Fig. 2 is a schematic structural view of the first clamping plate and the first hydraulic cylinder in the bullet cavity main body component of the present invention.

Fig. 3 is a schematic view of the clamping plate in the bullet cavity main body component of the present invention.

Fig. 4 is a schematic structural diagram of the bracket, the connecting plate and the second hydraulic cylinder in the bullet cavity main body component of the present invention.

Detailed Description

The following description is provided for illustrative purposes, and other advantages and features of the present invention will become apparent to those skilled in the art from the following detailed description.

Please refer to fig. 1-4. It should be understood that in the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate the position or positional relationship based on the position or positional relationship shown in the drawings, or the position or positional relationship that the product of the present invention is usually placed when in use, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element to which the term refers must have a specific position, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," "third," and the like are used solely to distinguish one from another and are not to be construed as indicating or implying relative importance. The terms "horizontal", "vertical", "suspended" and the like do not imply that the components are absolutely required to be horizontal or suspended, but may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the present invention, it should be noted that, unless otherwise specifically stated or limited, the terms "disposed," "mounted," "connected" and "connected" are to be construed broadly and may include, for example, a fixed connection, a detachable connection, an integral connection, a mechanical connection, an electrical connection, a direct connection, an indirect connection through an intermediary, and a communication between two elements. The specific meaning of the above terms in the present invention can be understood as a specific case by those skilled in the art.

The embodiment is as follows:

as shown in figures 1-4, for the missile cavity body member for installing the rudder wing of the missile provided by the invention, the missile cavity body member comprises a top plate 1, a bottom plate 2, an outer ring plate 3 and an inner ring plate 4. The top plate 1 and the bottom plate 2 are arranged at intervals up and down and are fixedly connected through an outer ring plate 3 and an inner ring plate 4, and the inner ring plate 4 is coaxially arranged inside the outer ring plate 3. Four inner circular holes (not shown) which are arranged at equal angles are formed in the peripheral wall of the inner ring plate 4, and four outer circular holes 31 which are arranged at equal angles are formed in the peripheral wall of the outer ring plate 3. The four inner circular holes and the four outer circular holes 31 are arranged in a one-to-one correspondence manner, and the central axes of the inner circular holes and the central axes of the outer circular holes 31 are located on the same straight line.

Wherein, the central position of the top plate 1 is provided with a through hole (not shown) with the same inner diameter as the inner ring plate 4, so that the guided missile can be inserted into the inner cavity of the inner ring plate 4.

When the missile is required to be installed with the rudder wing, the hydraulic cylinder I5 is fixed to the outer side of the outer ring plate 3 through the flange plate, the clamp plate 6 extends into the outer circular hole 31, the support 7 is fixed to the positioning hole 21 in the lower side of the bottom plate 2, the missile is placed in the cavity in the inner ring plate 4, the connecting plate 9 is driven to move upwards through operation of the hydraulic cylinder II 8, the missile is driven to move upwards along the cavity, after the missile moves upwards to a specified height, the clamp plate 6 is driven to move inwards through the hydraulic cylinder I5, the missile is clamped, the wing surface of the missile is installed on the missile, then the missile continues to move upwards, the rudder surface of the missile is installed on the missile, and the missile rudder wing is installed rapidly.

Furthermore, be equipped with a plurality of profile modeling support columns 32 that can form location bearing structure with the roof cooperation on the outer wall of outer crown plate 3 to bottom plate 2 rocks appears in the time of preventing the assembly, leads to the unstable condition of guided missile installation.

In the present application, the top plate 1, the bottom plate 2, the outer ring plate 3, and the inner ring plate 4 are integrally fixed or machined by welding.

Therefore, the utility model has the advantages of it is following:

The above embodiments are merely illustrative of the principles and effects of the present invention, and are not intended to limit the present invention. Modifications and variations can be made to the above-described embodiments by those skilled in the art without departing from the spirit and scope of the present invention. Accordingly, it is intended that all equivalent modifications or changes which may be made by those skilled in the art without departing from the spirit and technical spirit of the present invention shall be covered by the claims of the present invention.

Claims

1. A bullet chamber body component for installing missile rudder wing which characterized in that: the inner ring plate is coaxially arranged inside the outer ring plate, an inner circular hole is formed in the peripheral wall of the inner ring plate, an outer circular hole is formed in the peripheral wall of the outer ring plate, and the central axis of the inner circular hole and the central axis of the outer circular hole are located on the same straight line; and a plurality of profiling supporting columns which can be matched with the top plate to form a positioning and supporting structure are arranged on the outer wall of the outer ring plate.

2. The missile cavity body member for installing the missile rudder wing as claimed in claim 1, wherein: and two positioning holes are formed in the end face of the bottom plate.

3. The missile cavity body member for installing the rudder wing of a missile as claimed in claim 1, wherein: the number of the inner circular holes is four, and the inner circular holes are arranged on the peripheral wall of the inner ring plate at equal angles; the four outer circular holes are arranged on the peripheral wall of the outer ring plate at equal angles; the four inner circular holes and the four outer circular holes are correspondingly arranged one by one.

4. The missile cavity body member for installing the rudder wing of a missile as claimed in claim 1, wherein: the top plate, the bottom plate, the outer ring plate and the inner ring plate are fixed into a whole through welding or are integrally processed.