Combustion chamber structure capable of limiting contraction deformation of head explosive surface

Abstract

The invention discloses a combustion chamber structure for limiting contraction deformation of a head explosive surface, which comprises an explosive column, a shell with a heat insulation layer, a lining layer and a heat insulation ring, the heat insulation ring is positioned at the head of a combustion chamber and is bonded with the shell with the heat insulation layer through an adhesive, and the explosive column is bonded with the shell with the heat insulation layer and the heat insulation ring through the lining layer. The heat insulation ring with the limiting function is arranged on the head powder surface of the combustion chamber, so that radial shrinkage deformation of the head powder surface is effectively prevented, the problem of assembly interference between an inner molded surface of a grain and an ignition device due to curing deformation is solved, danger caused by manual shaping of the powder surface is avoided, and the production efficiency is improved. And meanwhile, a slit formed between the heat insulation ring and the ignition device can effectively prevent the ignition device from falling off due to ablation, so that the possible pushing and pressure oscillation phenomenon is avoided, the working efficiency of the solid rocket engine is improved, the process is simple, the universality is high, the production and maintenance cost is reduced, and the cost is reduced and the efficiency is improved.

Description

Technical Field

[0001] The invention belongs to the technical field of solid rocket engine combustion chamber structure design, and in particular relates to a combustion chamber structure capable of limiting the shrinkage and deformation of a head charge surface. Background Art

[0002] The combustion chamber charge is one of the important parts of the solid rocket engine structure, providing power for the engine and thus propelling the missile body. However, during the cooling and solidification process, the solid propellant grain will shrink and deform in the axial and radial directions due to the internal stress. For the ignition device installed at the head of the combustion chamber, the radial shrinkage of the inner surface of the grain will cause the assembly interference problem between the combustion chamber head charge surface and the ignition device during the final assembly process, resulting in failure to assemble normally. Therefore, a certain gap is usually reserved between the inner surface of the grain and the ignition device during the design process to avoid this problem.

[0003] However, the rational design of the reserved gap faces challenges. On the one hand, for engines of different diameters, the shrinkage of the inner surface of the grain during the curing process is different, and the design can only rely on empirical estimates; on the other hand, the mechanical properties of the propellant are greatly affected by seasonal changes, and the shrinkage of the inner surface of the grain during the curing process in different seasons is also different. Once the grain surface is deformed, it needs to be manually reshaped to eliminate interference, which increases the danger. In addition, unreasonable reserved gaps may cause the ignition device to fall off due to ablation, thereby stimulating thrust and pressure oscillations that affect the working efficiency of solid rocket engines. Summary of the invention

[0004] In order to overcome the deficiencies in the prior art, the present invention provides a combustion chamber structure that can limit the shrinkage and deformation of the head charge surface. By arranging an insulating ring with a limiting function on the head charge surface of the combustion chamber, the radial shrinkage and deformation of the head charge surface can be effectively prevented, thereby avoiding the assembly interference problem between the inner surface of the charge column and the ignition device due to solidification deformation, and avoiding the danger brought by artificial shaping of the charge surface. At the same time, the slit formed between the insulating ring and the ignition device effectively prevents the ignition device from falling off due to ablation, thereby avoiding the thrust and pressure oscillation phenomenon that may be caused by this, which is beneficial to improving the reliability of the solid rocket engine during operation.

[0005] The specific technical solutions of the present invention are as follows:

[0006] A combustion chamber structure for limiting the shrinkage and deformation of the head charge surface, comprising a charge, a shell with an insulating layer, and a lining. The combustion chamber structure also includes an insulating ring, which is located at the head of the combustion chamber and bonded to the shell with an insulating layer by an adhesive. The charge is bonded to the shell with an insulating layer and the insulating ring by a lining.

[0007] The insulating ring has a limiting function. When the insulating ring is coated on the charge surface close to the combustion chamber head, the hardness of the material itself prevents the radial shrinkage and deformation of the inner surface of the charge.

[0008] A narrow gap is formed between the heat-insulating ring and the ignition device installed on the head of the combustion chamber to protect the ignition device from being burned and falling off.

[0009] Preferably, the material of the thermal insulation ring is ablation-resistant phenolic resin.

[0010] Preferably, the cross-section of the thermal insulation ring is L-shaped.

[0011] Preferably, the thickness of the thermal insulation ring is 1 mm.

[0012] Preferably, the material of the drug column is solid propellant.

[0013] Preferably, the charge is a tube-slot type charge in the form of inner hole combustion.

[0014] Preferably, the outer diameter of the medicine column is φ359.8 mm, and the inner diameter is φ173 mm to φ176 mm.

[0015] The present invention has the following beneficial effects:

[0016] (1) The present invention sets a heat-insulating ring on the charge surface of the combustion chamber head to limit the position of the charge surface of the head. The heat-insulating ring is firmly bonded to the heat-insulating layer and the charge column by an adhesive and a lining layer respectively. When the heat-insulating ring is coated on the charge surface of the combustion chamber head, the hardness of the material itself can effectively prevent the charge surface from radial deformation, thereby avoiding the assembly interference problem with the ignition device during the final assembly process.

[0017] (2) The thermal insulation ring provided by the present invention is made of ablation-resistant material. At the same time, the narrow gap between the thermal insulation ring and the ignition device can effectively prevent the head ignition device from falling off due to root ablation, thereby avoiding the thrust and pressure oscillation phenomenon that may be caused by this, which is beneficial to improving the working efficiency of the solid rocket engine.

[0018] (3) The heat-insulating ring provided by the present invention avoids the manual shaping process after the medicine surface shrinks and deforms, thereby reducing the danger of the manufacturing process;

[0019] (4) The combustion chamber structure provided by the present invention is simple in process and has high versatility, which is conducive to reducing production and maintenance costs, and is also conducive to improving the reliability of the solid rocket engine during operation, thereby achieving cost reduction and efficiency improvement. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions disclosed in the present invention, the following briefly introduces the drawings required to be used in some embodiments disclosed in the present invention. Obviously, the drawings described below are only drawings of some embodiments disclosed in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings. In addition, the drawings described below can be regarded as schematic diagrams, and are not limitations on the actual size of the products involved in the embodiments disclosed in the present invention, the actual process of the method, etc.

[0021] Figure 1 A front half-section view of a combustion chamber structure capable of limiting the shrinkage and deformation of the head charge surface provided in an embodiment of the present invention.

[0022] The accompanying drawings are marked as follows: 1. powder column; 2. shell with insulation layer; 3. insulation ring; 4. lining. DETAILED DESCRIPTION

[0023] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0024] The present invention provides a combustion chamber structure capable of limiting the shrinkage and deformation of the head charge surface, comprising a charge, a shell with a thermal insulation layer, and a lining. The combustion chamber structure also comprises an insulating ring, which is located at the head of the combustion chamber and is bonded to the shell with a thermal insulation layer by an adhesive. The charge is bonded to the shell with a thermal insulation layer and the insulating ring by a lining.

[0025] The insulating ring has a limiting function. When the insulating ring is coated on the charge surface close to the combustion chamber head, the hardness of the material itself prevents the radial shrinkage and deformation of the inner surface of the charge.

[0026] A narrow gap is formed between the heat-insulating ring and the ignition device installed on the head of the combustion chamber to protect the ignition device from being burned and falling off.

[0027] Preferably, the material of the thermal insulation ring is ablation-resistant phenolic resin.

[0028] Preferably, the cross-section of the thermal insulation ring is L-shaped.

[0029] Preferably, the thickness of the thermal insulation ring is 1 mm.

[0030] Preferably, the material of the drug column is solid propellant.

[0031] Preferably, the charge is a tube-slot type charge in the form of inner hole combustion.

[0032] Preferably, the outer diameter of the medicine column is φ359.8 mm, and the inner diameter is φ173 mm to φ176 mm.

[0033] Example

[0034] like Figure 1 As shown, a combustion chamber structure capable of limiting the shrinkage and deformation of the head charge surface provided by an embodiment of the present invention comprises a charge (1), a shell with an insulation layer (2), an insulation ring (3) and a lining (4); the insulation ring (3) is located at the head of the combustion chamber and is bonded to the shell with an insulation layer (2) by an adhesive; the charge (1) is bonded to the shell with an insulation layer (2) and the insulation ring (3) by the lining (4); the insulation ring (3) is made of ablation-resistant phenolic resin material, has an L-shaped cross-section and a thickness of 1 mm, and prevents radial shrinkage and deformation of the inner surface of the charge by the hardness of the material itself; the material of the charge (1) is The solid propellant is a tube-shaped charge in the form of inner hole combustion, and adopts a wall-attached casting process; the shell (2) with an insulation layer is a cylindrical structure, with pin holes and threaded holes, the insulation layer has equal thickness and a debonding structure is designed at the tail, the insulation layer is bonded to the shell, wherein the shell is made of ultra-high strength steel, and the insulation layer is made of EPDM rubber, which can effectively prevent heat from being transferred to the metal shell, play a role in protecting the metal shell, and has passed a large number of engineering application tests; the lining (4) uses a special adhesive for solid propellant and EPDM rubber, which ensures that the interface of the grain (1) is reliably bonded in the combustion chamber and will not debond.

[0035] In the embodiment of the present invention, when the insulating ring (3) is coated on the powder surface of the powder column (1) close to the head of the combustion chamber, the hardness of the material itself prevents the radial shrinkage and deformation of the head powder surface, thereby avoiding interference with the ignition device installed on the head of the combustion chamber, avoiding the artificial shaping process after the powder surface shrinks and deforms, and reducing the danger of the manufacturing process; at the same time, the slit between the insulating ring and the ignition device effectively prevents the head ignition device from falling off due to root ablation, thereby avoiding the thrust and pressure oscillation phenomenon that may be caused by this, which is beneficial to improving the working efficiency of the solid rocket engine.

[0036] Although the present invention has been disclosed as a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the above disclosed content without departing from the spirit and scope of the present invention. Therefore, any simple modification, equivalent change and modification made to the above embodiment according to the technical essence of the present invention without departing from the content of the technical solution of the present invention shall belong to the protection scope of the technical solution of the present invention. The protection scope of the present invention shall be subject to the attached claims.

[0037] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A combustion chamber structure for limiting the shrinkage and deformation of the head charge surface, comprising a charge column (1), a shell with a heat insulation layer (2), and a lining layer (4), characterized in that: The combustion chamber structure also includes an insulation ring (3); The heat-insulating ring (3) is located at the head of the combustion chamber and is bonded to the shell (2) with the heat-insulating layer by means of an adhesive; The thermal insulation ring (3) is bonded to the drug column (1) via a lining layer (4), and the drug column (1) is bonded to the shell (2) with a thermal insulation layer via a lining layer (4).

2. A combustion chamber structure for limiting the shrinkage and deformation of the head charge surface according to claim 1, characterized in that: The heat-insulating ring (3) has a limiting function and prevents the radial shrinkage and deformation of the head medicine surface by using the hardness of the material itself.

3. A combustion chamber structure for limiting the shrinkage and deformation of the head charge surface according to claim 1, characterized in that: A narrow gap is formed between the heat insulating ring (3) and an ignition device installed at the head of the combustion chamber to protect the ignition device from burning and falling off.

4. A combustion chamber structure for limiting the shrinkage and deformation of the head charge surface according to claim 1, characterized in that: The material of the thermal insulation ring (3) is ablation-resistant phenolic resin.

5. A combustion chamber structure for limiting the shrinkage and deformation of the head charge surface according to claim 1, characterized in that: The cross section of the heat insulating ring (3) is L-shaped.

6. A combustion chamber structure for limiting the shrinkage and deformation of the head charge surface according to claim 1, characterized in that: The thickness of the thermal insulation ring (3) is 1 mm.

7. A combustion chamber structure for limiting the shrinkage and deformation of the head charge surface according to claim 1, characterized in that: The material of the drug column (1) is solid propellant.

8. A combustion chamber structure for limiting the shrinkage and deformation of the head charge surface according to claim 1, characterized in that: The charge (1) is a tube-shaped charge in the form of inner hole combustion.

9. A combustion chamber structure for limiting the shrinkage and deformation of the head charge surface according to claim 1, characterized in that: The outer diameter of the medicine column (1) is φ359.8 mm, and the inner diameter is φ173 mm to φ176 mm.

Images