A launch tube rear cover structure and installation and use method

Abstract

The invention relates to a rear cover structure of a launch tube. It comprises a rear end ring, an inner pressure ring, an outer pressure ring, a fragile cover sheet, an O-shaped sealing ring and the like. The rear end ring is an inner and outer double thread structure, the inner thread cooperates with the inner pressure ring, the outer thread cooperates with the outer pressure ring, and the rear end ring is provided with a sealing ring. An axially adjustable limiting boss is provided on the inner pressure ring, which plays an anti-loosening role in combination with a thread locking glue. The outer pressure ring is mounted on the outer ring of the rear end ring, and forms a sealing link with the fragile cover sheet and the O-shaped sealing ring. The fragile cover sheet has a weak link, which is broken under the action of the engine gas flow. Its beneficial effects are as follows: the limiting mechanism is connected by threads, has an axially adjustable function, can eliminate the assembly gap caused by the processing error of the missile and the launch tube, and realizes the reliable limiting function of the tail of the missile; the engine gas flow is used as the power source for breaking the fragile cover, no additional power is required, and has the advantages of simple structure, low cost, high reliability and the like; it overcomes the problem that the recoil of the missile after launch is too large, which is not conducive to the portable launch of a single soldier group, and improves the stability of the missile exiting the tube posture.

Description

Technical Field

[0001] The invention belongs to the technical field of missile launching, and specifically relates to a structure, installation and use method of a rear cover of a launching tube. Background Art

[0002] In the design process of storage and transportation launch tubes, the tube body, tube cover, director, and locking mechanism are key components that directly affect the performance of storage and transportation launch tubes. The rear cover is a type of tube cover in the launch tube and is installed at the tail of the launch tube. The design of the rear cover requires good sealing performance at ordinary times, so that the missile inside is in a good storage environment state, and it can be opened quickly when the missile is launched. When the locking mechanism is to release the mechanical lock of the missile before launch, the design of the rear cover must also consider the limited position function of the missile launched at an inclined angle to prevent the missile from moving backward under the action of gravity, causing the electrical connector on the missile to separate and fall off or directly slide out of the tail of the launch tube. The gas flow is a feature that needs to be considered in the design of the rear cover. When the missile is launched, the high-speed, high-temperature airflow containing solid particles generated by the engine will produce severe jet impact on the rear cover of the launch tube, including thermal shock and dynamic shock effects, which seriously affect the launch posture of the missile. Summary of the invention

[0003] The purpose of the present invention is to provide a launch tube rear cover structure, and a corresponding installation and use method, which adopts a threaded connection limit structure to make the tail limit mechanism axially adjustable, eliminate the assembly gap caused by the structural processing error of the missile and the launch tube, and realize reliable limit of the missile tail. In the case of limited space in a small-caliber missile launch tube, the gas flow discharge guide channel is released as much as possible to solve the problem that the missile launch recoil is too large, which is not conducive to portable launch by a single soldier group, and can improve the stability of the missile exiting the tube. It has the advantages of simple structure, good sealing, convenient service handling, high reliability, etc.

[0004] To achieve the above purpose, the technical solution adopted by the present invention is as follows:

[0005] A launch tube rear cover structure is mainly characterized in that it includes a rear end ring, an inner pressure ring, an outer pressure ring, a fragile cover plate, an O-ring and a tail gas flow channel.

[0006] The rear end ring is the main body of the rear cover structure, and adopts a structural design scheme of internal and external double threads. The rear end ring is a concentric cylindrical ring structure. The front inner profile of the rear end ring is sleeved with the outer profile of the rear end of the launch tube body. The rear end ring is provided with a rectangular annular groove at the junction with the launch tube body. The inner thread cooperates with the inner pressure ring, and the outer thread cooperates with the outer pressure ring. The end face of the rear end ring is provided with an O-ring installation groove. The inner pressure ring has symmetrically arranged limiting bosses inside, and adopts a threaded limiting structure, which has an axially adjustable function. When installed, it is used in combination with thread locking glue to play a role in preventing loosening. The outer pressure ring is installed on the outer ring of the rear end ring, and forms a sealing link with the fragile cover plate and the O-ring to ensure the sealing of the launch tube rear cover. The fragile cover plate is pre-engraved with a weak link, which is broken under the action of the engine gas flow. The O-ring is made of silicone rubber and installed in the sealing groove of the rear end ring 1.

[0007] Furthermore, the installation and use of the rear cover of the launch tube are as follows:

[0008] Furthermore, the rear end ring is glued to the launch tube body as one, and the sealing between the bonding interface is achieved by the junction of the rectangular annular groove provided on the rear end ring and the launch tube body (sealing glue groove) and the epoxy resin glue.

[0009] Furthermore, after the missile is loaded into the launch tube, it is positioned and locked by a locking mechanism, and then rotated and installed into the inner pressure ring until the end surface of the missile is pressed tightly to achieve the limiting function.

[0010] Furthermore, the fragile cover piece is installed into the outer pressure ring, and then integrally rotated and sleeved on the rear end ring until the O-ring is compressed and deformed, thereby realizing the sealing function of the rear cover.

[0011] Furthermore, before the missile is launched, the locking mechanism releases the mechanical lock on the missile, and the inner pressure ring blocks the tail of the missile to prevent the missile from moving backwards under the action of gravity.

[0012] Furthermore, when the missile is launched, the engine is working, the gas flow breaks through the fragile cover plate, and the gas flow discharge channel is opened. In the present invention, the negative windward area of ​​the tail gas flow channel only accounts for 0.8-0.9% of the area of ​​the entire launch tube tail channel.

[0013] The present invention has the beneficial effects of:

[0014] 1. The threaded connection limit structure is adopted to make the tail limit mechanism axially adjustable, eliminating the assembly gap caused by the structural processing error between the missile and the launch tube, and realizing the limit function of the missile tail.

[0015] 2. The rear cover is a fragile cover, which uses the engine gas flow as the crushing power source. No additional mechanism is required to provide power. It has the advantages of simple structure, low cost and high reliability.

[0016] 3. When the space of a small-caliber missile launch tube is limited, the gas flow discharge channel is released as much as possible, which solves the problem of excessive recoil after missile launch, which is not conducive to portable launch by a single soldier group, and improves the stability of the missile's exit posture. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 is a cross-sectional view of the rear cover structure of the present invention;

[0018] Figure 2 It is the front view and right view of the inner pressure ring 2.

[0019] In the accompanying drawings, the same reference numerals are used to denote the same elements or structures, wherein:

[0020] 1-rear end ring, 2-inner pressure ring, 3-outer pressure ring, 4-fragile cover plate, 5-O-ring, 6-launch cylinder, 7-missile, 8-rectangular annular groove, 9-inner thread connection, 10-outer thread connection, 11-limiting boss, 12-tooling hole. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0022] like Figure 1 , Figure 2 As shown, an embodiment of the present invention is a fragile launch tube rear cover structure, including a rear end ring 1, an inner pressure ring 2, an outer pressure ring 3, a fragile cover piece 4, and an O-ring 5.

[0023] The rear end ring 1 is a concentric cylindrical ring structure, which is connected to the rear end outer surface of the launch tube 6 through the front end inner surface, and is bonded into one piece by epoxy resin glue. There are also three rectangular annular grooves 8 on the bonding surface (the rectangular annular grooves 8 on the bonding surface can have 2 to 5, and only three rectangular annular grooves 8 are used as an example in this embodiment.) The rectangular annular grooves 8 can improve the shear strength at the bonding surface and help ensure the sealing between the bonding interfaces.

[0024] The inner pressure ring 2 is connected to the inner thread of the rear end ring 1 by an outer thread, and the tooling is inserted into the tooling holes 12 on both sides of the inner pressure ring 2 to facilitate rotation operation until the limiting boss 11 presses the rear end surface of the missile 7. The mechanism has the function of axial adjustment, which can compensate for structural processing errors and eliminate gaps.

[0025] The fragile cover sheet 4 is made of aluminum foil film surface as the base material, and the film surface is composited with non-woven fabric and pre-made with cross-marks as weak links. The outer rings on both sides of the film surface are bonded and fixed with aluminum alloy pressure rings. The fragile cover sheet 4 is placed on the inner ring of the outer pressure ring 3, and the O-ring 5 is rotated and pressed through the external thread connection 10 to achieve the sealing of the back cover.

[0026] It is easy to understand that after the rear cover structure is assembled, the only thing that protrudes from the inner surface of the launch tube is the limiting boss 11 structure of the inner pressure ring 2, which releases the tail gas flow channel to the maximum extent. The negative windward area of ​​the tail gas flow channel only accounts for 0.8-0.9% of the area of ​​the entire launch tube tail channel. At the same time, the limiting boss 11 is symmetrically arranged in structure, and the gas flow impact force is reasonably distributed.

[0027] The technical parameters achieved are as follows: Axial adjustment limit mechanism, the adjustment range reaches ±2mm, which can cover the error range of the missile and the launch tube assembly size. The membrane breaking pressure of the fragile fragments is 0.04Mpa-0.08Mpa, and the membrane breaking pressure value can be adjusted through reasonable design. The windward area of ​​the gas blocking part is 147.7mm 2 , accounting for only 0.85% of the entire launch tube tail channel area, and the gas channel is basically completely open.

[0028] Those skilled in the art will easily understand that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A launch tube rear cover structure, characterized in that: It includes a rear end ring, an inner pressure ring, an outer pressure ring, a fragile cover plate, an O-ring and a tail gas flow channel; the rear end ring is the main body of the rear cover, and is provided with an inner and outer double thread structure, the rear end ring is a concentric cylindrical ring structure, the front end inner profile of the rear end ring is sleeved with the outer profile of the rear end of the launch tube body, and a rectangular annular groove is provided at the junction with the launch tube body; the inner thread cooperates with the inner pressure ring, the outer thread cooperates with the outer pressure ring, and the end face of the rear end ring is provided with an O-ring installation groove; the inner pressure ring has symmetrically arranged limiting bosses inside; the outer pressure ring is placed on the outer ring of the rear end ring, and forms a sealing link with the fragile cover plate and the O-ring; The outer thread of the inner pressure ring matches the inner thread of the rear end cover, and is rotated by means of the tooling hole until the limiting boss presses the rear end face of the missile; The breakable cover piece is arranged at the inner circle of the outer pressure ring, and the outer thread of the rear end ring cooperates with the inner thread of the outer pressure ring to press the O-ring to seal the rear cover.

2. The rear cover structure of the launch tube according to claim 1, characterized in that: There are 2 to 5 rectangular annular grooves arranged at the junction of the rear end ring and the launch tube body, and the rear end ring and the launch tube body are glued into one body.

3. The rear cover structure of the launch tube according to claim 1, characterized in that: The breakable cover sheet is based on an aluminum foil membrane surface, on which a non-woven fabric is composited and pre-engraved with weak links, and the outer circles on both sides of the membrane surface are bonded and fixed with aluminum alloy pressure rings.

4. The rear cover structure of the launch tube according to claim 1, characterized in that: It also includes a tail gas flow channel, and the passive windward area of ​​the tail gas flow channel only accounts for 0.8-0.9% of the area of ​​the entire launch tube tail channel.

5. The rear cover structure of the launch tube according to claim 1, characterized in that: The O-type sealing ring is made of silicone rubber.

6. A method for installing and using a rear cover structure of a launch tube, comprising a rear end ring, an inner pressure ring, an outer pressure ring, a fragile cover plate, an O-ring and a tail gas flow channel; the rear end ring adopts a structural design scheme of inner and outer double threads, the rear end ring is a concentric cylindrical ring structure, the front end inner profile of the rear end ring is sleeved with the outer profile of the rear end of the launch tube body, and the rear end ring is provided with a rectangular annular groove at the junction with the launch tube body; the inner thread cooperates with the inner pressure ring, the outer thread cooperates with the outer pressure ring, and the end face of the rear end ring is provided with an O-ring installation groove; the inner pressure ring has symmetrically arranged limiting bosses inside, and adopts a threaded limiting structure with an axially adjustable function. It is used in combination with thread locking glue during installation to prevent loosening; the outer pressure ring is installed on the outer ring of the rear end ring, and forms a sealing link with the fragile cover plate and the O-ring to ensure the sealing of the rear cover of the launch tube; the fragile cover plate is pre-engraved with a weak link, which can be broken under the action of the engine gas flow; the O-ring is installed in the sealing groove of the rear end ring; The installation and use of the launch tube rear cover structure is as follows: 1) The rear end ring is glued to the launch tube body as one, and the sealing between the bonding interface is achieved by the O-ring arranged on the rear end ring, the rectangular annular groove arranged on the rear end ring and the junction of the launch tube body and the epoxy resin glue; 2) After the missile is loaded into the launch tube, it is first positioned and locked by the locking mechanism, and then rotated to install the inner pressure ring. The outer thread of the inner pressure ring matches the inner thread of the rear end cover, and the tooling hole is used to rotate and operate until the limiting boss presses the rear end face of the missile to realize the limiting function; 3) Install the fragile cover piece into the outer pressure ring, and then rotate it as a whole to fit on the rear end ring until the O-ring is compressed and deformed to achieve the sealing function of the rear cover; 4) Before the missile is launched, the locking mechanism releases the mechanical lock on the missile, and the inner pressure ring blocks the tail of the missile to prevent the missile from moving backwards under the action of gravity; 5) When the missile is launched, the engine is working, the gas flow breaks through the fragile cover plate, and the gas flow discharge channel is opened. The passive windward area of ​​the tail gas flow channel only accounts for 0.8-0.9% of the area of ​​the entire launch tube tail channel.

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