Combustion chamber shell of solid rocket engine

Abstract

The invention provides a solid rocket engine combustion chamber shell, and relates to the technical field of solid rocket engines. The device comprises an injection molding cylinder body, the metal front joint is limited in the first port of the injection molding cylinder body; and the metal rear joint is arranged at the second port of the injection molding cylinder body in a sleeving manner and is limited at the second port of the injection molding cylinder body. The injection molding barrel body is manufactured through the plastic injection molding process, the weight is light, the overall performance and large-scale production of the guided missile are facilitated, the injection molding barrel body, the front metal connector and the rear metal connector are integrally formed in an injection molding mode, the front metal connector and the rear metal connector are limited on the injection molding barrel body, and the overall structural strength and connection stability are improved. On the whole, the connecting structure is low in cost, small in manufacturing difficulty, high in connecting strength and easy to produce on a large scale.

Description

Technical Field

[0001] The invention relates to the technical field of solid rocket engines, and in particular to a combustion chamber casing of a solid rocket engine. Background Art

[0002] The combustion chamber shell is one of the important components in the structure of solid rocket engines. It is a tank for loading solid propellants, a place for propellant combustion, and also a component of the missile body. However, the metal engine is heavy, which affects the overall performance of the missile, and the material utilization rate is low during the processing, the production cost is high, and it is not conducive to large-scale production; the winding fiber in the composite shell is expensive, and the cost is mainly generated in the mold part. The larger the aspect ratio of the product, the more difficult it is to make the mold, and the interface in each step of the molding process is often guaranteed by bonding, which is difficult to detect and repair.

[0003] Therefore, there is an urgent need for a solid rocket engine combustion chamber casing that is low in cost, easy to manufacture, has high connection strength, and is easy to mass produce. Summary of the invention

[0004] The purpose of the present invention is to provide a solid rocket engine combustion chamber casing, which solves the technical problems of high cost and great manufacturing difficulty in the prior art. The preferred technical solutions among the many technical solutions provided by the present invention can produce many technical effects as described below.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] The present invention provides a solid rocket engine combustion chamber casing, comprising:

[0007] Injection molded barrel;

[0008] A metal front joint, wherein the metal front joint is limited in the first port of the injection molding barrel;

[0009] A metal rear joint is sleeved on the second end of the injection molding cylinder and is limited at the second end of the injection molding cylinder.

[0010] Preferably, the outer peripheral side of the metal front joint is bonded to the inside of the first port of the injection molding cylinder body; the inner side wall of the metal rear joint is bonded to the outside of the second port of the injection molding cylinder body.

[0011] Preferably, it also includes:

[0012] A front interface, wherein the first port of the injection molding barrel is configured as the front interface, and the metal front joint is limited within the front interface.

[0013] Preferably, it also includes:

[0014] a first annular boss, the first annular boss being coaxially disposed on the outer peripheral side of the metal front joint;

[0015] A first annular groove is provided in the front interface, and the first annular boss is fitted in the first annular groove.

[0016] Preferably, it also includes:

[0017] A first limiting ring, the first limiting ring is coaxially fixedly connected to one end of the metal rear joint close to the metal front joint;

[0018] A second annular groove is provided on the circumference of the injection molding cylinder, and the first limiting ring is fitted in the second annular groove.

[0019] Preferably, it also includes:

[0020] A connecting ring is coaxially fixedly connected between the metal rear joint and the first limiting ring, and the wall thickness of the connecting ring is smaller than the wall thickness of the first limiting ring.

[0021] Preferably, the cross-sections of the connecting ring and the first limiting ring are convex.

[0022] Preferably, it also includes:

[0023] A second annular boss, a plurality of the second annular bosses are axially arranged on the side wall of the metal rear joint;

[0024] A third annular groove, a plurality of the third annular grooves are axially opened on the second end circumferential side of the injection molding barrel, and a plurality of the second annular bosses are adapted in the third annular grooves.

[0025] Preferably, it also includes:

[0026] The second limiting ring is coaxially fixedly connected to one end of the metal rear joint close to the metal front joint and is embedded in the outer side wall of the injection molding cylinder.

[0027] Preferably, it also includes:

[0028] Vias, a plurality of the vias are circumferentially arranged between the second limiting ring and the metal rear connector.

[0029] In the technical solution provided by the present invention, the injection-molded barrel body is made by plastic injection molding process, which is light in weight and beneficial to the overall performance and large-scale production of the missile. The injection-molded barrel body is integrally injection-molded with the metal front joint and the metal rear joint, and the metal front joint and the metal rear joint are respectively limited on the injection-molded barrel body, thereby improving the overall structural strength and connection stability. Overall, the present application has low cost, low manufacturing difficulty, high connection strength, and is easy to mass-produce. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0031] Figure 1 is a cross-sectional schematic diagram of embodiment 1 of the present invention;

[0032] Figure 2 It is a cross-sectional schematic diagram of embodiment 2 of the present invention.

[0033] In the figure, 1 is the barrel; 2 is the front joint; 3 is the rear joint; 4 is the first annular boss; 5 is the first annular groove; 6 is the front interface; 7 is the second annular groove; 8 is the first limiting ring; 9 is the connecting ring; 10 is the second annular boss; 11 is the third annular groove; 12 is the second limiting ring; 13 is the through hole. DETAILED DESCRIPTION

[0034] To make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other implementation methods obtained by ordinary technicians in this field without creative work belong to the scope of protection of the present invention.

[0035] Example 1, reference Figure 1 A specific embodiment of the present invention provides a solid rocket engine combustion chamber casing, comprising:

[0036] Injection molding barrel 1;

[0037] A metal front connector 2, the metal front connector 2 is limited in the first port of the injection molding barrel 1;

[0038] The metal rear joint 3 is sleeved on the second end of the injection molding barrel 1 and is limited at the second end of the injection molding barrel 1 .

[0039] The metal engine is heavy, which affects the overall performance of the missile, and the material utilization rate is low during the processing, the production cost is high, and it is not conducive to large-scale production; the winding fiber in the composite material shell is expensive, and the cost is mainly generated in the mold part, and the larger the aspect ratio, the greater the difficulty of making the product mold, and the interface is often ensured by bonding during the molding process of each step, and the bonding detection is difficult and the repair difficulty is high. In the present application, the injection molding barrel 1 is made by plastic injection molding technology, which is light in weight, is conducive to the overall performance of the missile and large-scale production, wherein the injection molding barrel 1 is integrally injection molded with the metal front joint 2 and the metal rear joint 3, and the metal front joint 2 and the metal rear joint 3 are respectively limited on the injection molding barrel 1, which improves the overall structural strength and connection stability. On the whole, the present application has low cost, low difficulty in making, high connection strength, and is easy to mass produce.

[0040] The metal rear connector 3 may be located outside the second port of the injection molding barrel 1 or inside the second port of the injection molding barrel 1 , depending on actual conditions.

[0041] According to a further optimized solution, the outer peripheral side of the metal front joint 2 is bonded to the inside of the first port of the injection molding barrel 1 ; and the inner side wall of the metal rear joint 3 is bonded to the outside of the second port of the injection molding barrel 1 .

[0042] By bonding, the roughness is increased at the positions where the metal front joint 2 and the metal rear joint 3 are in contact with the injection molding barrel 1, which helps to improve the connection strength.

[0043] Further optimization plans also include:

[0044] The front interface 6 , the first port of the injection molding barrel 1 is set as the front interface 6 , and the metal front joint 2 is limited in the front interface 6 .

[0045] Further optimization plans also include:

[0046] A first annular boss 4, which is coaxially arranged on the outer peripheral side of the metal front joint 2; the first annular boss 4 and the metal front joint 2 are an integral structure;

[0047] The first annular groove 5 is provided in the front interface 6 , and the first annular boss 4 is adapted in the first annular groove 5 .

[0048] According to the first annular boss 4, a first annular groove 5 is formed on the injection molding barrel 1 after injection molding is completed. Under the mutual cooperation of the first annular groove 5 and the first annular boss 4, the connection stability and structural strength of the metal front joint 2 and the injection molding barrel 1 are effectively improved.

[0049] Between the metal rear joint 3 and the injection molding barrel 1 are arranged:

[0050] A first limiting ring 8, the first limiting ring 8 is coaxially fixedly connected to one end of the metal rear joint 3 close to the metal front joint 2;

[0051] The second annular groove 7 is provided on the outer circumference or the inner circumference of the injection molding barrel 1 , and the first limiting ring 8 is fitted in the second annular groove 7 .

[0052] According to the first limiting ring 8, a second annular groove 7 is formed on the injection molding barrel 1 after the injection molding is completed. Under the mutual cooperation of the second annular groove 7 and the first limiting ring 8, the connection stability and structural strength of the metal rear joint 3 and the injection molding barrel 1 are effectively improved.

[0053] Further optimization plans also include:

[0054] The connecting ring 9 is coaxially fixedly connected between the metal rear joint 3 and the first limiting ring 8. The wall thickness of the connecting ring 9 is smaller than the wall thickness of the first limiting ring 8. The cross-sections of the connecting ring 9 and the first limiting ring 8 are convex.

[0055] like Figure 1 As shown, such an arrangement helps to enhance the connection strength between the metal rear joint 3 and the injection molding barrel 1 in the radial and axial directions.

[0056] Further optimization plans also include:

[0057] A second annular boss 10, wherein a plurality of second annular bosses 10 are axially arranged on the inner side wall or the outer side wall of the metal rear joint 3; the plurality of second annular bosses 10 and the metal rear joint 3 are an integral structure;

[0058] A third annular groove 11 , a plurality of third annular grooves 11 are axially opened on the outer circumference or inner circumference of the second end of the injection molding barrel 1 , and a plurality of second annular bosses 10 are fitted in the third annular grooves 11 .

[0059] like Figure 1 As shown, such an arrangement further enhances the connection strength between the metal rear joint 3 and the injection molding barrel 1 in the radial and axial directions.

[0060] Embodiment 2, as Figure 2 As shown, the difference between this embodiment and embodiment 1 is that the following is arranged between the metal rear connector 3 and the injection molding barrel 1:

[0061] The second limiting ring 12 is coaxially fixedly connected to one end of the metal rear joint 3 close to the metal front joint 2, and is embedded in the outer wall of the injection molding barrel 1; a through hole 13, a plurality of through holes 13 are circumferentially arranged between the second limiting ring 12 and the metal rear joint 3.

[0062] After the injection molding of the injection molding barrel 1 is completed, the injection liquid wraps the second limiting ring 12 and passes through the through hole 13. After the molding is cooled, the second limiting ring 12 is embedded in the outer wall of the injection molding barrel 1, which helps to improve the axial and circumferential connection stability and strength between the metal rear joint 3 and the injection molding barrel 1.

[0063] Before the injection molding of the injection molding barrel 1 begins, the metal front joint 2 and the metal rear joint 3 are first installed in the cavity of the injection mold. After the injection molding process is completed, the injection molding barrel 1, the metal front joint 2 and the metal rear joint 3 are integrally formed.

[0064] The material safety factor of the injection molding barrel 1 is 1.5, the material safety factor of the metal front joint 2 and the metal rear joint 3 is 1.3, the allowable stress of the injection molding barrel 1 material is 340 / 1.5=226Mpa, and the allowable stress of the metal front joint 2 and the metal rear joint 3 material is 460 / 1.3=353Mpa. After stress analysis, the injection molding barrel 1 does not exceed 226MPa at any place, and the maximum stress is about 220MPa, which occurs in the middle section of the barrel; the stress of the metal front joint 2 and the metal rear joint 3 does not exceed the maximum allowable stress of their materials. The local stress concentration position can be optimized in the actual production process, which has little impact on the product.

[0065] After mold flow analysis, the products in the two embodiments have good injection molding processability. The air pocket is located at the edge, which is conducive to exhaust and will not cause air entrapment, so it will not affect the structural strength of the product design. At the same time, the above analysis can be used to guide the actual production process and avoid possible risks in production in advance.

[0066] It should be noted that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", etc. used herein to indicate the orientation or position relationship is based on the orientation or position relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as a limitation on the present application. In addition, the terms "first", "second", "third", etc. are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0067] In the description of this article, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to the specific circumstances.

[0068] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention should be based on the protection scope of the claims.

Claims

1. A solid rocket engine combustion chamber casing, characterized in that: include: Injection molded barrel (1); A metal front joint (2), wherein the metal front joint (2) is limited in a first port of the injection molding barrel (1); A metal rear joint (3), wherein the metal rear joint (3) is sleeved on the second end of the injection molding barrel (1) and is limited at the second end of the injection molding barrel (1).

2. The solid rocket motor combustion chamber casing according to claim 1, characterized in that: The outer peripheral side of the metal front joint (2) is bonded to the inside of the first port of the injection molding barrel (1); and the inner side wall of the metal rear joint (3) is bonded to the outside of the second port of the injection molding barrel (1).

3. The solid rocket motor combustion chamber casing according to claim 1, characterized in that: Also includes: A front interface (6), wherein the first port of the injection molding barrel (1) is arranged as the front interface (6), and the metal front joint (2) is limited in the front interface (6).

4. The solid rocket motor combustion chamber casing according to claim 3, characterized in that: Also includes: A first annular boss (4), the first annular boss (4) being coaxially arranged on the outer peripheral side of the metal front joint (2); A first annular groove (5), wherein the first annular groove (5) is provided in the front interface (6), and the first annular boss (4) is adapted in the first annular groove (5).

5. The solid rocket motor combustion chamber casing according to any one of claims 1 to 4, characterized in that: Also includes: A first limiting ring (8), the first limiting ring (8) being coaxially fixedly connected to one end of the metal rear joint (3) close to the metal front joint (2); A second annular groove (7), wherein the second annular groove (7) is provided on the circumferential side of the injection molding barrel (1), and the first limiting ring (8) is adapted in the second annular groove (7).

6. The solid rocket motor combustion chamber casing according to claim 5, characterized in that: Also includes: A connecting ring (9), the connecting ring (9) is coaxially fixedly connected between the metal rear joint (3) and the first limiting ring (8), and the wall thickness of the connecting ring (9) is smaller than the wall thickness of the first limiting ring (8).

7. The solid rocket motor combustion chamber casing according to claim 6, characterized in that: The cross-sections of the connecting ring (9) and the first limiting ring (8) are convex.

8. The solid rocket motor combustion chamber casing according to claim 5, characterized in that: Also includes: A second annular boss (10), wherein a plurality of the second annular bosses (10) are axially arranged on the side wall of the metal rear joint (3); A third annular groove (11), a plurality of the third annular grooves (11) are axially opened on the second end circumferential side of the injection molding barrel (1), and a plurality of the second annular bosses (10) are adapted in the third annular grooves (11).

9. The solid rocket motor combustion chamber casing according to any one of claims 1 to 4, characterized in that: Also includes: A second limiting ring (12), the second limiting ring (12) is coaxially fixedly connected to one end of the metal rear joint (3) close to the metal front joint (2), and is embedded in the outer wall of the injection molding barrel (1).

10. The solid rocket motor combustion chamber casing according to claim 9, characterized in that: Also includes: Through holes (13), a plurality of the through holes (13) are circumferentially arranged between the second limiting ring (12) and the metal rear joint (3).

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