Space cylinder bomb separation auxiliary support mechanism and launching cylinder

Abstract

The application provides a space shell-and-missile separation auxiliary support mechanism and a launching cylinder in the technical field of shell-and-missile separation, which comprises front auxiliary supports and rear auxiliary supports, the front auxiliary supports are uniformly installed on the front end of the surface of the missile body, and the rear auxiliary supports are uniformly installed on the rear end of the surface of the missile body. The front auxiliary support comprises a lower cylinder, a compression spring and a limiting screw, the compression spring is arranged in the front auxiliary support, and the front auxiliary support is arranged in close contact with the launching cylinder guide rail through the compression spring. The lower cylinder is internally provided with a clamping groove, the clamping groove and the limiting screw are arranged in cooperation and are provided with a redundant design for realizing the collection and fixation of the front auxiliary support after the shell-and-missile separation. The rear auxiliary support is arranged in clearance fit with the launching cylinder guide rail and is used for controlling the movement state of the missile body in the flight process. The application can realize reliable support and sliding separation between the launching cylinder and the missile body, and meanwhile, beneficial effects such as simple structure and light mass are achieved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of barrel and missile separation, in particular to a space barrel and missile separation auxiliary support mechanism and a launch barrel. BACKGROUND

[0002] With the development of aerospace technology, space barrel and missile separation is a major trend in future development and is also a guarantee of international status and strategic deterrence for each country. Currently, the missile body is mainly installed in the launch barrel, and the two are carried in the form of a combination in the launch platform such as a rocket for launching. The launch barrel needs to withstand various load conditions during transportation, launching and flight to ensure the reliability of the connection and complete the barrel and missile separation after flying to the specified height. In order to ensure the controllability of the separation attitude, an auxiliary support is often provided on the surface of the missile body to match the guide rail of the launch barrel, which is used for supporting and sliding separation of the missile body.

[0003] The traditional auxiliary support mainly adopts hard contact sliding with no gap, which has the following disadvantages: 1. The machining tolerance control is extremely strict. If the gap between the auxiliary support and the guide rail is too large, the supporting effect will be lost, and if the gap is too small, the separation will be stuck. 2. The friction between the auxiliary support and the guide rail is large and difficult to control during the design process, which requires multiple tests and verification, and is easy to damage the coating of the guide rail, seriously reducing the service life. 3. The hard contact connection mode generates a large load during flight and vibration, which is not conducive to the lightweight design of the launch barrel. 4. Hard contact can easily cause deformation of the launch barrel guide rail, which may affect the smoothness of separation, and even affect the smooth completion of the flight mission. SUMMARY

[0004] In view of the defects in the prior art, the purpose of the present application is to provide a space barrel and missile separation auxiliary support mechanism and a launch barrel.

[0005] According to the space barrel and missile separation auxiliary support mechanism provided by the present application, the front auxiliary support is uniformly installed at the front end of the surface of the missile body, and the rear auxiliary support is uniformly installed at the rear end of the surface of the missile body.

[0006] The front auxiliary support includes a lower barrel, a compression spring and a limiting screw. The compression spring is arranged inside the front auxiliary support, and the front auxiliary support is arranged by pressing and fitting the launch barrel guide rail through the compression spring.

[0007] The lower barrel is internally provided with a clamping groove, and the clamping groove and the limiting screw are arranged in a redundant design to realize the collection and fixation of the front auxiliary support after the barrel and missile separation.

[0008] The rear auxiliary support is arranged in a gap fit with the launch barrel guide rail to control the movement state of the missile body during flight.

[0009] In some embodiments, the elastic body is connected to the launching barrel guide rail through the front auxiliary support and the rear auxiliary support, and the plurality of front auxiliary supports are evenly distributed at the front end of the surface of the elastic body at an angle of 120°, and the plurality of rear auxiliary supports are evenly distributed at the rear end of the surface of the elastic body at an angle of 120°.

[0010] In some embodiments, the axial distance between the front auxiliary support and the center of mass on the elastic body is equal to the axial distance between the rear auxiliary support and the center of mass on the elastic body.

[0011] In some embodiments, the front auxiliary support further comprises a locking pin and an upper barrel body, and the locking pin is arranged on the front auxiliary support.

[0012] By cooperating the locking pin with the upper barrel body and the lower barrel body, the compression spring is compressed when the assembly is in place on the ground, and the compression spring is released when the barrel and elastic body assembly is assembled.

[0013] In some embodiments, the limiting screws are arranged on both sides of the front auxiliary support, the limiting screws are fixed through the limiting screw holes on the upper barrel body, and the ends of the limiting screws extend into the clamping grooves on the lower barrel body.

[0014] In some embodiments, the upper barrel body at one end of the front auxiliary support is arranged in soft contact with the launching barrel guide rail through the compression spring, and the lower barrel body at the other end of the front auxiliary support is connected to the elastic body, which is used to prevent the launching barrel guide rail from being deformed during the assembly on the ground and the flight process, thereby affecting the separation attitude.

[0015] The other end of the rear auxiliary support is connected to the elastic body.

[0016] In some embodiments, when the assembly is in place on the ground, the front auxiliary support is compressed to insert the locking pin, and the front auxiliary support is arranged at a certain distance from the launching barrel guide rail.

[0017] When the barrel and elastic body assembly is completed, the locking pin is extracted to release the compression spring, and the front auxiliary support is arranged in contact with the launching barrel guide rail.

[0018] In some embodiments, the front auxiliary support and the rear auxiliary support are both provided with a concave hole on the end surface of the end connected to the elastic body, and the front auxiliary support and the rear auxiliary support are both installed on the surface of the elastic body through the concave hole, and the end surface of the end connected to the elastic body of the front auxiliary support and the rear auxiliary support is arranged in a circular arc shape.

[0019] In some embodiments, the surface of the launching barrel guide rail is treated by a thick plating film process, and the front auxiliary support and the rear auxiliary support are both arranged in arc contact with the launching barrel guide rail.

[0020] A launching barrel comprises the spatial barrel and elastic body separation auxiliary support mechanism.

[0021] Compared with the prior art, the application has the following beneficial effects:

[0022] 1、The application adopts compression spring to match the front auxiliary support and the launching cylinder guide rail, adopts gap matching to match the rear auxiliary support and the launching cylinder guide rail, the launching cylinder guide rail has small load bearing and no deformation risk, which is beneficial to reliable separation between the projectile and the launching cylinder;

[0023] 2、The application plays a supporting and connecting role between the launching cylinder and the projectile through the front auxiliary support and the rear auxiliary support, and through the hard contact-free connecting mode, the launching cylinder has small load bearing, which is beneficial to lightweight design of the launching cylinder;

[0024] 3、The application adopts the soft support contact mode of the compression spring between the front auxiliary support and the launching cylinder guide rail, the friction is small when the projectile and the launching cylinder are separated, and the compression spring force can be compensated, no test verification is needed, the coating on the launching cylinder guide rail is not damaged, and the service life of the launching cylinder is significantly improved. BRIEF DESCRIPTION OF DRAWINGS

[0025] Other features, objects and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0026] Figure 1 is a structural schematic diagram of the space cylinder projectile separation auxiliary support mechanism of the application;

[0027] Figure 2 is a local enlarged schematic diagram of the space cylinder projectile separation auxiliary support mechanism of the application Figure 1 ;

[0028] Figure 3 is a local enlarged schematic diagram of the space cylinder projectile separation auxiliary support mechanism of the application Figure 2 ;

[0029] Figure 4 is a top view schematic diagram of the front auxiliary support of the application;

[0030] Figure 5 is a sectional view schematic diagram of the front auxiliary support of the application Figure 1 ;

[0031] Figure 6 is a sectional view schematic diagram of the front auxiliary support of the application Figure 2 ;

[0032] Figure 7 is a top view schematic diagram of the rear auxiliary support of the application;

[0033] Figure 8 is a front view schematic diagram of the rear auxiliary support of the application;

[0034] Figure 9is a schematic view of the structure of the front auxiliary support of the present application in the assembled state on the ground;

[0035] Figure 10 is a schematic view of the structure of the front auxiliary support of the present application in the flight state;

[0036] Figure 11 is a schematic view of the structure of the front auxiliary support of the present application in the state after separation.

[0037] Reference signs:

[0038] front auxiliary support 1 locking pin threaded section 151

[0039] upper cylinder 11 detent slot 16

[0040] compression spring 12 rear auxiliary support 2

[0041] lower cylinder 13 elastic body 3

[0042] limiting screw 14 launch tube guide rail 4

[0043] locking pin 15 concave hole 5 DETAILED DESCRIPTION

[0044] The present application will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present application. These all belong to the protection scope of the present application.

[0045] Example 1

[0046] As Figures 1-11The shown application includes front auxiliary support 1 and rear auxiliary support 2. The front auxiliary support 1 is evenly installed on the front end of the surface of the projectile body 3, including an upper cylinder 11, a compression spring 12, a lower cylinder 13, a limiting screw 14, and a locking pin 15. The front auxiliary support 1 is tightly attached to the launch tube guide rail 4 through the internal compression spring 14, and the attachment arc is set to 180°. In order to reduce the friction between the auxiliary supports as much as possible, the surface of the launch tube guide rail 4 needs to be coated, and the arc surface attachment design is adopted, and the surface roughness of both is set to 0.8. The launch tube guide rail 4 needs to use the same material and surface treatment method as the upper cylinder (11), so as to ensure that the friction between them is a constant value, and the service life can be greatly improved. The rear auxiliary support 2 is gap fitted with the launch tube guide rail 4, and the attachment arc is set to 160°, which is used to prevent the vibration of the projectile body during flight from being too large. The front auxiliary support 1 and the rear auxiliary support 2 are evenly installed on the surface of the projectile body 3 through the concave hole 5, which is used to adjust the radial error caused by processing and assembly, and to ensure that the arc centers of the auxiliary supports and the launch tube guide rail are coaxial. The lower cylinder 13 is provided with a clamping groove inside to cooperate with the limiting screw 14, which is used to realize the collection and fixation of the rear auxiliary support after the separation of the cylinder and the projectile, and to ensure that there is no excess space.

[0047] The compression spring 12 is installed between the upper cylinder 11 and the lower cylinder 13, and the spring compression stroke is determined by the distance between them. The compression spring 12 needs to be matched with the friction between the coated launch tube guide rail 4 and the upper cylinder 11. The stiffness dispersion of the compression spring 12 on the three front auxiliary supports 1 should not be greater than 10%, which ensures that the launch tube is evenly stressed in three directions, so as to ensure that the pressure between the auxiliary support and the launch tube guide rail is small, and the upper cylinder and the launch tube guide rail are attached with a specific pressure value. The coating treatment plays a protective and lubricating role for the launch tube guide rail 4, reducing the friction between the auxiliary support and the launch tube guide rail. The limiting screw 14 is distributed on both sides of the front auxiliary support 1, which is fixed through the limiting screw hole at the lower end of the upper cylinder 11. The limiting screw 14 extends to the clamping groove 16 of the lower cylinder on both sides.

[0048] When the front auxiliary support 1 is separated from the launch tube guide rail 4, the front auxiliary support moves outward under the action of the compression spring 12, and through the cooperation of the limiting screw 14 and the clamping groove 16, the collection and fixation of the front auxiliary support 1 after the separation of the cylinder and the projectile are realized. The limiting screw 14 at this place adopts a redundant design on both sides to prevent the impact caused by separation from being too large, causing the front auxiliary support to fly out after separation. Redundant design means that there is a limiting screw 14 and a clamping groove 16 on both sides of the front auxiliary support 1. Through redundant design, even if one of the limiting screws 14 fails, the reliable collection of the front auxiliary support 1 after separation can still be completed, as shown in Figure 11

[0049] ​The locking pin 15 needs to be matched with the internal locking hole of the upper cylinder body 11 and the lower cylinder body 13, and in the ground assembly process, the auxiliary support 1 needs to be compressed by a tool to insert the locking pin, and the ground assembly of the front auxiliary support 1 is completed. At this time, the front auxiliary support 1 and the launch cylinder guide rail 4 need to ensure a spacing of more than 5 mm to facilitate the assembly of the projectile and the launch cylinder. After the assembly of the cylinder projectile combination is completed, the locking pin 15 needs to be pulled out to release the compressed spring 12, so as to ensure the fit of the front auxiliary support 1 and the launch cylinder guide rail 4. The outer side of the locking pin 15 is processed with a threaded section 18, so as to facilitate the assembly and disassembly of the locking pin 15.

[0050] Specifically, in the embodiment, the use mode of the space cylinder projectile separation auxiliary support mechanism of the application comprises:

[0051] 1. As shown in the figure, the ground assembly steps are as follows: Figure 9

[0052] Firstly, the rear auxiliary support 2 and the lower cylinder body 13 are connected with the projectile 3, the compressed spring 12 is placed in the lower cylinder body 14, and the upper cylinder body 11 is placed above the compressed spring 12;

[0053] Secondly, the upper cylinder body 11 is driven by a tool to compress the compressed spring 12 until the upper cylinder body 11 is fitted with the lower cylinder body 13, at this time, the corresponding locking holes of the upper cylinder body 11 and the lower cylinder body 13 are coincided, the locking pin 15 is inserted, and the ground locking of the front auxiliary support 1 is completed;

[0054] Thirdly, the assembly of the two limiting screws 14 is completed, and the screws enter the clamping grooves 16 in the lower cylinder.

[0055] 2. As shown in the figure, the assembly to the flight state steps are as follows: Figure 10

[0056] Firstly, the general assembly of the cylinder projectile combination is completed;

[0057] Secondly, the radial installation positions of the front and rear auxiliary supports are adjusted through the concave holes 5 on the end faces of the auxiliary supports, so as to ensure that the centers of the auxiliary supports are coaxial with the center of the launch cylinder guide rail 4;

[0058] Thirdly, the front auxiliary support 1 is fitted with the launch cylinder guide rail 1 by cooperating the threaded section 151 of the locking pin with the disassembly tool and completing the disassembly.

[0059] 3. As shown in the figure, the state of the front auxiliary support 1 after the cylinder projectile separation is as follows: Figure 11

[0060] ​​​When the barrel bomb is separated, the front auxiliary support 1 is separated from the barrel guide rail 4, at this time, the compression spring 12 loses the upper end constraint, and pushes the upper barrel body 11 to move outward to the limit screw 14 and the clamping groove 16 to complete the clamping.

[0061] Embodiment 2

[0062] A barrel, comprising the space barrel bomb separation auxiliary support mechanism of embodiment 1.

[0063] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0064] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other without conflict.

Claims

1. A space cylinder bullet separation auxiliary support mechanism characterized by, The front auxiliary support (1) and the rear auxiliary support (2) are evenly arranged on the front end and the rear end of the surface of the projectile body (3); The front auxiliary support (1) comprises a lower cylinder (13), a compression spring (12) and a limiting screw (14), the compression spring (12) is arranged in the front auxiliary support (1), and the front auxiliary support (1) is arranged in close contact with the launching barrel guide rail (4) through the compression spring (12); The lower cylinder (13) is internally provided with a clamping groove (16), the clamping groove (16) is arranged in cooperation with the limiting screw (14) and adopts a redundant design for realizing the collection and fixation of the front auxiliary support (1) after the separation of the cylinder and the projectile; The redundant design is that the limiting screws (14) are arranged on both sides of the front auxiliary support (1); the limiting screws (14) are fixed through the limiting screw holes in the upper cylinder (11), and the two ends of the limiting screws (14) extend into the clamping grooves (16) in the lower cylinder (13); The rear auxiliary support (2) is arranged in gap cooperation with the launching barrel guide rail (4) and is used for controlling the movement state of the projectile body (3) in the flight process; The projectile body (3) is connected with the launching barrel guide rail (4) through the front auxiliary support (1) and the rear auxiliary support (2), and a plurality of front auxiliary supports (1) are evenly arranged on the front end of the surface of the projectile body (3) at an angle of 120°, and a plurality of rear auxiliary supports (2) are evenly arranged on the rear end of the surface of the projectile body (3) at an angle of 120°; The front auxiliary support (1) further comprises a locking pin (15) and an upper cylinder (11), and the locking pin (15) is arranged on the front auxiliary support (1); The locking pin (15) is arranged in cooperation with the upper cylinder (11) and the lower cylinder (13), realizes the compression action of the compression spring (12) when the assembly on the ground is in place, and realizes the release action of the compression spring (12) when the cylinder-projectile assembly is assembled; The front auxiliary support (1) and the rear auxiliary support (2) are both provided with a concave hole (5) on the end face of the one end connected with the projectile body (3), the front auxiliary support (1) and the rear auxiliary support (2) are both evenly arranged on the surface of the projectile body (3) through the concave hole (5), and the front auxiliary support (1) and the rear auxiliary support (2) are both arranged in a circular arc shape on the side end face connected with the projectile body (3).

2. The space-frame pop-out separation assist support mechanism of claim 1, wherein, The axial distance between the center of mass positions on the front auxiliary support (1) and the projectile body (3) is equal to the axial distance between the center of mass positions on the rear auxiliary support (2) and the projectile body (3).

3. The space-frame pop-out assist support mechanism of claim 1, wherein, The upper cylinder (11) on one end of the front auxiliary support (1) is arranged in soft contact with the launching barrel guide rail (4) through the compression spring (12), and the lower cylinder (13) on the other end of the front auxiliary support (1) is connected with the projectile body (3) and is used for preventing the launching barrel guide rail (4) from being deformed in the ground assembly stage and the flight process, thereby affecting the separation attitude; One end of the rear auxiliary support (2) is arranged in gap cooperation with the launching barrel guide rail (4), and the other end of the rear auxiliary support (2) is connected with the projectile body (3).

4. The space-frame pop-out separation assist support mechanism of claim 1, wherein, When the assembly on the ground is in place, the front auxiliary support (1) is compressed to insert the locking pin (15), and the front auxiliary support (1) is arranged at a certain distance from the launching barrel guide rail (4). When the barrel and cartridge assembly is assembled, the compression spring (12) is released by pulling out the locking pin (15), and the front auxiliary support (1) is attached to the barrel guide rail (4).

5. The space-frame pop-out separation assist support mechanism of claim 1, wherein, The surface of the barrel guide rail (4) is treated by thick plating film process, and the front auxiliary support (1) and the rear auxiliary support (2) are both arc-surface attached to the barrel guide rail (4).

6. A barrel comprising the space barrel and cartridge separation auxiliary support mechanism according to any one of claims 1-5.

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