Heat insulation structure for full-filling charge stress release

Abstract

The invention provides a heat insulation structure for full-filling charge stress release. The heat insulation structure sequentially comprises a combustion chamber shell, a barrel section heat insulation layer, thin film isolation paper I, a coating sleeve, thin film isolation paper II, a stress release heat insulation layer and a grain from outside to inside. The film isolation paper I is laid on the inner surface of the heat insulation layer of the second cylinder body section and is in contact with the outer surface of the second coating sleeve cylinder body section; the inner surface of the first coating sleeve cylinder body section is bonded with the outer surface of the stress release heat insulation layer cylinder body section; the film isolation paper II is laid on the inner surface of the head of the coating sleeve and is in contact with the outer surface of the head of the stress release heat insulation layer. The stress release heat insulation structure is additionally arranged on the combustion chamber barrel section and the combustion chamber head, the coordinated deformation capacity of the grain under the mechanical load and temperature load changes is improved, and then grain stress release and structural integrity improvement are achieved.

Description

Technical Field

[0001] This invention belongs to the field of solid rocket engine propellant design technology, specifically relating to an insulating structure for stress relief during full-load propellant loading. Background Technology

[0002] From manufacturing to completing a combat mission, solid rocket engines inevitably undergo a series of environmental conditions, including temperature shocks, long-term storage, transportation vibrations, ejection impacts, and flight overloads, as well as a sudden increase in internal pressure due to engine ignition. These conditions cause drastic changes in the stress and strain of the propellant grain, potentially leading to cracks or interface debonding, posing potential risks to engine operation. Therefore, ensuring the structural integrity of solid rocket engine propellant grains under these environmental conditions is a crucial issue for guaranteeing mission success.

[0003] In the design of solid rocket motors, stress relief ring structures are often used to ensure the structural integrity of the propellant grain. However, for fully loaded propellant grains, the head is a closed structure, making it impossible to implement a ring-shaped stress relief structure design. In such cases, a stress relief debonding layer can be used to improve the structural integrity of the propellant grain. Summary of the Invention

[0004] To address the aforementioned issues, this invention proposes an insulation structure for stress relief in fully loaded propellant. By adding stress-relieving insulation structures to the combustion chamber cylinder section and the combustion chamber head, the coordinated deformation capability of the propellant grain under varying mechanical and temperature loads is improved, thereby achieving stress relief and enhancing structural integrity.

[0005] The specific technical solution is as follows:

[0006] An insulation structure for stress relief of fully loaded propellant includes, from the outside to the inside: a combustion chamber shell, a cylindrical section insulation layer, a thin film separator I, a covering sleeve, a thin film separator II, a stress relief insulation layer, and a propellant column;

[0007] The combustion chamber shell includes a combustion chamber shell head and a combustion chamber shell cylindrical section;

[0008] The cylindrical section insulation layer includes a first cylindrical section insulation layer and a second cylindrical section insulation layer; the first cylindrical section insulation layer is the portion of the cylindrical section insulation layer near the head with a length L (10mm≤L≤shell length / 5); the second cylindrical section insulation layer is the remaining portion of the cylindrical section insulation layer excluding the first cylindrical section insulation layer.

[0009] The covering sleeve includes a covering sleeve head and a covering sleeve body section; the covering sleeve body section includes a first covering sleeve body section and a second covering sleeve body section; the first covering sleeve body section is the portion of the covering sleeve body section near the head with a length L (10mm≤L≤shell length / 5); the second covering sleeve body section is the remaining portion of the covering sleeve body section excluding the insulation layer of the first body section;

[0010] The stress-relieving insulation layer includes a stress-relieving insulation layer head and a stress-relieving insulation layer cylindrical section.

[0011] The inner surface of the combustion chamber shell cylindrical section is bonded to the outer surface of the cylindrical section insulation layer; the inner surface of the combustion chamber shell head is bonded to the outer surface of the covering sleeve head; the inner surface of the insulation layer of the first cylindrical section is bonded to the outer surface of the first covering sleeve cylindrical section.

[0012] The thin film isolation paper I is laid on the inner surface of the insulation layer of the second cylindrical section and is in contact with the outer surface of the second covered sleeve section;

[0013] The inner surface of the first covered sleeve section is bonded to the outer surface of the stress-relieving insulation layer section;

[0014] The thin film isolation paper II is laid on the inner surface of the cover head and contacts the outer surface of the stress relief insulation layer head.

[0015] The propellant grain is formed by casting propellant after the insulation layer, the covering sleeve, and the head stress-relieving insulation layer of the barrel section are vulcanized.

[0016] The inner surface of the combustion chamber shell section is bonded to the outer surface of the insulation layer of the section with adhesive.

[0017] After the thin film isolation paper I is laid, it is squeezed with an airbag to remove the air between the thin film isolation paper I and the insulation layer of the second cylindrical section.

[0018] The inner surface of the combustion chamber shell head is bonded to the outer surface of the cover head with adhesive.

[0019] The inner surface of the insulation layer of the first cylindrical section is bonded to the outer surface of the first covered sleeve cylindrical section with adhesive.

[0020] The covering sleeve is compressed by an airbag to achieve a firm bond with the inner surface of the combustion chamber shell head and the outer surface of the insulation layer of the first cylindrical section, and to purge the air between the second covering sleeve cylindrical section and the thin film isolation paper I.

[0021] After the thin film isolation paper II is laid, it is squeezed with an airbag to remove the air between the thin film isolation paper II and the head of the covering sleeve.

[0022] The inner surface of the first covered sleeve section is bonded to the outer surface of the stress-relieving insulation layer section with adhesive.

[0023] The stress-relieving insulation layer is compressed by an airbag to achieve a firm bond with the outer surface of the first covered sleeve section and to remove the air between the stress-relieving insulation layer and the thin film release paper II.

[0024] The combustion chamber shell is made of high-strength alloy steel;

[0025] The insulation layer of the cylindrical section, the covering sleeve, and the head stress-relieving insulation layer are made of EPDM rubber.

[0026] The propellant grain uses hydroxyl-butyl propellant.

[0027] Compared with the prior art, the beneficial effects achieved by this invention are as follows:

[0028] 1. The present invention designs a stress-relieving heat insulation structure in the combustion chamber head and cylinder section, which effectively alleviates the stress and strain of the propellant grain in the combustion chamber head and cylinder section.

[0029] 2. This invention improves the coordinated deformation ability of the propellant grain under changes in mechanical and temperature loads by utilizing the synergistic stress release effect of the stress-relieving insulation structure of the combustion chamber head and cylinder section, thereby avoiding the occurrence of propellant grain cracks and interface debonding and improving the structural integrity of the propellant grain.

[0030] 3. This invention is easy to process and implement, has low cost, and high process reliability. Attached Figure Description

[0031] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0032] Figure 1 This is a schematic diagram of an insulation structure for stress relief of a fully loaded propellant, provided as an embodiment of the present invention.

[0033] Reference numerals: 1. Combustion chamber shell; 2. Insulation layer of cylinder section; 3. Covering sleeve; 4. Stress relief insulation layer; 5. Thin film isolation paper I; 6. Thin film isolation paper II; 7. Propellant grain.

[0034] Specific implementation methods

[0035] The present invention will be further described below with reference to the accompanying drawings and specific embodiments. It should be noted that the drawings are all in a very simplified form and use non-precise ratios, and are only used to facilitate and clarify the purpose of illustrating the embodiments of the present invention.

[0036] An insulating structure for stress relief in fully loaded propellant charges, such as Figure 1 As shown, from the outside to the inside, it includes: combustion chamber shell 1, cylindrical section insulation layer 2, thin film isolation paper I 5, covering sleeve 3, thin film isolation paper II 6, stress relief insulation layer 4, and propellant 7.

[0037] The combustion chamber shell 1 includes a combustion chamber shell head and a combustion chamber shell cylindrical section;

[0038] The cylindrical section insulation layer 2 includes a first cylindrical section insulation layer and a second cylindrical section insulation layer; the first cylindrical section insulation layer is the portion of the cylindrical section insulation layer 2 near the head L length; the second cylindrical section insulation layer is the remaining portion of the cylindrical section insulation layer 2 excluding the first cylindrical section insulation layer.

[0039] The covering sleeve 3 includes a covering sleeve head and a covering sleeve body section; the covering sleeve body section includes a first covering sleeve body section and a second covering sleeve body section; the first covering sleeve body section is the portion of the covering sleeve body section near the head L in length; the second covering sleeve body section is the remaining portion of the covering sleeve body section excluding the insulation layer of the first sleeve body section.

[0040] The stress-relieving insulation layer 4 includes a stress-relieving insulation layer head and a stress-relieving insulation layer cylindrical section.

[0041] The inner surface of the combustion chamber shell cylindrical section is bonded to the outer surface of the cylindrical section insulation layer 2; the inner surface of the head of the combustion chamber shell 1 is bonded to the outer surface of the head of the covering sleeve 3; the inner surface of the insulation layer of the first cylindrical section is bonded to the outer surface of the first covering sleeve cylindrical section.

[0042] The thin film isolation paper I5 is laid on the inner surface of the insulation layer of the second cylinder section and is in contact with the outer surface of the second covered sleeve section.

[0043] The inner surface of the first covered sleeve section is bonded to the outer surface of the stress-relieving insulation layer section;

[0044] The thin film isolation paper II6 is laid on the inner surface of the cover head and contacts the outer surface of the stress relief insulation layer head.

[0045] The propellant grain 7 is formed by casting propellant after the insulation layer 2, the covering sleeve 3, and the head stress-relieving insulation layer 4 of the cylindrical section are vulcanized.

[0046] The inner surface of the combustion chamber shell section is bonded to the outer surface of the insulation layer 2 of the section with adhesive.

[0047] After the thin film isolation paper I5 is laid, it is squeezed with an airbag to remove the air between the thin film isolation paper I5 and the insulation layer of the second cylinder section.

[0048] The inner surface of the combustion chamber shell head is bonded to the outer surface of the cover head with adhesive.

[0049] The inner surface of the insulation layer of the first cylindrical section is bonded to the outer surface of the first covered sleeve cylindrical section with adhesive.

[0050] The covering sleeve 3 is compressed by an airbag to achieve a firm bond with the inner surface of the combustion chamber shell head and the outer surface of the insulation layer of the first cylindrical section, and to purge the air between the second covering sleeve cylindrical section and the thin film isolation paper I5.

[0051] After the thin film isolation paper II6 is laid, it is squeezed with an airbag to remove the air between the thin film isolation paper II6 and the head of the covering sleeve.

[0052] The inner surface of the first covered sleeve section is bonded to the outer surface of the stress-relieving insulation layer section with adhesive.

[0053] The stress-relieving insulation layer 4 is compressed by an airbag to achieve a firm bond with the outer surface of the first covered sleeve section and to remove the air between the stress-relieving insulation layer and the thin film release paper II6.

[0054] The combustion chamber shell 1 is made of high-strength alloy steel;

[0055] The insulation layer 2 of the cylindrical section, the covering sleeve 3, and the head stress-relieving insulation layer 4 are made of EPDM rubber.

[0056] The propellant grain 7 uses hydroxyl-butyl propellant.

[0057] The specific operation steps of this embodiment are provided below:

[0058] The combustion chamber shell 1 is made of high-strength alloy steel, and the cylinder section insulation layer 2, the covering sleeve 3, and the stress relief insulation layer 4 are made of EPDM rubber.

[0059] The outer surface of the insulation layer 2 of the cylindrical section is bonded to the inner surface of the cylindrical section of the combustion chamber shell 1 with adhesive.

[0060] A thin film isolation paper I5 is laid on the inner surface of the insulation layer of the second cylindrical section. The head of the thin film isolation paper I5 is glued to the inner surface of the head of the insulation layer of the second cylindrical section within 5mm. The thin film isolation paper I5 is squeezed by an airbag to remove the air between the insulation layer of the second cylindrical section and the thin film isolation paper I5.

[0061] The inner surface of the head of the combustion chamber shell 1 is coated with glue and bonded to the outer surface of the head of the cover sleeve 3;

[0062] The inner surface of the insulation layer (L=50mm) of the first cylindrical section is coated with adhesive and bonded to the outer surface of the first covered sleeve section (L=50mm). The second covered sleeve section is placed on the thin film release paper I5.

[0063] The airbag compression sleeve 3 is used to firmly bond the head of the sleeve to the inner surface of the combustion chamber shell head, the outer surface of the first sleeve cylinder section (L=50mm) to the inner surface of the insulation layer of the first cylinder section (L=50mm), and to purge the air between the second sleeve cylinder section and the thin film isolation paper I5.

[0064] A thin film isolation paper II6 is laid on the inner surface of the head of the cover, and the thin film isolation paper II6 is squeezed by an airbag to expel the air between the head of the cover and the thin film isolation paper II6.

[0065] The stress relief insulation layer head is placed on the combustion chamber head film isolation paper II6, and the stress relief insulation layer 4 is squeezed by an airbag to remove the air between the head of the stress relief insulation layer and the film isolation paper II6.

[0066] The inner surface of the first covered sleeve section (L=50mm) is coated with adhesive and bonded to the outer surface of the stress-relieving insulation layer section (L=50mm). The stress-relieving insulation layer 4 is then compressed with an airbag to firmly bond the outer surface of the stress-relieving insulation layer section to the inner surface of the first covered sleeve section, and the air between the stress-relieving insulation layer and the thin film release paper II6 is expelled.

[0067] After the insulation layer 2, the covering sleeve 3, and the stress-relieving insulation layer 4 of the cylinder section are vulcanized, hydroxyl propellant is poured to form the propellant column 7.

[0068] Therefore, the thermal insulation structure for stress relief provided by the present invention effectively alleviates the stress and strain of the propellant grain in the combustion chamber head and cylinder section, realizes coordinated deformation of the propellant grain under changes in mechanical and temperature loads, and improves the structural integrity of the propellant grain.

[0069] Although 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 using the disclosed methods and techniques 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 scope of the invention's technical solutions are within the protection scope of the present invention. Contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. A thermal insulation structure for stress relief in fully loaded propellant charges, characterized in that, From the outside in, the following are included: Combustion chamber shell (1), cylindrical section insulation layer (2), thin film isolation paper I (5), covering sleeve (3), thin film isolation paper II (6), stress relief insulation layer (4), propellant column (7); The combustion chamber shell (1) includes a combustion chamber shell head and a combustion chamber shell cylindrical section; The cylindrical section insulation layer (2) includes a first cylindrical section insulation layer and a second cylindrical section insulation layer; the first cylindrical section insulation layer is the part of the cylindrical section insulation layer (2) near the head with a length of L; the second cylindrical section insulation layer is the remaining part of the cylindrical section insulation layer (2) excluding the first cylindrical section insulation layer; wherein 10mm≤L≤shell length / 5. The covering sleeve (3) includes a covering sleeve head and a covering sleeve body section; the covering sleeve body section includes a first covering sleeve body section and a second covering sleeve body section; the first covering sleeve body section is the part of the covering sleeve body section near the head L length; the second covering sleeve body section is the remaining part of the covering sleeve body section excluding the insulation layer of the first body section. The stress-relieving insulation layer (4) includes a stress-relieving insulation layer head and a stress-relieving insulation layer cylinder section. The inner surface of the combustion chamber shell cylindrical section is bonded to the outer surface of the cylindrical section insulation layer (2); the inner surface of the head of the combustion chamber shell (1) is bonded to the outer surface of the head of the covering sleeve (3); the inner surface of the insulation layer of the first cylindrical section is bonded to the outer surface of the first covering sleeve cylindrical section; The thin film isolation paper I (5) is laid on the inner surface of the insulation layer of the second cylinder section and is in contact with the outer surface of the second covered sleeve section; The inner surface of the first covered sleeve section is bonded to the outer surface of the stress-relieving insulation layer section; The thin film isolation paper II (6) is laid on the inner surface of the cover head and in contact with the outer surface of the stress relief insulation layer head.

2. The thermal insulation structure for stress relief of a fully loaded propellant charge according to claim 1, characterized in that: The inner surface of the combustion chamber shell section is bonded to the outer surface of the insulation layer (2) of the section with adhesive.

3. The thermal insulation structure for stress relief of a fully loaded propellant charge according to claim 1, characterized in that: After the thin film isolation paper I (5) is laid, it is squeezed with an airbag to remove the air between the thin film isolation paper I (5) and the insulation layer of the second cylinder section.

4. The thermal insulation structure for stress relief of fully loaded propellant according to claim 1, characterized in that: The inner surface of the combustion chamber shell head is bonded to the outer surface of the cover head with adhesive.

5. The thermal insulation structure for stress relief of a fully loaded propellant charge according to claim 1, characterized in that: The inner surface of the insulation layer of the first cylindrical section is bonded to the outer surface of the first covered sleeve cylindrical section with adhesive.

6. The thermal insulation structure for stress relief of a fully loaded propellant charge according to claim 1, characterized in that: The covering sleeve (3) is compressed by an airbag to achieve a firm bond with the inner surface of the combustion chamber shell head and the outer surface of the insulation layer of the first cylinder section, and to purge the air between the second covering sleeve cylinder section and the thin film isolation paper I (5).

7. The thermal insulation structure for stress relief of a fully loaded propellant charge according to claim 1, characterized in that: After the film isolation paper II (6) is laid, it is squeezed with an airbag to remove the air between the film isolation paper II (6) and the head of the cover sleeve.

8. The thermal insulation structure for stress relief of a fully loaded propellant charge according to claim 1, characterized in that: The inner surface of the first covered sleeve section is bonded to the outer surface of the stress-relieving insulation layer section with adhesive.

9. The thermal insulation structure for stress relief of a fully loaded propellant charge according to claim 1, characterized in that: The stress-relieving insulation layer (4) is compressed by an airbag to achieve a firm bond with the outer surface of the first covered sleeve section and to remove the air between the stress-relieving insulation layer and the thin film isolation paper II (6).

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