CN111595198A

CN111595198A - Guide rail type launching box body

Info

Publication number: CN111595198A
Application number: CN202010415038.0A
Authority: CN
Inventors: 付丽强; 俞刘建; 尚宇晴; 刘龙涛; 夏津; 查颖; 张晓宏; 樊浩; 郭金雷; 杨建东; 李建东
Original assignee: Shanghai Institute of Electromechanical Engineering
Current assignee: Shanghai Institute of Electromechanical Engineering
Priority date: 2020-05-15
Filing date: 2020-05-15
Publication date: 2020-08-28
Anticipated expiration: 2040-05-15
Also published as: CN111595198B

Abstract

The invention provides a guide rail type launching box body, which belongs to the technical field of missile launching and comprises a skin and a plurality of guide rails, wherein each guide rail comprises a mounting end and a bearing end, the guide rails are mounted in the skin through the mounting ends and are arranged along the circumferential direction of the skin, the end surface of each bearing end is of a cambered surface structure, the end surfaces of the bearing ends jointly enclose a first accommodating space, a missile is mounted in the first accommodating space, the outer wall of the missile is matched with the cambered surface structure, in the missile launching process, a missile body of the missile slides along the bearing ends in a guiding manner, an air rudder and missile wings respectively slide along the inner wall of the skin, and missile non-projectile launching is realized. The safety of the adjacent equipment is guaranteed, and the integration level of a weapon system is improved.

Description

Guide rail type launching box body

Technical Field

The invention relates to the technical field of missile launching, in particular to a guide rail type launching box body.

Background

Missile box type launching, also known as "storage and transportation box launching" or "shipping box launching". Missiles are launched from box-like containers mounted on a launcher. The box-shaped container has multiple functions, and when the box-shaped container is used as a transport box, the guided missile is placed on a guide rail in the box, and the damping, positioning and locking device is utilized to prevent the guided missile from being damaged due to vibration caused by impact in the transport process; the storage box is internally provided with temperature adjusting equipment filled with nitrogen and dry air, and the storage life can be prolonged after the storage box is sealed; the box as a launching box is internally provided with a launching guide rail, a safety locking mechanism and a cable, and is connected with a launching control system to carry out pre-launching inspection, aiming and launching.

For improving weapon system integration level, the needs of adaptation different environment, the integrated miniaturization in launching box cross-section is more and more urgent, under the miniaturized prerequisite of launching box, need fold in launching box with parts such as the bullet wing of guided missile along same direction by a wide margin, nevertheless because parts such as bullet wing are adjacent less after radial envelope, can't use conventional guide rail to hang or the slider mode of slideing supports the guided missile, so at present the mode that the guided missile was supported to the domestic and foreign use adapter more, the adapter is shed when nevertheless launching and is fallen and easily constitute the threat to closing on equipment, be unfavorable for the guarantee to close on equipment security.

Patent document CN208366160U discloses a mounting and adjusting mechanism for a small-caliber launching box guide rail, which is arranged outside a launching box and used for mounting and adjusting the guide rail inside the box body of the launching box, wherein two guide rails are symmetrically arranged on two sides of the inner wall of the box body, the mounting and adjusting mechanism is composed of a plurality of sub mechanisms which are arranged at intervals from one end to the other end of the launching box, have the same structure and are independently mounted and adjusted, each sub mechanism comprises a fixed frame arranged on the outer wall of the launching box, and two sides of each fixed frame are both provided with a group of fixed holes matched with small holes of the launching box and threaded holes of the guide rails; and each fixing hole is provided with an installation and adjustment assembly, but the design has insufficient utilization of the internal space of the missile and unreasonable structural design.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a guide rail type launch box body.

The guide rail type launch box body comprises a skin 1 and a plurality of guide rails 2;

the missile 3 is mounted inside the skin 1 by means of a plurality of rails 2.

Preferably, the plurality of rails 2 are installed inside the skin 1 and are arranged uniformly or non-uniformly along the circumference of the skin 1.

Preferably, the guide rail 2 has a T-shaped structure.

Preferably, the guide rail 2 comprises a mounting end and a bearing end, wherein the head part of the T-shaped structure is the mounting end, and the foot part of the T-shaped structure is the bearing end;

the guide rail 2 is mounted on the skin 1 via a mounting end.

Preferably, the end face of the bearing end is of an arc-shaped structure, and the end faces of the bearing ends enclose a first accommodating space together;

the missile 3 is installed in the first accommodation space.

Preferably, the missile 3 is provided with an air rudder 4 and missile wings 5;

the air rudder 4 and the missile wing 5 are respectively arranged along the circumference of the missile 3.

Preferably, a second accommodating space is formed between each two adjacent guide rails 2 and the skin 1, and the air rudder 4 and the missile wing 5 can be adjusted to be in a folded state and an unfolded state respectively;

when the missile 3 is installed in the first accommodating space, the air rudder 4 and the missile wing 5 are respectively in a folded state, and the air rudder 4 and the missile wing 5 are both installed in the second accommodating space.

Preferably, the number of said guide rails 2 is 4.

Preferably, the cross section of the skin 1 is an octagonal structure.

Preferably, in the launching process of the missile 3, the missile body of the missile 3 slides along the bearing end in a guiding way, and the air rudder 4 and the missile wing 5 respectively slide along the inner wall of the skin 1.

Compared with the prior art, the invention has the following beneficial effects:

1. the invention adopts a plurality of guide rails to be arranged in the skin to support the missile, which is beneficial to the miniaturization of the launching box body, avoids unsafe factors caused by the adoption of adapters to support the missile in the small and medium-sized launching box body in the prior art, realizes a missile-supporting and projectile-free launching mode, guarantees the safety of adjacent equipment, and improves the integration level of a weapon system.

2. The guide rail adopts a T-shaped structure, so that the problems of launching and supporting of the guided missile are solved, the space utilization rate in the skin is greatly improved, the miniaturization improvement of the box body of the launching box is realized, the structure is simple, and the practicability is high.

3. The end face of the bearing end of the missile is of a cambered surface structure, and the cambered surfaces are matched with the cambered surfaces of the outer walls of the missiles, so that the supporting strength of the missiles is increased, the missile bodies of the missiles can slide along the bearing end in a guiding mode when the missiles are launched, the air rudders and the missile wings slide along the inner walls of the skins, and the missiles can be launched without throwing objects.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

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

fig. 2 is a schematic structural view of the guide rail.

The figures show that:

skin 1 missile 3 missile wing 5

Multiple guide rails 2 air rudders 4 connecting support 6

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

The invention provides a guide rail type launching box body, which comprises a skin 1, a plurality of guide rails 2 and a missile 3, wherein the skin 1 is provided with a plurality of guide rails; the missile 3 is mounted inside the skin 1 by means of a plurality of rails 2.

Specifically, the plurality of guide rails 2 are installed inside the skin 1 and are uniformly or non-uniformly arranged along the circumferential direction of the skin 1, and the guide rails 2 comprise installation ends and bearing ends, wherein the head part of the T-shaped structure is the installation end, and the foot part of the T-shaped structure is the bearing end; the rails 2 are mounted on the skin 1 by mounting ends, one on eachPreferred embodiment(s) of the inventionThe guide rail 2 is welded on the skin 1 through a mounting end; at one isVariation exampleThe mounting end of the guide rail 2 is mounted on the skin 1 through a bolt.

Further, an intermediate section is further arranged between the mounting end and the bearing end of the guide rail 2, as shown in fig. 2, the thickness of the intermediate section is N, the width of the bearing end is M, where M > N, and when the guide rail 2 is specifically designed, the thickness of the intermediate section should be reduced as much as possible while the supporting strength is satisfied, on one hand, the contact area with the missile 3 is increased, and on the other hand, a larger second accommodating space is obtained, and the filling of the air rudder 4 and the missile wing 5 is satisfied.

Specifically, as shown in fig. 1 and 2, the guide rail 2 is of a T-shaped structure, and the width of the mounting end is greater than that of the bearing end, so that the mounting end and the skin 1 have a larger contact area, the firmness of the mounting of the guide rail 2 on the skin 1 is ensured, and the effective support of the missile 3 is ensured.

Specifically, as shown in fig. 1 and fig. 2, the end surface of the bearing end is an arc surface structure, and the end surfaces of the plurality of bearing ends together enclose a first accommodating space; the missile 3 is installed in the first accommodating space, and the end face of the bearing end is of a cambered surface structure and is matched with the cambered surface of the outer wall of the missile 3.

Specifically, as shown in fig. 1, the missile 3 is provided with an air rudder 4 and missile wings 5; the air rudders 4 and the missile wings 5 are respectively arranged along the circumferential direction of the missile 3, a second accommodating space is formed between each two adjacent guide rails 2 and the skin 1, and the air rudders 4 and the missile wings 5 can be respectively adjusted to be in a folded state and a stretched state; when the missile 3 is installed in the first accommodating space, the air rudder 4 and the missile wing 5 are respectively in a folded state, and the air rudder 4 and the missile wing 5 are both installed in the second accommodating space.

Further, the air rudder 4 and the missile wing 5 are installed on the missile 3 through the connecting support piece 6, the connecting support piece 6 is installed on one side of the second accommodating space, when the air rudder 4 and the missile wing 5 are in a folded state, the free ends of the air rudder 4 and the missile wing 5 extend to the other side of the second accommodating space, so that the internal space of the skin 1 can be fully utilized, and the volume of the skin 1 is reduced.

At one isPreferred embodiment(s) of the inventionThe connection support 6 is mounted on the projectile 3 by means of a screw connection.

Specifically, as shown in fig. 1, in the launching process of the missile 3, the missile body of the missile 3 slides along the bearing end in a guiding manner, and the air rudder 4 and the missile wing 5 slide along the inner wall of the skin 1, so that the missile 3 is launched without throwing objects.

In a specific embodimentExamplesAs shown in fig. 1, the number of the guide rails 2 is 4, the cross section of the skin 1 is an octagonal structure, the skin 1 is an octagonal prism structure, the side surfaces of the skin 1 are respectively marked as a first side surface, a second side surface, a third side surface, a fourth side surface, a fifth side surface, a sixth side surface, a seventh side surface and an eighth side surface, and the mounting ends of the 4 guide rails 2 are respectively welded to the inner walls of the second side surface, the fourth side surface, the sixth side surface and the eighth side surface.

In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.

Claims

1. A guide rail type launch box body is characterized by comprising a skin (1) and a plurality of guide rails (2);

the missile (3) is arranged inside the skin (1) through a plurality of guide rails (2).

2. The rail-mounted launch box casing according to claim 1, characterized in that the plurality of rails (2) are mounted inside the skin (1) and are arranged uniformly or non-uniformly along the circumference of the skin (1).

3. The guideway-style launch box body of claim 1, characterized in that the guideway (2) is a T-shaped structure.

4. The guideway-style launch box body of claim 3, characterized in that the guideway (2) comprises a mounting end and a carrying end;

the head part of the T-shaped structure is a mounting end, and the foot part of the T-shaped structure is a bearing end;

the guide rail (2) is mounted on the skin (1) through a mounting end.

5. The guideway-type launch box body of claim 4, wherein the end surfaces of the bearing ends are cambered structures, and the end surfaces of the plurality of bearing ends together enclose a first accommodating space;

the missile (3) is installed in the first accommodating space.

6. The guideway-type launch box body according to claim 4, characterized in that the missile (3) is provided with an air rudder (4) and missile wings (5);

the air rudder (4) and the missile wing (5) are respectively arranged along the circumference of the missile (3).

7. The rail-mounted launch box body according to claim 6, characterized in that a second receiving space is formed between each two adjacent rails (2) and the skin (1);

the air rudder (4) and the missile wing (5) can be adjusted to be in a folded state and an unfolded state respectively;

when the missile (3) is installed in the first accommodating space, the air rudder (4) and the missile wing (5) are respectively in a folded state, and the air rudder (4) and the missile wing (5) are both installed in the second accommodating space.

8. The guideway-launch box body of claim 1, characterized in that the number of the guideways (2) is 4.

9. The rail-mounted launch box body according to claim 1, characterized in that the cross-section of the skin (1) is an octagonal structure.

10. The guideway type launch box body according to claim 5, characterized in that during the launch of the missile (3), the missile body of the missile (3) slides along the bearing end in a guiding way, and the air rudder (4) and the missile wing (5) respectively slide along the inner wall of the skin (1).