Guiding groove type composite concentric launching tube

Abstract

The application relates to a concentric launching cylinder structure with a guide groove composite material, which comprises a cylinder body, a baffle and a flow guide base; wherein the cylinder body is integrally formed by an outer cylinder, an inner cylinder and connecting rib plates using a composite material; the inner cylinder is a non-closed circular structure and provides a pitching and yawing launching orientation for a missile; two adjacent connecting rib plates form a guide groove, which provides a rolling direction guide for missile launching and also provides installation space for a cylinder-missile mechanical locking mechanism and an electrical connection separation mechanism; a sector space formed by the inner cylinder, the outer cylinder and the connecting rib plates serves as a gas exhaust passage of the concentric cylinder; the bottom of the cylinder body is provided with the baffle, the baffle is provided with sector holes corresponding to the gas exhaust passage of the cylinder body around the baffle, and the baffle is used for gas exhaust; the baffle is provided with a circular hole in the center, and the missile engine gas passes through the center circular hole of the baffle and is turned over at the flow guide base, and the baffle is used for preventing the reflection airflow from entering the inner cylinder of the launching cylinder.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of missile launching device, and particularly relates to a guide groove type composite concentric launching cylinder. BACKGROUND

[0002] The concentric cylinder is used for launching a missile by adopting two-layer cylinder walls to provide initial launching guidance for the missile and provide a forward exhaust passage for engine gas. The engine gas flow of the missile is turned by 180 degrees by the guide effect of the bottom guide cone, enters the gap between the inner and outer cylinders, and is finally exhausted to the atmosphere through the front end of the launching cylinder. The concentric cylinder has the advantages of independent gas exhaust and independent electronic equipment, and is therefore safe. Each concentric cylinder is an independent launching unit, and has higher universality and maintainability.

[0003] However, due to the strength requirement of the concentric cylinder during storage and transportation, the exhaust requirement of high-temperature gas flow during launching, and the structure form limitation of the traditional concentric cylinder, the inner cylinder of the traditional concentric cylinder is a complete cylinder structure made of metal material, and this type of concentric cylinder cannot directly provide roll direction limiting for the missile.

[0004] The authorized patent CN105910492B “Vertical hot launching inner circle outer square concentric cylinder structure of winged missile” relates to an inner circle outer square concentric cylinder structure. The concentric cylinder structure realizes the concentric cylinder launching of the winged missile by setting inner-outer cylinder connecting partitions at four wing movement channels. The patent aims to realize the vertical hot launching of the concentric cylinder of the large-diameter winged missile. The wing movement channel is formed in the non-closed area of the inner cylinder, and the missile, single wing and inner cylinder do not interfere with each other, and an adapter is needed to adjust the gap. The launching cylinder limits the roll direction movement by installing guide rails inside the launching cylinder, which needs secondary assembly, increases production cost, and has high requirements on machining precision.

[0005] The published patent CN202110527286.9 “Composite concentric cylinder structure” relates to a concentric cylinder structure in which the inner and outer cylinders are both circular and are formed of composite materials, which reduces the weight of the concentric cylinder. In the patent, a metal structure is embedded in the concentric cylinder, and the forming method is complex.

[0006] According to the search results of relevant literature and patents, there is no report on the guide groove type composite concentric launching cylinder. SUMMARY

[0007] The technical problem solved by the application is to provide a guide groove type composite concentric cylinder structure to solve the roll direction guidance problem of the missile during launching of the concentric cylinder.

[0008] The technical scheme of the present application is: a concentric launching cylinder structure with guide grooves and composite materials, comprising a cylinder body, a baffle and a flow guide base; wherein the cylinder body is integrally formed by an outer cylinder, an inner cylinder and connecting rib plates using composite materials; the inner cylinder is a non-closed circular structure, providing a pitching and yawing launching orientation for a missile; two adjacent connecting rib plates form a guide groove, providing a rolling direction guide for missile launching, and also providing installation space for a cylinder-missile mechanical locking mechanism and an electrical connection separation mechanism; a fan-shaped space formed by the inner cylinder, the outer cylinder and the connecting rib plates serves as a gas exhaust passage of the concentric cylinder; the bottom of the cylinder body is provided with the baffle, the baffle is provided with fan-shaped holes corresponding to the gas exhaust passage of the cylinder body around the baffle, for gas exhaust; the center of the baffle is provided with a circular hole, after the missile engine gas passes through the center circular hole of the baffle, the gas is turned over at the flow guide base, and the baffle is used to prevent the reflection gas flow from entering the inner cylinder of the launching cylinder.

[0009] Preferably, the flow guide base is installed at the rear end of the concentric launching cylinder, the inner part of the flow guide base is a center-protruding flow guide cone, and the outer part is a hemispherical structure; the missile engine gas flow is bounced by the inner part of the flow guide base, and is turned by 180° to enter the gas exhaust passage of the cylinder body.

[0010] Preferably, the cone angle of the flow guide cone of the flow guide base is 25°-35°, the top SR8-SR12 of the cone angle is a hemispherical head, and the bottom sides are circular arc structures for transition; the outer arc of the flow guide cone is tangent to the inner wall of the outer cylinder, and the gas exhaust is smooth.

[0011] Preferably, the distance between the vertex of the flow guide cone and the rear end surface of the baffle is 25mm-30mm.

[0012] Preferably, the number of the fan-shaped spaces is at least 2, and according to the missile layout, a missile body surface protruding object, a cylinder-missile mechanical locking mechanism and an electrical connection separation mechanism are installed in the guide groove.

[0013] Preferably, the number of the fan-shaped spaces is preferably 4.

[0014] Preferably, the fan-shaped holes on the baffle correspond to the flame exhaust passage formed by the inner cylinder, the outer cylinder and the connecting rib plates, and other non-holed parts effectively prevent the turned gas flow from flowing into the inner cylinder, reducing the ablation of the gas to the missile body.

[0015] Preferably, the baffle and the flow guide base are installed on the cylinder body using radial screws.

[0016] Preferably, before the cylinder body is bonded, a resin-based heat-resistant coating is sprayed on the outer surface of the core mold; after the cylinder body 1 is demolded, a heat-resistant coating is formed at the inner cylinder, the outer cylinder and the connecting rib plates, so that the inner cylinder, the outer cylinder and the connecting rib plates have good heat-resistant capability.

[0017] The rolling orientation of the missile is realized by the cooperation of the guide groove formed by the two adjacent connecting rib plates and the gap between the sliding block on the outer surface of the missile body, and the pitching and yawing orientation of the missile is realized by the cooperation of the inner wall of the inner cylinder and the centering part of the missile body.

[0018] Compared with the prior art, the application has the beneficial effects that the application provides a guide groove type composite concentric launching cylinder, and proposes a new concentric cylinder launching scheme with rolling orientation function.

[0019] (1) The application has novel concept, ingenious design, simple mechanism, convenient operation, and is suitable for the concentric cylinder launching demand of the missile with rolling orientation demand; the pitching and yawing orientation of the missile is realized by the cooperation of the inner wall of the inner cylinder and the centering part of the missile body, and the guide rail and adapter do not need to be designed separately, and the structure is simpler.

[0020] (2) The application uses a non-closed inner cylinder structure, which not only meets the rolling orientation demand of the concentric cylinder launching of the missile, but also provides installation space of the radial mechanical locking mechanism and the radial electrical connection separation mechanism of the launching cylinder and the missile, and placement space of the protrusions on the outer surface of the missile body.

[0021] (3) The application uses composite material integral molding technology, which not only reduces the weight of the concentric cylinder compared with the traditional metal concentric cylinder, but also simplifies the processing technology of the concentric cylinder and reduces the cost.

[0022] (4) The application combines the specific design of the flow guide base with the design of the baffle structure, so that the gas flow emitted by the missile engine is bounced by the flow guide cone of the flow guide base, turns 180° and then enters the gas exhaust passage of the cylinder body, effectively prevents the reflected gas flow from entering the inner cylinder of the launching cylinder, and realizes smooth gas exhaust. BRIEF DESCRIPTION OF DRAWINGS

[0023] Fig. 1 It is a structural layout drawing of the concentric launching cylinder of the application;

[0024] Fig. 2 It is a cylinder body sectional view of the application;

[0025] Fig. 3 It is a baffle structure view of the application;

[0026] Fig. 4 It is a flow guide base structure view of the application;

[0027] Fig. 5 It is a working principle view of the application. DETAILED DESCRIPTION

[0028] The application will be further described below in combination with the embodiments.

[0029] The structural composition and working principle of the application are shown in Figs. 1-5 .

[0030] 1) Structure introduction

[0031] A concentric launching cylinder structure with guide groove composite material comprises a cylinder body 1, a baffle 2, a flow guide base 3 and the like. The cylinder body is composed of an outer cylinder 4, an inner cylinder 5 and connecting rib plates 6. The inner cylinder, the outer cylinder and the connecting rib plates are integrally formed by using composite material. The inner cylinder is a non-closed circular structure, which provides the missile with a pitch and yaw launching orientation. Two adjacent connecting rib plates form a guide groove, which provides the missile launching with a roll direction guide, and also provides installation space for the cylinder-missile mechanical locking mechanism and the electrical connection separation mechanism. The fan-shaped space formed by the inner cylinder, the outer cylinder and the connecting rib plates serves as a gas exhaust passage of the concentric cylinder.

[0032] The cylinder body is provided with a baffle at the bottom, the center of the baffle is designed with a circular hole, and four fan-shaped holes corresponding to the gas exhaust passage of the cylinder body 1 are designed around the baffle, which are used for gas exhaust. The center of the baffle is designed with a circular hole, the missile engine gas passes through the center circular hole of the baffle, and then is turned over at the flow guide base. At the same time, the non-hole area of the baffle can effectively prevent the bottom reflected airflow from entering the inner cylinder, thereby reducing the ablation of the gas to the missile body. The other parts of the baffle 2 are closed structures, which prevent the reflected airflow from entering the inner cylinder of the launching cylinder.

[0033] The concentric launching cylinder is provided with a flow guide base at the rear end, the inside of the flow guide base is a center-protruding flow guide cone, and the outside is a hemispherical structure. The gas flow emitted by the missile engine is bounced by the inside circular cone of the flow guide base, and then enters the gas exhaust passage of the cylinder body after being turned by 180°. The cone angle of the flow guide cone of the flow guide base is 30°, the top of the cone angle is a SR10mm hemispherical head, the bottom sides are circular arc structures for transition, the outer arc of the flow guide cone is tangent to the inner wall of the outer cylinder, and the distance between the vertex of the flow guide cone and the rear end surface of the baffle is 30mm, so that the gas exhaust is smooth.

[0034] In a preferred embodiment of the present application, a resin-based heatproof coating is sprayed on the outer surface of the core mold before the cylinder body 1 is bonded, and the heatproof coating is formed at the inner cylinder, the outer cylinder and the connecting rib plates after the cylinder body 1 is demolded, so that the inner cylinder, the outer cylinder and the connecting rib plates have good heatproof capability.

[0035] 2) Structure installation scheme

[0036] When the concentric cylinder is installed, the outer cylinder at the rear end of the cylinder body 1 is designed with a radial threaded connection interface, the baffle 2 is installed at the rear end of the cylinder body 1 in a sleeving manner (wherein the four fan-shaped holes of the baffle 2 correspond to the fan-shaped exhaust space formed by the outer cylinder 4, the inner cylinder 5 and the connecting rib plates 6 in the cylinder body 1), and the flow guide base 3 is installed at the rear end of the baffle 2 in a sleeving manner. The baffle 2 and the flow guide base 3 are installed on the cylinder body 1 by using radial screws, which has the advantages of simple installation structure, easy maintenance and less protrusions outside the cylinder.

[0037] The radial electrical connection separation mechanism, the mechanical locking mechanism of the cylinder, the slider on the surface of the missile body, the cable cover and other protrusions are arranged in the guide groove formed by the two connecting rib plates 6 in the barrel 1. The gap between the guide groove formed by the two adjacent connecting rib plates and the slider on the surface of the missile body is matched to realize the roll orientation of the missile, and the cooperation between the inner wall of the inner cylinder and the centering part of the missile body realizes the pitch and yaw orientation of the missile. Therefore, it is not necessary to separately design a guide rail and an adapter, and the structure is simpler.

[0038] 2) Launching process

[0039] After the missile is loaded into the launching barrel, the outer surface of the missile body is radially supported by the inner cylinder 5, and the corresponding mechanical locking mechanism is axially supported and limited. During launching, the high-temperature gas jetted out by the engine nozzle passes through the center hole of the baffle 2, is reversed by 180° through the conical flow guide cone of the flow guide base 3, and is discharged from the front end of the launching barrel through the four fan-shaped holes of the baffle 2 and the four fan-shaped exhaust channels of the barrel 1. The baffle plays a blocking role on the reversed gas to prevent the reversed gas from entering the space of the inner cylinder 5. During the forward movement of the missile out of the barrel, the guide groove of the launching barrel realizes the limiting and guiding of the roll direction of the missile through the limiting action on the slider of the missile body, and the limiting action of the inner cylinder of the launching barrel on the centering part of the missile body realizes the limiting and guiding of the pitch and yaw directions of the missile, so as to ensure the attitude accuracy of the missile when it is out of the barrel. At the same time, according to the requirement of launching speed, the aperture of the center hole of the baffle can be designed to make the concentric cylinder provide appropriate ejection force.

[0040] The undisclosed technology of the present application is common knowledge to those skilled in the art.

Claims

1. A concentric launch tube structure with a guide groove made of composite material, characterized in that... The system includes a cylinder, baffle, and flow guide base. The cylinder is integrally formed from composite materials, consisting of an outer cylinder, an inner cylinder, and connecting stiffeners. The inner cylinder is a non-enclosed circular structure that provides pitch and yaw launch orientation for the missile. Two adjacent connecting stiffeners form a guide groove to guide the roll direction of the missile launch and also provide installation space for the mechanical locking mechanism and electrical connection separation mechanism. The fan-shaped space formed by the inner cylinder, outer cylinder, and connecting stiffeners serves as the gas exhaust channel for the concentric cylinder. A baffle is installed at the bottom of the cylinder, with fan-shaped holes around its perimeter corresponding to the gas exhaust channel for gas exhaust. A circular hole is designed in the center of the baffle, through which the missile engine gas passes and then tumbles at the flow guide base. The baffle also prevents reflected airflow from entering the inner cylinder of the launch tube. The guide base is installed at the rear end of the concentric launch tube. The inside of the guide base is a centrally protruding guide cone, and the outside is a hemispherical structure. The exhaust gas flow ejected by the missile engine is deflected by the guide cone inside the guide base, turns 180° and enters the exhaust gas channel of the tube. The guide cone of the guide base has a cone angle of 25° to 35°. The top of the cone angle, SR8 to SR12, is a hemispherical head, and the bottom two sides are rounded transition structures. The outer arc of the guide cone is tangent to the inner wall of the outer cylinder, so the gas exhaust is smooth. The distance between the apex of the guide cone and the rear end face of the baffle is 25mm to 30mm; The fan-shaped holes on the baffle correspond to the exhaust channels formed by the inner cylinder, outer cylinder, and connecting stiffeners. Other un-holeed parts effectively prevent the turbulent airflow from flowing into the inner cylinder, reducing the ablation of the gas on the missile body. Before the cylinder is bonded, a resin-based heat-resistant coating is sprayed on the outer surface of the core mold. After the cylinder 1 is demolded, a heat-resistant coating is formed on the inner cylinder, outer cylinder, and connecting stiffener, giving the inner cylinder, outer cylinder, and connecting stiffener good heat resistance.

2. The concentric launching tube structure according to claim 1, characterized in that: The number of the aforementioned fan-shaped spaces is at least two. According to the missile layout, protrusions on the missile surface, a cannon-missile mechanical locking mechanism, and an electrical connection separation mechanism are installed in the guide slot.

3. The concentric launching tube structure according to claim 1, characterized in that: The number of sector-shaped spaces is preferably four.

4. The concentric launching tube structure according to claim 1, characterized in that: Both the baffle and the flow guide base are mounted on the cylinder using radial screws.

5. The concentric launching tube structure according to claim 1, characterized in that: The missile roll orientation is achieved by utilizing the gap fit between the guide groove formed by two adjacent connecting ribs and the slider on the outer surface of the missile body, and the pitch and yaw orientation of the missile is achieved by utilizing the fit between the inner wall of the inner cylinder and the centering part of the missile body.

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