Solid rocket engine connecting structure and solid rocket engine

Abstract

The utility model provides a solid rocket engine connecting structure and a solid rocket engine, the solid rocket engine connecting structure comprises clamping blocks and fasteners, the clamping blocks are inserted into limiting grooves distributed in the circumferential direction of a combustion chamber shell and a spray pipe shell, and the clamping blocks are fixedly connected with the combustion chamber shell through the fasteners. According to the connecting structure, connection of the combustion chamber and the spray pipe under specific conditions is met, and under the conditions that the size and the weight are limited and the connecting reliability is guaranteed, the connecting structure commonly adopted by the solid rocket engine is simple, good in assembly manufacturability and easy to disassemble.

Description

Technical Field

[0001] The present application relates to the field of solid rocket technology, and in particular to a solid rocket engine connection structure and a fixed rocket engine. Background Art

[0002] A solid rocket engine is a chemical rocket engine that uses solid propellant. After the solid propellant is ignited, it burns in the combustion chamber, converting chemical energy into heat energy, producing high-temperature and high-pressure combustion products. The combustion products flow through the nozzle, where they expand and accelerate, and the heat energy is converted into kinetic energy, and are discharged from the nozzle at high speed to generate thrust. Therefore, when designing, it is necessary to ensure the reliability of the connection between the nozzle and the combustion chamber, taking into account the various load requirements of the flight mission.

[0003] At present, solid rocket engines often use structural connections such as threaded structures, flange structures, and retaining ring structures.

[0004] The main disadvantages of the threaded structure connection are: first, the nozzle shell and the combustion chamber shell need to be rotated when assembled, which can easily cause the ignition cable to twist and even damage. Second, it is difficult to disassemble when dissecting the wreckage and replacing the nozzle, which can easily cause thread damage.

[0005] The main drawbacks of the flange structure solution are: large connection mass and unsuitability for small solid rocket engines.

[0006] The existing patent publication number is CN203925780U, which discloses a solid rocket engine connection structure, specifically a clamp connection structure of a solid rocket engine, including two structural forms of a clamp petal with a support ear and a clamp petal without a support ear; the cross-sectional shape of the clamp is L-shaped, which can improve the stress state; the support ear on one side of the clamp with a support ear is fixed to the front and rear joints with bolts, and a boss is provided on the other side of the clamp with a support ear, which cooperates with the ignition device and the rectangular groove on the end face of the nozzle to play a role in circumferential positioning and transmitting torsional torque; the clamp petal petal structure is inclined plane division, the division surface of the clamp petal with a support ear is a positive "eight" shape, and the clamp petal without a support ear is an inverted "eight" shape; the clamp without a support ear is limited by the division surface; the clamp is installed in the clamp groove of the front joint and the rear joint.

[0007] The main disadvantages of the clamping ring connection structure are: poor assembly processability and difficulty in assembly.

[0008] Therefore, the technical problem that urgently needs to be solved is: in some application scenarios of solid rocket engines, it is necessary to make the connection structure commonly used in solid rocket engines simple, with good assembly processability and easier disassembly under the condition of limiting volume and weight and ensuring connection reliability. Utility Model Content

[0009] The purpose of the present application is to provide a solid rocket engine connection structure and a solid rocket engine, wherein the connection structure satisfies the connection between the combustion chamber and the nozzle under specific conditions, and under the conditions of limiting the volume and weight and ensuring the reliability of the connection, the connection structure commonly used in solid rocket engines is simple, has good assembly processability, and is easier to disassemble.

[0010] To achieve the above-mentioned purpose, as the first aspect of the present application, the present application provides a solid rocket engine connection structure, including: a clamping block and a fastener, the clamping block is inserted into a circumferentially distributed limiting groove of the combustion chamber shell and the nozzle shell, and the clamping block is fixedly connected to the combustion chamber shell through the fastener.

[0011] The solid rocket engine connection structure as described above, wherein the clamping block comprises a plurality of clamping blocks, and the plurality of clamping blocks are evenly spaced apart and arranged along the circumferential direction of the combustion chamber casing.

[0012] The solid rocket engine connection structure as described above, wherein the clamping block has a central hole, and the combustion chamber shell is provided with a connection hole,

[0013] The fastener passes through the connecting hole of the combustion chamber housing and the central hole of the clamping block.

[0014] The solid rocket engine connection structure as described above, wherein the fastener is a screw, the screw passes through the connection hole of the combustion chamber shell and is threadedly connected to the center hole of the block.

[0015] As a second aspect of the present application, the present application provides a solid rocket engine, comprising the solid rocket engine connection structure, a combustion chamber and a nozzle,

[0016] The combustion chamber comprises a combustion chamber housing, and an end surface of the combustion chamber housing has a first ring tooth structure.

[0017] The nozzle comprises a nozzle housing, and the end surface of the nozzle housing has a second ring tooth structure.

[0018] The nozzle housing and the combustion chamber housing are axially limitedly connected by a second ring gear structure and a first ring gear structure.

[0019] The solid rocket engine connection structure is limit-connected in the gaps of the first ring tooth structure and the second ring tooth structure.

[0020] The solid rocket motor as described above, wherein the combustion chamber casing has a rotating annular groove,

[0021] The rotating annular groove is distributed along the inner wall of the combustion chamber housing, and the rotating annular groove is located on a side of the first ring tooth structure close to the interior of the combustion chamber housing.

[0022] The second ring tooth structure is connected in the rotating ring groove.

[0023] The solid rocket motor as described above, wherein the first ring tooth structure includes a plurality of first latch teeth and a plurality of first notches,

[0024] A plurality of first latch teeth are evenly spaced apart along the circumferential direction of the combustion chamber housing, and a first notch is provided between two adjacent first latch teeth;

[0025] The second ring tooth structure passes through the first notch and is inserted into the rotating ring groove.

[0026] The solid rocket motor as described above, wherein the second ring tooth structure includes a plurality of second latch teeth and a plurality of second notches,

[0027] The second latching teeth are evenly spaced apart along the circumferential direction of the nozzle housing, and a second notch is provided between two adjacent second latching teeth;

[0028] The second latch tooth passes through the first notch and is inserted into the rotating ring groove. The second latch tooth rotates a certain angle in the rotating ring groove. The second latch tooth is limited on the inner side of the first latch tooth. The second notch is aligned with the first notch. The solid rocket engine connection structure is connected in the first notch and the second notch.

[0029] The solid rocket engine as described above, wherein the number of the second latching teeth is the same as the number of the first latching teeth, and the number of the second notches is the same as the number of the first notches.

[0030] The solid rocket motor as described above, wherein the blocking block is arc-shaped.

[0031] The beneficial effects achieved by this application are as follows:

[0032] (1) The nozzle housing of the present application is first installed into the combustion chamber housing through the notch, and then rotated at a certain angle, and the second latch tooth is limited inside the first latch tooth to complete the axial limit, and then the clamping block is installed in the first notch and the second notch, and the clamping block is fixed to the combustion chamber housing by screws to complete the circumferential limit. The connection structure of the present application has the advantages of simple structure, good assembly processability, easy disassembly, reliable connection, and is suitable for the beneficial effects of connecting the combustion chamber and the nozzle under specific conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the embodiments of the present application 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 recorded in the present application. For those skilled in the art, other drawings can also be obtained based on these drawings.

[0034] Figure 1 This is a schematic diagram of the structure of the card block of an embodiment of the present application.

[0035] Figure 2 It is a schematic diagram of the cross-sectional structure of the combustion chamber shell of an embodiment of the present application.

[0036] Figure 3 This is a schematic diagram of the end surface structure of the nozzle shell of an embodiment of the present application.

[0037] Figure 4 This is a schematic diagram of the solid rocket engine structure including a solid rocket engine connection structure according to an embodiment of the present application.

[0038] Figure 5 This is a schematic diagram of the structure of the connection between the nozzle shell and the combustion chamber shell in an embodiment of the present application.

[0039] Figure numerals: 1-block; 2-combustion chamber housing; 3-nozzle housing; 4-fastener; 11-center hole; 21-first latch tooth; 22-rotating ring groove; 23-first notch; 31-second latch tooth; 32-second notch. DETAILED DESCRIPTION

[0040] The following is a clear and complete description of the technical solutions in the embodiments of the present application in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0041] Embodiment 1

[0042] like Figure 1 and 4 As shown, the present application provides a solid rocket engine connection structure, including: a block 1 and a fastener 4, the block 1 is inserted into the limiting grooves distributed along the circumferential direction of the combustion chamber housing 2 and the nozzle housing 3, and the block 1 is fixedly connected to the combustion chamber housing 2 through the fastener 4. The block 1 and the fastener 4 realize the fixed connection between the combustion chamber housing 2 and the nozzle housing 3. The solid rocket engine connection structure composed of the block 1 and the fastener 4 has the advantages of simple structure, convenient disassembly and assembly, reliable connection, good assembly process, and easy assembly.

[0043] like Figure 4As shown, the block 1 includes a plurality of blocks, and the plurality of blocks 1 are evenly spaced apart and arranged along the circumferential direction of the combustion chamber housing 2, so as to realize a reliable connection between the combustion chamber housing 2 and the nozzle housing 3. Preferably, the block 1 includes 10 blocks.

[0044] like Figure 1 As shown, the block 1 has a center hole 11. Corresponding to the center hole 11 of the block 1, the combustion chamber housing 2 is provided with a connecting hole, and the fastener 4 passes through the connecting hole of the combustion chamber housing 2 and the center hole 11 of the block 1. Thus, the block 1 is fixedly connected to the combustion chamber housing 2, and the block 1 provides a limiting effect on the circumferential (or annular) relative movement between the combustion chamber housing 2 and the nozzle housing 3.

[0045] Preferably, the fastener 4 is a screw, which passes through the connecting hole of the combustion chamber housing 2 and is threadedly connected with the central hole 11 of the block 1 .

[0046] Preferably, the clamping block 1 is arc-shaped, and is suitable for being arranged in a limiting groove provided in the combustion chamber housing 2 and the nozzle housing 3 to achieve a limiting and fixed connection between the combustion chamber housing 2 and the nozzle housing 3 .

[0047] Embodiment 2

[0048] like Figure 1-5 As shown, the present application provides a solid rocket engine, including a solid rocket engine connection structure, a combustion chamber and a nozzle, the combustion chamber including a combustion chamber shell 2, the end face of the combustion chamber shell 2 having a first ring tooth structure, the nozzle including a nozzle shell 3, the end face of the nozzle shell 3 having a second ring tooth structure, the nozzle shell 3 and the combustion chamber shell 2 are axially limitedly connected by the second ring tooth structure and the first ring tooth structure, the solid rocket engine connection structure is limitedly connected in the gap of the first ring tooth structure and the second ring tooth structure, thereby realizing the circumferential direction limitation between the combustion chamber shell 2 and the nozzle shell 3, that is to say, limiting the relative movement of the combustion chamber shell 2 and the nozzle shell 3 along the circumferential direction of the combustion chamber shell 2.

[0049] like Figure 2 As shown, the combustion chamber housing 2 has a rotating annular groove 22, which is distributed along the inner wall of the combustion chamber housing 2, and the rotating annular groove 22 is located on the side of the first annular gear structure close to the inside of the combustion chamber housing 2, and the second annular gear structure is connected to the rotating annular groove 22. When the block 1 is not installed, the second annular gear structure can rotate in the rotating annular groove 22 along the circumferential direction of the rotating annular groove 22.

[0050] like Figure 1 and 4As shown, the first ring tooth structure includes a plurality of first latch teeth 21 and a plurality of first notches 23. The plurality of first latch teeth 21 are evenly spaced apart along the circumferential direction of the combustion chamber housing 2, and a first notch 23 is provided between each adjacent two first latch teeth 21. The second ring tooth structure passes through the first notch 23 and is inserted into the rotating ring groove 22.

[0051] like Figure 3 As shown, the second ring tooth structure includes a plurality of second latch teeth 31 and a plurality of second notches 32. The second latch teeth 31 are evenly spaced apart along the circumferential direction of the nozzle housing 3, and there is a second notch 32 between two adjacent second latch teeth 31. The second latch teeth 31 pass through the first notch 23 and are inserted into the rotating ring groove 22. The second latch teeth 31 rotate a certain angle in the rotating ring groove 22. The second latch teeth 31 are limited to the inner side of the first latch teeth 21. The second notch 32 is aligned with the first notch 23. The solid rocket engine connection structure is connected in the first notch 23 and the second notch 32.

[0052] As a specific embodiment of the utility model, the nozzle housing 3 is first installed into the combustion chamber housing 2 through the first notch 23, and then the nozzle housing 3 is rotated 20° to complete the axial limit, and then the block 1 is installed in the first notch 23 and the second notch 32, and the screws are installed to complete the annular limit, and the assembly is completed.

[0053] As a specific embodiment of the present invention, the number of the second latch teeth 31 is the same as the number of the first latch teeth 21, and the number of the second notches 32 is the same as the number of the first notches 23. Preferably, the first notches 23 and the second notches 32 include 10, and the first latch teeth 21 and the second latch teeth 31 include 10. As a specific embodiment of the present invention, those skilled in the art can freely set the number or size of the first notches 23 and the second notches 32, as well as the first latch teeth 21 and the second latch teeth 31 in consideration of the load requirements. The size design should ensure the assembly processability to avoid the nozzle housing 3 from getting stuck when rotating.

[0054] The beneficial effects achieved by this application are as follows:

[0055] (1) The nozzle housing of the present application is first installed into the combustion chamber housing through the notch, and then rotated at a certain angle, and the second latch tooth is limited inside the first latch tooth to complete the axial limit, and then the clamping block is installed in the first notch and the second notch, and the clamping block is fixed to the combustion chamber housing by screws to complete the circumferential limit. The connection structure of the present application has the advantages of simple structure, good assembly processability, easy disassembly, reliable connection, and is suitable for the beneficial effects of connecting the combustion chamber and the nozzle under specific conditions.

[0056] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, "plurality" means two or more, unless otherwise clearly and specifically defined.

[0057] In the description of the present application, the word "for example" is used to mean "used as an example, illustration or explanation". Any embodiment described as "for example" in the present application is not necessarily to be construed as being more preferred or advantageous than other embodiments. In order to enable any technician in the field to implement and use the utility model, the following description is given. In the following description, details are listed for the purpose of explanation. It should be understood that a person of ordinary skill in the art can recognize that the utility model can be implemented without using these specific details. In other examples, well-known structures and processes will not be elaborated in detail to avoid unnecessary details that make the description of the utility model obscure. Therefore, the utility model is not intended to be limited to the embodiments shown, but is consistent with the widest range of principles and features disclosed in the present application.

[0058] The above description is only an embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the scope of the claims of the present invention.

Claims

1. A solid rocket engine connection structure, characterized in that: include: Blocks and fasteners, The block is inserted into the limiting grooves distributed along the circumferential direction of the combustion chamber housing and the nozzle housing. The clamping block is fixedly connected to the combustion chamber housing via the fastener.

2. The solid rocket motor connection structure according to claim 1, characterized in that: The clamping blocks include a plurality of blocks, and the plurality of clamping blocks are evenly spaced apart and arranged along the circumferential direction of the combustion chamber housing.

3. The solid rocket motor connection structure according to claim 2, characterized in that: The block has a central hole, and the combustion chamber housing has a connecting hole. The fastener passes through the connecting hole of the combustion chamber housing and the central hole of the clamping block.

4. The solid rocket motor connection structure according to claim 3, characterized in that: The fastener is a screw, which passes through the connecting hole of the combustion chamber housing and is threadedly connected with the central hole of the clamping block.

5. A solid rocket engine, characterized in that: The solid rocket engine connection structure, combustion chamber and nozzle according to any one of claims 1 to 4 are included. The combustion chamber comprises a combustion chamber housing, and an end surface of the combustion chamber housing has a first ring tooth structure. The nozzle comprises a nozzle housing, and the end surface of the nozzle housing has a second ring tooth structure. The nozzle housing and the combustion chamber housing are axially limitedly connected by a second ring gear structure and a first ring gear structure. The solid rocket engine connection structure is limit-connected in the gaps of the first ring tooth structure and the second ring tooth structure.

6. The solid rocket motor according to claim 5, characterized in that: The combustion chamber housing has a rotating annular groove. The rotating annular groove is distributed along the inner wall of the combustion chamber housing, and the rotating annular groove is located on a side of the first ring tooth structure close to the interior of the combustion chamber housing. The second ring tooth structure is connected in the rotating ring groove.

7. The solid rocket motor according to claim 6, characterized in that: The first ring tooth structure includes a plurality of first latch teeth and a plurality of first notches. A plurality of first latch teeth are evenly spaced apart along the circumferential direction of the combustion chamber housing, and a first notch is provided between two adjacent first latch teeth; The second ring tooth structure passes through the first notch and is inserted into the rotating ring groove.

8. The solid rocket motor according to claim 7, characterized in that: The second ring tooth structure includes a plurality of second latch teeth and a plurality of second notches. The second latching teeth are evenly spaced apart along the circumferential direction of the nozzle housing, and a second notch is provided between two adjacent second latching teeth; The second latch tooth passes through the first notch and is inserted into the rotating ring groove. The second latch tooth rotates a certain angle in the rotating ring groove. The second latch tooth is limited on the inner side of the first latch tooth. The second notch is aligned with the first notch. The solid rocket engine connection structure is connected in the first notch and the second notch.

9. The solid rocket motor according to claim 8, characterized in that: The number of the second latching teeth is the same as the number of the first latching teeth, and the number of the second notches is the same as the number of the first notches.

10. The solid rocket motor according to claim 9, characterized in that: The card block is arc-shaped.

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