A combustion chamber structure capable of limiting head surface shrinkage deformation

Abstract

The application discloses a combustion chamber structure for limiting the shrinkage and deformation of a head surface of a propellant, which comprises a propellant column, a shell with an insulating layer, and a lining layer, and further comprises an insulating ring, which is arranged at the head of the combustion chamber and is bonded to the shell with the insulating layer by means of an adhesive, and the propellant column is bonded to the shell with the insulating layer and the insulating ring through the lining layer. By arranging the insulating ring with a limiting function at the head surface of the combustion chamber, the radial shrinkage and deformation of the head surface are effectively prevented, so that the assembly interference problem between the inner surface of the propellant column and an ignition device due to the solidification deformation of the inner surface of the propellant column is avoided, the danger caused by the artificial shaping of the head surface is avoided, meanwhile, the gap formed between the insulating ring and the ignition device can effectively prevent the ignition device from being ablated and falling off, and then the thrust and pressure oscillation phenomenon caused by the ablation and falling off of the ignition device is avoided, which is favorable for improving the working efficiency of the solid rocket engine, and the process is simple, the universality is high, the production and maintenance costs are reduced, and the cost reduction and benefit increase are realized.

Description

Technical Field

[0001] This invention belongs to the technical field of solid rocket engine combustion chamber structure design, specifically relating to a combustion chamber structure that can limit the contraction and deformation of the propellant surface in the nose section. Background Technology

[0002] The propellant charge in the combustion chamber is a crucial component of a solid rocket motor, providing power to propel the missile body. However, during the cooling and solidification process, the solid propellant grain undergoes axial and radial shrinkage deformation due to internal stress. For the ignition device mounted at the combustion chamber head, this radial shrinkage of the propellant grain's inner surface can cause assembly interference between the propellant surface and the ignition device during final assembly, preventing proper assembly. Therefore, a certain gap is typically left between the propellant grain's inner surface and the ignition device during the design phase to avoid this issue.

[0003] However, designing a reasonable clearance presents challenges. On the one hand, the shrinkage of the propellant grain's inner surface during the curing process varies for engines of different diameters, requiring estimation based on experience during the design phase. On the other hand, the mechanical properties of the propellant are greatly affected by seasonal changes, and the shrinkage of the propellant grain's inner surface during curing also differs in different seasons. Furthermore, if the propellant surface deforms, manual reshaping is required to eliminate interference, increasing the risk. In addition, an unreasonable clearance could cause the ignition device to detach due to ablation, thereby triggering thrust and pressure oscillations and affecting the working efficiency of the solid rocket motor. Summary of the Invention

[0004] To overcome the shortcomings of the prior art, this invention provides a combustion chamber structure that can limit the shrinkage and deformation of the propellant head. By setting an insulating ring with a limiting function on the propellant head of the combustion chamber, radial shrinkage and deformation of the propellant head are effectively prevented. This avoids assembly interference problems between the inner surface of the propellant grain and the ignition device due to solidification deformation, and avoids the dangers caused by manual shaping of the propellant head. 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 possible thrust and pressure oscillation phenomena, which is beneficial to improving the reliability of solid rocket motors during operation.

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

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

[0007] The insulating ring has a limiting function. When the insulating ring covers the propellant surface near the head of the combustion chamber, it prevents the radial shrinkage deformation of the inner surface of the propellant by the hardness of the material itself.

[0008] The insulating ring forms a slit with the ignition device installed at the head of the combustion chamber to protect the ignition device from being burned off.

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

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

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

[0012] Preferably, the material of the propellant grain is a solid propellant.

[0013] Preferably, the propellant charge is a tubular type with an internal combustion chamber.

[0014] Preferably, the outer diameter of the drug cartridge is φ359.8mm and the inner diameter is φ173mm~φ176mm.

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

[0016] (1) The present invention limits the propellant surface at the head of the combustion chamber by setting an insulating ring. The insulating ring is firmly bonded to the insulating layer and the propellant column by an adhesive and a liner respectively. When it covers the propellant surface at the head of the combustion chamber, it can effectively prevent radial deformation of the propellant surface by the hardness of the material itself, thereby avoiding assembly interference with the ignition device during the final assembly process.

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

[0018] (3) The insulation ring provided by the present invention avoids the manual shaping process after the drug surface shrinks and deforms, thus reducing the danger of the manufacturing process;

[0019] (4) The combustion chamber structure provided by the present invention has a simple process and high versatility, which is conducive to reducing production and maintenance costs, and at the same time, it is conducive to improving the reliability of solid rocket engines during operation, thus achieving cost reduction and efficiency improvement. Attached Figure Description

[0020] To more clearly illustrate the technical solutions disclosed in this invention, the accompanying drawings used in some embodiments of this invention will be briefly described below. Obviously, the drawings described below are merely drawings of some embodiments of this invention, and those skilled in the art can obtain other drawings based on these drawings. Furthermore, the drawings described below can be considered schematic diagrams and are not intended to limit the actual dimensions of the products or the actual flow of the methods involved in the embodiments of this invention.

[0021] Figure 1 This is a front half-sectional view of a combustion chamber structure that can limit the shrinkage and deformation of the propellant surface in an embodiment of the present invention.

[0022] The attached diagram is labeled as follows: 1. Propellant charge; 2. Shell with insulation layer; 3. Insulation ring; 4. Liner. Detailed Implementation

[0023] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort 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 that can limit the shrinkage and deformation of the propellant head, including a propellant grain, a shell with an insulating layer, and a liner. The combustion chamber structure also includes an insulating ring located at the head of the combustion chamber and bonded to the shell with an insulating layer by an adhesive. The propellant grain is bonded to the shell with an insulating layer and the insulating ring by the liner.

[0025] The insulating ring has a limiting function. When the insulating ring covers the propellant surface near the head of the combustion chamber, it prevents the radial shrinkage deformation of the inner surface of the propellant by the hardness of the material itself.

[0026] The insulating ring forms a slit with the ignition device installed at the head of the combustion chamber to protect the ignition device from being burned off.

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

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

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

[0030] Preferably, the material of the propellant grain is a solid propellant.

[0031] Preferably, the propellant charge is a tubular type with an internal combustion chamber.

[0032] Preferably, the outer diameter of the drug cartridge is φ359.8mm and the inner diameter is φ173mm~φ176mm.

[0033] Example

[0034] like Figure 1 As shown, an embodiment of the present invention provides a combustion chamber structure that can limit the shrinkage and deformation of the propellant head, comprising a propellant grain (1), a shell with an insulating layer (2), an insulating ring (3), and a liner (4); the insulating ring (3) is located at the head of the combustion chamber and is bonded to the shell with an insulating layer (2) by an adhesive; the propellant grain (1) is bonded to the shell with an insulating layer (2) and the insulating ring (3) by the liner (4); the insulating 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 propellant grain through the hardness of the material itself; the material of the propellant grain (1) is... The solid propellant is a tube-shaped charge with an internal combustion chamber, using a wall-mounted casting process. The shell (2) with insulation layer is a cylindrical structure with pin holes and threaded holes. The insulation layer has the same thickness and a debonding structure is designed at the tail. The insulation layer is bonded to the shell. The shell is made of ultra-high strength steel and the insulation layer is made of EPDM rubber, which can effectively prevent heat transfer to the metal shell and protect the metal shell. It has passed the test of a large number of engineering applications. The liner (4) uses a special adhesive for solid propellant and EPDM rubber to ensure reliable bonding of the interface of the propellant grain (1) in the combustion chamber and prevent debonding.

[0035] In the embodiments of the present invention, when the heat insulation ring (3) covers the propellant surface of the propellant grain (1) near the head of the combustion chamber, the hardness of the material itself prevents the radial shrinkage deformation of the propellant surface at the head, thereby avoiding interference with the ignition device installed at the head of the combustion chamber, avoiding the manual shaping process after the propellant surface shrinks and deforms, and reducing the danger of the manufacturing process; at the same time, the slit between the heat insulation ring and the ignition device effectively prevents the head ignition device from falling off due to root erosion, thereby avoiding the possible thrust and pressure oscillation phenomenon, which is conducive to improving the working efficiency of the solid rocket engine.

[0036] While the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the invention. Any person skilled in the art can make possible variations and modifications to the technical solutions of the present invention based on the disclosed content without departing from the spirit and scope of the invention. Therefore, any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the present invention. The protection scope of the present invention is defined by the appended claims.

[0037] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A combustion chamber structure for limiting the shrinkage and deformation of the propellant head, comprising a propellant grain (1), a shell with an insulating layer (2), and a liner (4), characterized in that: The combustion chamber structure also includes an insulating ring (3); The heat insulation ring (3) is located at the head of the combustion chamber and is bonded to the shell (2) with heat insulation layer by adhesive. The insulating ring (3) is bonded to the drug column (1) through the liner (4), and the drug column (1) is bonded to the shell (2) with the insulating layer through the liner (4). The insulating ring (3) has a limiting function, which prevents the radial shrinkage deformation of the head of the medicine surface by the hardness of the material itself. The insulating ring (3) forms a slit with the ignition device installed at the head of the combustion chamber to protect the ignition device from erosion and falling off; the insulating ring (3) has an L-shaped cross section.

2. The combustion chamber structure for limiting the shrinkage and deformation of the propellant surface in the head according to claim 1, characterized in that, The material of the insulating ring (3) is ablation-resistant phenolic resin.

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

4. The combustion chamber structure for limiting the shrinkage and deformation of the propellant surface in the head according to claim 1, characterized in that, The material of the propellant grain (1) is a solid propellant.

5. The combustion chamber structure for limiting the shrinkage and deformation of the propellant surface in the head according to claim 1, characterized in that, The propellant charge (1) is a tubular type charge with an internal combustion chamber.

6. The combustion chamber structure for limiting the shrinkage and deformation of the propellant surface in the head according to claim 1, characterized in that, The outer diameter of the drug column (1) is φ359.8mm and the inner diameter is φ173mm~φ176mm.

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