Connecting and fixing structure for tail ignition controller of solid rocket engine

Abstract

A connecting and fixing structure for an ignition controller of a solid rocket engine is characterized by comprising a combustion chamber shell, a tail pipe shell, a connecting ring, the ignition controller and screws. After the connecting ring is assembled, 12 matching steps and circumferential reinforcing ribs which are evenly distributed in the circumferential direction are designed in the direction towards a spray pipe at the tail of an engine. Two threaded counterbores are designed in each matching step and are used for assembling and fixing the ignition controller and the connecting ring; the ignition controller can be adjusted and positioned within the range of + / -15 degrees at the tail of the solid rocket engine through the 12 matching steps. The overall space utilization rate of the system is improved, installation is easy, and cost is low. Moreover, through the design that the matching steps and the circumferential reinforcing ribs are additionally arranged on the connecting ring, not only can the structural strength of the connecting ring be ensured, but also the ignition controller can be fixed within any range of + / -15 degrees in the circumferential direction, and the spatial layout requirement in a guided missile steering engine room is met.

Description

Technical Field

[0001] The invention belongs to the technical field of solid rocket engine structures, and in particular relates to a solid rocket engine tail ignition controller connection and fixing structure. Background Art

[0002] In recent years, with the gradual demand for energy distribution management and attitude and orbit control integration technology of solid rocket engines, its ignition control has become increasingly complex. In order to reduce the mass and volume of the ignition circuit and effectively improve the maneuverability of the ignition control system, at present, the ignition control system is designed as a highly integrated ignition controller. This structure needs to reserve a certain installation space in the overall missile layout. The existing ignition controller is generally fixed on the inner wall of the front cabin of the solid rocket engine by an outer circle wall hanging method, which requires a certain axial space. For weapon systems with compact space, reserving the installation space of the ignition controller will not be conducive to the overall optimization configuration. At the same time, the fixed connection structure between the ignition controller and the engine needs to meet the requirements of reliable connection between the ignition controller and the engine under external load conditions. How to make more reasonable use of the space layout and facilitate the reliable connection between the ignition controller and the engine has attracted much attention.

[0003] In view of the characteristics of the Laval nozzle of the solid rocket engine, the convergent section of the nozzle shell is generally a conical closing rotary body structure with a certain cone angle. This conical structure leads to a low layout utilization rate in the convergent section space. Since the shape of the ignition controller itself can be designed on demand according to the layout requirements based on the principles of high reliability, miniaturization, and lightweight, the layout design of the ignition controller can be carried out through the convergent section space of the nozzle shell. However, considering the reliability of the missile body structure and the process operability during processing, it is inconvenient to add redundant structural designs to the tail of the combustion chamber shell for reliable connection with the ignition controller; the nozzle shell is a pressure-bearing structural part, and the change of its rotary body structure may cause structural stress concentration, so it should be avoided to add redundant connection structures to the nozzle shell. In summary, how to reliably connect the ignition controller at the tail of the engine is a problem that needs to be solved. Summary of the invention

[0004] In order to solve the above problems, the present invention proposes a connection and fixing structure that can reliably connect an ignition controller at the rear of an engine.

[0005] The technical solution of the present invention is:

[0006] A solid rocket engine ignition controller connection and fixing structure, comprising a combustion chamber shell, a tail pipe shell, a connecting ring, an ignition controller and screws;

[0007] After the connecting ring is assembled, 12 circumferentially evenly distributed matching steps and circumferential reinforcement ribs are designed toward the engine tail nozzle direction; each matching step is designed with 2 threaded countersunk holes for assembling and fixing the ignition controller to the connecting ring; the 12 matching steps are used to adjust the positioning of the ignition controller within the range of ±15° at the tail of the solid rocket engine.

[0008] The outer side of the connecting ring is a threaded structure, and the threaded structure matches the internal threaded structure at the rear of the combustion chamber casing, and is used to fix the tail pipe casing and the combustion chamber casing.

[0009] The ignition controller is designed according to the requirements of the internal ignition control circuit and the convergent section profile of the nozzle shell. The ignition controller is a semicircular ring structure, and three connecting parts are designed at the edge of the outer ring, each of which is spaced 60 degrees apart; each connecting part is designed with two circular through holes, which match the threaded countersunk holes on the connecting ring, and the ignition controller and the connecting ring are relatively fixed after being tightened through the threaded countersunk holes by 6 screws.

[0010] The combustion chamber shell, tail pipe shell, connecting ring, and ignition controller connecting parts are all made of metal materials; further, the combustion chamber shell, tail pipe shell, and connecting ring connecting parts are all made of high-strength carbon steel materials; the ignition controller connecting part is made of aluminum alloy material, and the screws are made of stainless steel material.

[0011] The threaded countersunk hole on the connecting ring is 9mm deep and the thread specification is M3; the thickness of the connecting part on the ignition controller is 6mm, and the diameter of the internal through hole of the connecting part is Φ3.5mm; the screws are M3×12 hexagon socket screws.

[0012] The beneficial effects of the present invention are as follows:

[0013] (1) Improves the overall space utilization of the system, and is easy to install and low cost;

[0014] (2) By adding matching steps and circumferential reinforcement ribs to the connecting ring, not only can the connection and fixation of the ignition controller be achieved, but also the structural strength of the connecting ring can be ensured;

[0015] (3) The ignition controller can be fixed within any circumferential range of ±15°, which is applicable to all solid rocket engine structures that use connecting rings to connect and fix the tail pipe and combustion chamber, and meets the installation space requirements of the missile rudder compartment. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] 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 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.

[0017] Figure 1 A schematic diagram of a connecting ring structure provided in an embodiment of the present invention;

[0018] Figure 2 A schematic diagram of the structure of an ignition controller provided in an embodiment of the present invention;

[0019] Figure 3 A schematic diagram of the connection and fixing structure of the ignition controller provided in an embodiment of the present invention.

[0020] In the figure: 1 is the combustion chamber housing, 2 is the tail pipe housing, 3 is the connecting ring, 4 is the ignition controller, 5 is the screw, and 6 is the matching step.

[0021] Specific implementation methods

[0022] The following describes the embodiments of the present invention through specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention.

[0023] It should be noted that the illustrations provided in the following embodiments are only schematic illustrations of the basic concept of the present invention, and thus the drawings only show components related to the present invention rather than being drawn according to the number, shape and size of components in actual implementation. In actual implementation, the type, quantity and proportion of each component may be changed arbitrarily, and the component layout may also be more complicated.

[0024] A solid rocket engine ignition controller connection and fixing structure, comprising a combustion chamber housing 1, a tail pipe housing 2, a connecting ring 3, an ignition controller 4 and a screw 5;

[0025] After the connecting ring 3 is assembled, 12 circumferentially evenly distributed matching steps 6 and circumferential reinforcement ribs are designed toward the engine tail nozzle direction; each matching step 6 is designed with 2 threaded countersunk holes for assembling and fixing the ignition controller 4 to the connecting ring 3; the 12 matching steps 6 are used to adjust the positioning of the ignition controller 4 within the range of ±15° at the tail of the solid rocket engine.

[0026] like Figure 1 , 3As shown, the outer side of the connecting ring 3 is a threaded structure, and the threaded structure matches the internal threaded structure at the rear of the combustion chamber housing 1 , and is used to fix the tail pipe housing 2 to the combustion chamber housing 1 .

[0027] like Figure 2 As shown, the ignition controller 4 is designed according to the internal ignition control circuit and the nozzle shell convergence section profile requirements. The ignition controller 4 is a semicircular ring structure, and three connecting parts are designed at the edge of the outer ring with a spacing of 60 degrees between each other; each connecting part is designed with two circular through holes, and the circular through holes match the threaded countersunk holes on the connecting ring 3. Six screws 5 are used to tighten the ignition controller 4 and the connecting ring 3 through the threaded countersunk holes and then fix them relatively.

[0028] like Figure 3 As shown, further, the connection parts of the combustion chamber shell 1, the tail pipe shell 2, the connecting ring 3, and the ignition controller 4 are all made of metal materials; the connection parts of the combustion chamber shell 1, the tail pipe shell 2, and the connecting ring 3 are all made of high-strength carbon steel materials; the connection parts of the ignition controller 4 are made of aluminum alloy materials, and the screws are made of stainless steel materials.

[0029] like Figure 3 As shown, further, the threaded countersunk hole on the connecting ring 3 is 9mm deep and the thread specification is M3; the connecting part on the ignition controller (4) is 6mm thick and the internal through hole diameter of the connecting part is Φ3.5mm; the screws are M3×12 hexagon socket screws.

[0030] The embodiment provided by the present invention:

[0031] In a certain solid rocket engine, the tail pipe housing 2 and the combustion chamber housing 1 are connected by a connecting ring 3 structure, and the outer thread structure of the connecting ring 3 matches the inner thread structure of the tail of the combustion chamber housing, which is used to fix the tail pipe housing 2 and the combustion chamber housing 1; by improving the structure of the connecting ring 3, after the connecting ring 3 is assembled, 12 matching steps and circumferential reinforcement ribs are designed in the circumferential direction toward the engine tail nozzle, and each matching step is designed with 2 threaded countersunk holes, which are used to assemble and fix the ignition controller 4 thereto;

[0032] The connection and fixing structure in the embodiment of the present invention has passed various environmental tests.

[0033] The embodiments of the present invention described above are only used to help explain the present invention. These embodiments are selected and specifically described in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well. The embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. Obviously, many modifications and changes can be made according to the content of this specification, which all belong to the protection scope of the present invention.

Claims

1. A solid rocket engine ignition controller connection fixing structure, characterized in that: The invention comprises a combustion chamber casing (1), a tail pipe casing (2), a connecting ring (3), an ignition controller (4) and screws (5); after being assembled, the connecting ring (3) is provided with 12 circumferentially evenly distributed matching steps (6) and circumferential reinforcing ribs in the direction of the tail nozzle of the engine; each matching step (6) is provided with 2 threaded countersunk holes for assembling and fixing the ignition controller (4) and the connecting ring (3); the 12 matching steps (6) are used for adjusting the positioning of the ignition controller (4) within the range of ±15° at the tail of the solid rocket engine.

2. A solid rocket engine ignition controller connection and fixing structure as claimed in claim 1, characterized in that: The outer side of the connecting ring (3) is a threaded structure, and the threaded structure matches the internal threaded structure of the tail portion of the combustion chamber housing (1), and is used to fix the tail pipe housing (2) and the combustion chamber housing (1).

3. A solid rocket engine ignition controller connection and fixing structure as claimed in claim 1, characterized in that: The ignition controller (4) is a semicircular ring structure, and three connection parts are designed at the edge of the outer ring, each of which is spaced 60 degrees apart; each connection part is designed with two circular through holes; the circular through holes match the threaded countersunk holes on the connecting ring (3), and the ignition controller (4) and the connecting ring (3) are relatively fixed after being tightened through the threaded countersunk holes by using six screws (5).

4. A solid rocket engine ignition controller connection and fixing structure as claimed in claim 1, characterized in that: The combustion chamber housing (1), the tail pipe housing (2), the connecting ring (3) and the connecting parts of the ignition controller (4) are all made of metal materials.

5. A solid rocket engine ignition controller connection and fixing structure as claimed in claim 4, characterized in that: The connection parts of the combustion chamber casing (1), the tail pipe casing (2) and the connection ring (3) are all made of high-strength carbon steel materials.

6. A solid rocket engine ignition controller connection and fixing structure as claimed in claim 4, characterized in that: The connecting part of the ignition controller (4) is made of aluminum alloy material.

7. A solid rocket engine ignition controller connection and fixing structure as claimed in claim 1, characterized in that: The screws are made of stainless steel.

8. A solid rocket engine ignition controller connection and fixing structure as claimed in claim 1, characterized in that: The threaded countersunk hole on the connecting ring (3) has a depth of 9 mm and a thread specification of M3.

9. A solid rocket engine ignition controller connection and fixing structure as claimed in claim 1, characterized in that: The thickness of the connecting part on the ignition controller (4) is 6 mm, and the diameter of the internal through hole of the connecting part is Φ3.5 mm; the screws are M3×12 hexagon socket screws.

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