An integrated thermal insulation layer structure for a solid rocket motor and its fabrication method

Abstract

This invention provides an integrated insulation layer structure for solid rocket motors and its manufacturing method. The integrated insulation layer structure includes a combustion chamber shell, a front-end artificial debonding layer, a rear-end artificial debonding layer, an integrated cylindrical insulation layer, thin-film isolation paper I, and thin-film isolation paper II, achieving a complete insulation structure design. By employing an integrated insulation layer structure, hydraulic press molding process, and airbag venting process, the overlapping and protruding structures caused by traditional insulation layer laying are eliminated. This enables precise consistency in the insulation structure and mass of different solid rocket motors, achieving operational consistency between different solid rocket motors.

Description

Technical Field

[0001] This invention belongs to the technical field of engine insulation layer structure, and specifically relates to an integrated insulation layer structure for a solid rocket engine and its manufacturing method. Background Technology

[0002] Solid rocket engines, as a type of mechanical device that converts chemical energy into kinetic energy, mainly consist of a combustion chamber, an ignition device, and a nozzle. Due to their advantages such as simple structure, large impulse, small size, reliable operation, safe use, low cost, and high maneuverability, solid rocket engines are widely used in rockets, missiles, satellites, and spacecraft for interstage separation, forward and reverse thrust, fairing separation, and spacecraft-rocket rotation.

[0003] During the operation of solid rocket motors, to ensure accurate and timely stage separation, fairing jettison, and launch vehicle rotation, solid rocket motors must be arranged in groups and maintain operational consistency, posing new challenges to motor design. Adopting an integrated insulation layer structure can eliminate the splicing between insulation structures, achieving precise consistency in the insulation structures of different solid rocket motors, thereby improving operational consistency among them. Summary of the Invention

[0004] To overcome the shortcomings of existing technologies, the inventors have conducted intensive research and provided an integrated insulation layer structure for solid rocket engines and its manufacturing method. By employing an integrated insulation layer structure, hydraulic press molding process, and airbag venting process, the overlapping and protruding structures caused by traditional insulation layer laying are eliminated, achieving precise consistency in the insulation structure and mass of different solid rocket engines, and achieving operational consistency between different solid rocket engines.

[0005] The technical solution provided by this invention is as follows:

[0006] In a first aspect, an integrated thermal insulation layer structure for a solid rocket motor includes: a combustion chamber shell, a head artificial debonding layer bottom layer, a tail artificial debonding layer bottom layer, an integrated cylindrical thermal insulation layer, a thin film isolation paper I, and a thin film isolation paper II.

[0007] The combustion chamber housing has a front opening and a rear opening at both ends. The front opening is used to install the ignition device, and the rear opening is used to install the nozzle.

[0008] The outer surface of the bottom layer of the artificial debonding layer at the head is bonded to the inner surface of the arc section and the front end of the cylinder section of the combustion chamber shell by adhesive, and the central hole of the artificial debonding layer at the head is positioned and aligned with the front opening of the combustion chamber shell at the head.

[0009] The outer surface of the bottom layer of the artificial debonding layer at the tail end is bonded to the inner surface of the tail section of the combustion chamber shell using an adhesive, and the tail end face of the artificial debonding layer at the tail end is positioned and aligned with the tail end face of the combustion chamber shell.

[0010] Thin film release paper I is laid on the inner surface area of ​​the head arc section and the front end of the cylindrical section of the bottom layer of the head artificial debonding layer; thin film release paper II is laid on the inner surface area of ​​the rear end of the bottom layer of the tail artificial debonding layer.

[0011] The integrated cylindrical insulation layer covers the combustion chamber shell. Its outer surface is bonded to the inner surface of the combustion chamber shell cylindrical section, the inner surface of the bottom layer of the artificial debonding layer at the head without the thin film release paper I, and the inner surface of the bottom layer of the artificial debonding layer at the tail without the thin film release paper II by adhesive. The central hole at the head of the integrated cylindrical insulation layer is positioned and aligned with the front opening at the head of the combustion chamber shell, and the tail end face is positioned and aligned with the tail end face of the combustion chamber shell.

[0012] Secondly, a method for manufacturing an integrated thermal insulation layer structure for a solid rocket motor includes the following steps:

[0013] The artificial release layer of the head is formed by pressing the bottom layer of the artificial release layer using a head artificial release layer molding die;

[0014] The tail-end artificial debonding layer bottom layer is formed by pressing with a tail-end artificial debonding layer bottom layer molding die;

[0015] The integrated cylindrical insulation layer is formed by pressing an integrated cylindrical insulation layer mold.

[0016] Apply adhesive to the head and tail of the combustion chamber shell, and lay the bottom layer of the artificial debonding layer at the head and the bottom layer of the artificial debonding layer at the tail.

[0017] Thin film release paper I is laid on the inner surface area of ​​the head arc section and the front end of the cylindrical section of the bottom layer of the artificial debonding layer at the head; thin film release paper II is laid on the inner surface area of ​​the rear end of the bottom layer of the artificial debonding layer at the tail.

[0018] The airbag is used to squeeze the film release paper I and film release paper II to remove the air between the bottom layer of the artificial de-adhesive layer at the head and film release paper I, and between the bottom layer of the artificial de-adhesive layer at the tail and film release paper II.

[0019] Adhesive is applied to the inner surface of the combustion chamber shell section, the inner surface of the head where the artificial debonding layer is not covered with thin film isolation paper, and the inner surface of the tail where the artificial debonding layer is not covered with thin film isolation paper, and an integrated shell insulation layer is laid.

[0020] The airbag is used to compress the integrated cylindrical insulation layer to remove the air between the integrated cylindrical insulation layer and the film separator paper I and film separator paper II;

[0021] The laid head artificial debonding layer bottom layer, tail artificial debonding layer bottom layer and integrated cylinder insulation layer are vulcanized to obtain the molded integrated insulation layer structure.

[0022] The integrated thermal insulation layer structure and manufacturing method for a solid rocket motor provided by the present invention have the following beneficial effects:

[0023] (1) The present invention provides an integrated insulation layer structure for a solid rocket engine and its manufacturing method. The integrated insulation layer structure eliminates the splicing structure between insulation structures, and achieves precise consistency of insulation structures for different solid rocket engines, thereby improving the working consistency between different solid rocket engines.

[0024] (2) The present invention provides an integrated insulation layer structure for a solid rocket engine and its manufacturing method. The insulation layer structure components are formed by hydraulic press molding process, and the artificial debonding layer bottom layer of the head, the artificial debonding layer bottom layer of the tail, the integrated cylindrical insulation layer, the thin film isolation paper I, and the thin film isolation paper II are laid and bonded by airbag exhaust process. This eliminates the overlapping and protruding structure produced by traditional insulation layer sheets, ensures the precise consistency of insulation layer structures of different solid rocket engines, and reduces negative mass. Attached Figure Description

[0025] Figure 1 A schematic diagram of an integrated thermal insulation layer structure for a solid rocket motor provided by the present invention;

[0026] Figure 2 This is an enlarged schematic diagram of a partial structure of the head of the integrated insulation layer provided by the present invention;

[0027] Figure 3 This is an enlarged schematic diagram of a partial structure at the tail of the integrated insulation layer provided by the present invention.

[0028] Figure 4 This is a schematic diagram of the integrated cylindrical insulation layer structure provided by the present invention;

[0029] Figure 5 This is a schematic diagram of the bottom layer structure of the artificial deadhesion layer for the head provided by the present invention;

[0030] Figure 6 This is a schematic diagram of the bottom layer structure of the artificial debonding layer at the tail provided by the present invention;

[0031] Figure 7 This invention provides a schematic diagram of the head artificial debonding layer bottom layer molding die and its manufacturing process.

[0032] Figure 8 The tail-end artificial debonding layer bottom molding die and its manufacturing schematic diagram are provided for this invention;

[0033] Figure 9The integrated cylindrical insulation layer molding die and its manufacturing process are shown in the schematic diagram provided by this invention.

[0034] Explanation of icon numbers

[0035] 1—Combustion chamber shell; 2—Head artificial debonding layer bottom layer; 3—Tail artificial debonding layer bottom layer; 4—Integrated cylinder insulation layer; 5—Film separation paper I; 6—Film separation paper II; 7—Head artificial debonding layer bottom layer molding upper mold; 8—Head artificial debonding layer bottom layer molding lower mold; 9—Tail artificial debonding layer bottom layer molding upper mold; 10—Tail artificial debonding layer bottom layer molding lower mold; 11—Integrated cylinder insulation layer molding lower mold; 12—Integrated cylinder insulation layer molding upper mold; 13—Integrated cylinder insulation layer molding center bottom mold; 14—Integrated cylinder insulation layer molding forming mold; 15—Integrated cylinder insulation layer molding center mold; 16—Integrated cylinder insulation layer molding center rod. Detailed Implementation

[0036] The features and advantages of the present invention will become clearer and more explicit from the following detailed description.

[0037] The term “exemplary” as used herein means “serving as an example, embodiment, or illustration.” Any embodiment illustrated herein as “exemplary” is not necessarily to be construed as superior to or better than other embodiments.

[0038] See Figure 1 The present invention provides an integrated heat insulation layer structure for a solid rocket motor, including a combustion chamber shell 1, a head artificial debonding layer bottom layer 2, a tail artificial debonding layer bottom layer 3, an integrated cylindrical heat insulation layer 4, a thin film isolation paper I 5, and a thin film isolation paper II 6.

[0039] The combustion chamber shell 1 is made of high-strength alloy steel; the head artificial de-adhesion layer bottom layer 2, the tail artificial de-adhesion layer bottom layer 3, and the integrated cylinder insulation layer 4 are made of EPDM rubber as the base material, and vulcanizing agents, flame retardants, reinforcing agents, tackifiers, antioxidants, etc. may also be added to the material.

[0040] See Figure 1 The combustion chamber housing 1 has a front opening and a rear opening at both ends. The front opening is a small opening for installing an ignition device, and the rear opening is a large opening for installing a nozzle.

[0041] See Figure 1 and Figure 2 The outer surface of the bottom layer 2 of the artificial debonding layer at the head is bonded to the inner surface of the arc segment at the head and the front end of the cylindrical segment of the combustion chamber shell 1 by an adhesive, and the center hole of the artificial debonding layer 2 at the head is positioned and aligned with the front opening of the head of the combustion chamber shell 1.

[0042] See Figure 1 and Figure 3 The outer surface of the bottom layer 3 of the artificial debonding layer at the tail end is bonded to the inner surface of the tail section of the combustion chamber shell 1 by an adhesive, and the tail end face of the artificial debonding layer 3 at the tail end end face of the combustion chamber shell 1 is positioned and aligned.

[0043] See Figure 1 and Figure 2 A thin film release paper I5 is laid on the inner surface area of ​​the head arc segment and the front end of the cylindrical segment within 20±2mm of the bottom layer 2 of the artificial debonding layer at the head.

[0044] See Figure 1 and Figure 3 A thin film isolation paper II6 is laid on the inner surface area of ​​the bottom layer 3 of the artificial de-adhesion layer at the tail end, within 40±2mm from the tail end face of the combustion chamber shell.

[0045] See Figure 1 , Figure 2 and Figure 3 As shown, the integrated cylindrical insulation layer 4 covers the combustion chamber shell 1. Its outer surface is bonded to the inner surface of the cylindrical section of the combustion chamber shell 1, the inner surface of the bottom layer 2 of the artificial debonding layer at the head without the thin film release paper I5, and the inner surface of the bottom layer 3 of the artificial debonding layer at the tail without the thin film release paper II6 by adhesive. This ensures that the central hole at the head of the integrated cylindrical insulation layer 4 is positioned and aligned with the front opening at the head of the combustion chamber shell 1, and the tail end face is positioned and aligned with the tail end face of the combustion chamber shell 1.

[0046] The overlapping areas of the thin film isolation paper I5 and thin film isolation paper II6 with the integrated cylinder insulation layer 4 are not bonded. After the propellant is cast, the non-bonded areas are used to release the internal stress of the propellant.

[0047] This invention also provides a method for manufacturing an integrated thermal insulation layer structure for a solid rocket motor, comprising the following steps:

[0048] Step 1: Press the head artificial release layer bottom layer 2 using a head artificial release layer bottom molding die.

[0049] See Figure 7 The head artificial debonding layer bottom layer molding die includes an upper mold 7 for head artificial debonding layer bottom layer molding as a punch and a lower mold 8 for head artificial debonding layer bottom layer molding as a die. The forming surfaces of the upper mold 7 and the lower mold 8 are a combination of arc surface and cylindrical surface, which are consistent with the inner and outer surfaces of the head artificial debonding layer bottom layer 2, respectively. A central hole is opened at the rear end of the upper mold 7 for head artificial debonding layer bottom layer molding, and a central boss is machined at the front end of the lower mold 8 for head artificial debonding layer bottom layer molding. The central hole and the central boss cooperate to realize the alignment of the forming surfaces of the die and the punch.

[0050] The EPDM rubber-based material is laid on the bottom of the lower mold 8 for the artificial release layer of the head. The upper mold 7 for the artificial release layer of the head is then placed in, ensuring that the center hole is aligned with the center boss of the lower mold 8. A hydraulic press is used to pre-form the upper mold 7 by applying pressure. The hydraulic press pressure is 50±5 N·m, the pre-forming temperature is 60±3℃, and the holding time is 30±2 min. The product is then manufactured as follows. Figure 5 The artificial desiccant layer 2 shown is the bottom layer of the head.

[0051] Step 2: The bottom layer of the artificial debonding layer at the tail is formed by pressing it with a tail-end artificial debonding layer bottom molding die 3.

[0052] See Figure 8 The tail-end artificial debonding layer bottom layer molding die includes a tail-end artificial debonding layer bottom layer molding upper die 9 as a punch and a tail-end artificial debonding layer bottom layer molding lower die 10 as a die; the forming surfaces of the tail-end artificial debonding layer bottom layer molding upper die 9 and tail-end artificial debonding layer bottom layer molding lower die 10 are cylindrical surfaces, which are consistent with the inner and outer surfaces of the tail-end artificial debonding layer bottom layer 3, respectively; a central hole is opened at the rear end of the tail-end artificial debonding layer bottom layer molding upper die 9, and a central boss is machined at the front end of the tail-end artificial debonding layer bottom layer molding lower die 10. The central hole and the central boss cooperate to realize the alignment of the forming surfaces of the die and the punch.

[0053] The EPDM rubber-based material is laid in the groove of the upper mold 9 for the bottom layer of the artificial release layer. The lower mold 10 for the bottom layer of the artificial release layer is then placed in, ensuring that the central boss is positioned and aligned with the central hole of the upper mold 9. A hydraulic press is used to pre-form the bottom layer of the artificial release layer using pressure of 50±5 N·m, a pre-forming temperature of 60±3℃, and a holding time of 30±2 min. The product is then manufactured as follows. Figure 6 The bottom layer 3 of the artificial debonding layer at the tail is shown.

[0054] Step 3: The integrated cylindrical insulation layer 4 is formed by pressing and molding with an integrated cylindrical insulation layer molding die.

[0055] See Figure 9 The integrated cylindrical insulation layer molding die includes a punch assembly and a die assembly. The punch assembly includes an integrated cylindrical insulation layer molding center bottom die 13, an integrated cylindrical insulation layer molding forming die 14, an integrated cylindrical insulation layer molding center die 15, and an integrated cylindrical insulation layer molding center rod 16. The die assembly includes an integrated cylindrical insulation layer molding lower die 11 and an integrated cylindrical insulation layer molding upper die 12.

[0056] The integrated cylindrical insulation layer molding center rod 16 is assembled from back to front with the integrated cylindrical insulation layer molding center bottom mold 13 and the integrated cylindrical insulation layer molding forming mold 14. The integrated cylindrical insulation layer molding center mold 15 is assembled inside the integrated cylindrical insulation layer molding forming mold 14. The outer side of the integrated cylindrical insulation layer molding forming mold 14 is machined with a circumferential groove, the length of which corresponds to the length of the cylindrical section of the combustion chamber shell 1. The combined surface of the outer surfaces of the integrated cylindrical insulation layer molding center bottom mold 13 and the integrated cylindrical insulation layer molding forming mold 14 is consistent with the inner surface of the integrated cylindrical insulation layer. The integrated cylindrical insulation layer molding lower mold 11 and the integrated cylindrical insulation layer molding upper mold 12 are connected to form a cavity that accommodates the punch assembly. The inner surface of the cavity is consistent with the outer surface of the integrated cylindrical insulation layer.

[0057] An annular groove is formed at the tail of the central hole of the integrated cylindrical insulation layer molding center bottom mold 13, which mates with the annular boss at the tail of the integrated cylindrical insulation layer molding center rod 16; an inner ring groove and an outer ring groove are formed on the front end face of the integrated cylindrical insulation layer molding center bottom mold 13, which mate with the rear end bosses of the integrated cylindrical insulation layer molding center mold 15 and the integrated cylindrical insulation layer molding forming mold 14, respectively; the front end diameter of the integrated cylindrical insulation layer molding center mold 15 is increased and an annular boss is formed, which mates with the front end annular groove of the integrated cylindrical insulation layer molding forming mold 14 to form a limit; the integrated cylindrical insulation layer molding center rod 16 is inserted into the central hole of the integrated cylindrical insulation layer molding lower mold 11 for alignment and passes through the central through hole of the integrated cylindrical insulation layer molding upper mold 12 for alignment.

[0058] The integrated cylindrical insulation layer molding center bottom mold 13 is fitted onto the integrated cylindrical insulation layer molding center rod 16, ensuring that the rear annular groove of the integrated cylindrical insulation layer molding center bottom mold 13 is positioned and aligned with the annular boss of the integrated cylindrical insulation layer molding center rod 16; the integrated cylindrical insulation layer molding forming mold 14 is fitted onto the integrated cylindrical insulation layer molding center rod 16, ensuring that the rear boss of the integrated cylindrical insulation layer molding forming mold 14 is positioned and aligned with the front outer ring groove of the integrated cylindrical insulation layer molding center bottom mold 13; the integrated cylindrical insulation layer molding center mold 15 is fitted onto the integrated cylindrical insulation layer molding center rod 16, ensuring that the integrated cylindrical insulation layer molding... The rear end boss of the center mold 15 is positioned and aligned with the front inner ring groove of the integrated cylindrical insulation layer molding center bottom mold 13; the front annular boss is positioned and aligned with the front annular groove of the integrated cylindrical insulation layer molding mold 14; EPDM rubber as the base material is laid on the circumferential groove on the outer surface of the integrated cylindrical insulation layer molding mold 14 and the outer surface of the integrated cylindrical insulation layer molding center bottom mold 13, and then placed into the integrated cylindrical insulation layer molding lower mold 11. Pre-forming is performed using the integrated cylindrical insulation layer molding upper mold 12, with a hydraulic press pressure of 50±5 N·m, a pre-forming temperature of 60±3℃, and a holding time of 30±2 min. The product is manufactured as follows. Figure 4 The integrated cylindrical insulation layer 4 is shown.

[0059] Step 4: Apply adhesive to the head and tail of the combustion chamber shell 1, and lay the head artificial debonding layer bottom layer 2 and the tail artificial debonding layer bottom layer 3;

[0060] Step 5: Lay a thin film isolation paper I5 on the inner surface area of ​​the head arc section and the front end of the cylinder section of the head artificial deadhesion layer 2, and lay a thin film isolation paper II6 on the inner surface area of ​​the tail artificial deadhesion layer 3 within 40±2mm from the tail end face of the combustion chamber shell.

[0061] Step 6: Use an airbag to squeeze the film release paper I5 and film release paper II6. The airbag inflation pressure is 0.8-1.2MPa to purge the air between the bottom layer 2 of the head manual release layer and film release paper I5, and between the bottom layer 3 of the tail manual release layer and film release paper II6.

[0062] Step 7: Apply adhesive to the inner surface of the combustion chamber shell 1 cylinder section, the inner surface of the head artificial debonding layer bottom layer 2 without the film isolation paper, and the inner surface of the tail artificial debonding layer bottom layer 3 without the film isolation paper, and lay the integrated cylinder insulation layer 4.

[0063] Step 8: Use an airbag to compress the integrated cylindrical insulation layer 4. The airbag inflation pressure is 0.8-1.2MPa to purge the air between the integrated cylindrical insulation layer 4 and the thin film isolation paper I 5 and the thin film isolation paper II 6.

[0064] Step 9: The laid artificial debonding layer 2 (head), artificial debonding layer 3 (tail), and integrated cylinder insulation layer 4 are vulcanized at a temperature of 55–65°C for 3–5 hours to obtain the formed integrated insulation layer structure. Notably, the manufacturing parameters for the integrated insulation layer of solid rocket motors produced in the same batch are kept consistent.

[0065] The performance of four sets of integrated heat insulation layer structures for solid rocket engines manufactured in the same batch using the manufacturing method of the present invention is shown in Table 1.

[0066] Table 1 Summary of the performance of integrated thermal insulation layer for solid rocket motors

[0067]

[0068]

[0069] Therefore, the present invention provides an integrated insulation layer structure for solid rocket motors and its manufacturing method. It adopts a hydraulic press molding process and an airbag venting process to eliminate the overlapping protrusions caused by traditional insulation layer laying. Compared with the traditional method of removing insulation layer overlapping protrusions by mechanical processing, it is easier to mass-produce and implement, has low cost, and high process reliability. At the same time, it achieves precise consistency in the insulation structure and quality of different solid rocket motors, thereby improving the working consistency between different solid rocket motors.

[0070] The present invention has been described in detail above with reference to specific embodiments and exemplary examples; however, these descriptions should not be construed as limiting the present invention. Those skilled in the art will understand that various equivalent substitutions, modifications, or improvements can be made to the technical solutions and embodiments of the present invention without departing from the spirit and scope of the invention, and all such modifications and improvements fall within the scope of the present invention. The scope of protection of the present invention is defined by the appended claims.

[0071] The contents not described in detail in this specification are common knowledge to those skilled in the art.

Claims

1. An integrated thermal insulation layer structure for a solid rocket motor, characterized in that, It includes a combustion chamber shell (1), a head artificial de-adhesion layer bottom layer (2), a tail artificial de-adhesion layer bottom layer (3), an integrated cylinder insulation layer (4), a thin film isolation paper I (5), and a thin film isolation paper II (6); The combustion chamber housing (1) has a front opening and a rear opening at both ends, the front opening is used to install the ignition device, and the rear opening is used to install the nozzle; The outer surface of the bottom layer (2) of the artificial debonding layer at the head is bonded to the inner surface of the arc section and the front end of the cylinder section of the combustion chamber shell (1) by adhesive, and the central hole of the artificial debonding layer (2) at the head is positioned and aligned with the front opening of the head of the combustion chamber shell (1). The outer surface of the bottom layer (3) of the tail artificial debonding layer is bonded to the inner surface of the tail section of the combustion chamber shell (1) by adhesive, and the tail end face of the tail artificial debonding layer (3) is positioned and aligned with the tail end face of the combustion chamber shell (1). A thin film release paper I (5) is laid on the inner surface area of ​​the head arc section and the front end of the cylindrical section of the head artificial debonding layer bottom layer (2); a thin film release paper II (6) is laid on the inner surface area of ​​the rear end of the tail artificial debonding layer bottom layer (3); The integrated cylindrical insulation layer (4) covers the combustion chamber shell (1). Its outer surface is bonded to the inner surface of the cylinder section of the combustion chamber shell (1), the inner surface of the bottom layer of the artificial debonding layer (2) at the head without the thin film isolation paper I (5), and the inner surface of the bottom layer of the artificial debonding layer (3) at the tail without the thin film isolation paper II (6). The central hole at the head of the integrated cylindrical insulation layer (4) is positioned and aligned with the front opening at the head of the combustion chamber shell (1), and the tail end face is positioned and aligned with the tail end face of the combustion chamber shell (1).

2. The integrated thermal insulation layer structure for a solid rocket motor according to claim 1, characterized in that, A thin film release paper I (5) is laid on the inner surface area of ​​the head arc segment and the front end of the cylindrical segment within 20±2mm of the bottom layer (2) of the artificial de-adhesion layer of the head.

3. The integrated thermal insulation layer structure for a solid rocket motor according to claim 1, characterized in that, The inner surface area of ​​the bottom layer (3) of the tail artificial de-adhesion layer (3) within 40±2mm from the tail end face of the combustion chamber shell is covered with thin film isolation paper II (6).

4. A method for manufacturing an integrated thermal insulation layer structure for a solid rocket motor, characterized in that, Includes the following steps: The artificial debonding layer of the head is formed by pressing the bottom layer of the artificial debonding layer using a head artificial debonding mold (2); The bottom layer of the artificial debonding layer at the tail is formed by pressing with a tail-end artificial debonding layer bottom molding die (3); An integrated cylindrical insulation layer is formed by pressing an integrated cylindrical insulation layer mold (4); Apply adhesive to the head and tail of the combustion chamber shell (1), and lay the head artificial debonding layer bottom layer (2) and the tail artificial debonding layer bottom layer (3); Thin film release paper I (5) is laid on the inner surface area of ​​the head arc section and the front end of the cylindrical section of the bottom layer of the head artificial debonding layer (2); Thin film release paper II (6) is laid on the inner surface area of ​​the rear end of the bottom layer of the tail artificial debonding layer (3); Airbags are used to squeeze the film release paper I (5) and film release paper II (6) to purge the air between the bottom layer (2) of the head artificial release layer and film release paper I (5), and between the bottom layer (3) of the tail artificial release layer and film release paper II (6). Apply adhesive to the inner surface of the combustion chamber shell (1) cylinder section, the inner surface of the head artificial debonding layer bottom layer (2) without thin film isolation paper, the inner surface of the tail artificial debonding layer bottom layer (3) without thin film isolation paper, and lay an integrated cylinder insulation layer (4). The air is expelled between the integrated cylindrical insulation layer (4) and the thin film isolation paper I (5) and the thin film isolation paper II (6) by using an airbag to compress the integrated cylindrical insulation layer (4); The laid head artificial debonding layer bottom layer (2), tail artificial debonding layer bottom layer (3) and integrated cylinder insulation layer (4) are vulcanized to obtain the molded integrated insulation layer structure.

5. The method for manufacturing the integrated thermal insulation layer structure of a solid rocket motor according to claim 4, characterized in that, The head artificial debonding layer bottom layer molding die includes an upper mold (7) for head artificial debonding layer bottom layer molding as a punch and a lower mold (8) for head artificial debonding layer bottom layer molding as a die; the forming surfaces of the upper mold (7) and the lower mold (8) are a combination of arc surface and cylindrical surface, which are consistent with the inner and outer surfaces of the head artificial debonding layer bottom layer (2), respectively; a central hole is opened at the rear end of the upper mold (7) for head artificial debonding layer bottom layer molding, and a central boss is machined at the front end of the lower mold (8) for head artificial debonding layer bottom layer molding. The central hole and the central boss cooperate to realize the alignment of the forming surfaces of the die and the punch.

6. The method for manufacturing the integrated thermal insulation layer structure of a solid rocket motor according to claim 5, characterized in that, The artificial debonding layer (2) of the head is formed by pressing the bottom mold of the head artificial debonding layer (2) by means of the following: the material with EPDM rubber as the base is laid on the bottom of the lower mold (8) of the head artificial debonding layer, the upper mold (7) of the head artificial debonding layer is placed in and the center hole is positioned and aligned with the center boss of the lower mold (8), the upper mold (7) of the head artificial debonding layer is pressurized and preformed to make the head artificial debonding layer (2).

7. The method for manufacturing the integrated thermal insulation layer structure of a solid rocket motor according to claim 4, characterized in that, The tail-end artificial debonding layer bottom molding die includes a tail-end artificial debonding layer bottom molding upper die (9) as a punch and a tail-end artificial debonding layer bottom molding lower die (10) as a die; the forming surfaces of the tail-end artificial debonding layer bottom molding upper die (9) and the tail-end artificial debonding layer bottom molding lower die (10) are cylindrical surfaces, which are consistent with the inner and outer surfaces of the tail-end artificial debonding layer bottom (3) respectively; a central hole is opened at the rear end of the tail-end artificial debonding layer bottom molding upper die (9), and a central boss is machined at the front end of the tail-end artificial debonding layer bottom molding lower die (10). The central hole and the central boss cooperate to realize the alignment of the forming surfaces of the die and the punch.

8. The method for manufacturing the integrated thermal insulation layer structure of a solid rocket motor according to claim 7, characterized in that, The tail artificial detack layer bottom layer (3) is formed by pressing the tail artificial detack layer bottom layer mold with the tail artificial detack layer bottom layer mold as follows: the material with EPDM rubber as the base is laid in the groove of the tail artificial detack layer bottom layer mold (9), the tail artificial detack layer bottom layer mold (10) is placed in it and the central boss is positioned and aligned with the central hole of the tail artificial detack layer bottom layer mold (9), the tail artificial detack layer bottom layer mold (9) is pressurized and pre-formed to make the tail artificial detack layer bottom layer (3).

9. The method for manufacturing the integrated thermal insulation layer structure of a solid rocket motor according to claim 4, characterized in that, The integrated cylindrical insulation layer molding die includes a punch assembly and a die assembly. The punch assembly includes an integrated cylindrical insulation layer molding center bottom die (13), an integrated cylindrical insulation layer molding forming die (14), an integrated cylindrical insulation layer molding center die (15), and an integrated cylindrical insulation layer molding center rod (16). The die assembly includes an integrated cylindrical insulation layer molding lower die (11) and an integrated cylindrical insulation layer molding upper die (12). The integrated cylindrical insulation layer molding center rod (16) is assembled from back to front with the integrated cylindrical insulation layer molding center bottom mold (13) and the integrated cylindrical insulation layer molding forming mold (14). The integrated cylindrical insulation layer molding center mold (15) is assembled inside the integrated cylindrical insulation layer molding forming mold (14). The outer side of the integrated cylindrical insulation layer molding forming mold (14) is machined with a circumferential groove. The length of the circumferential groove corresponds to the length of the cylindrical section of the combustion chamber shell (1). The combined surface of the outer surfaces of the integrated cylindrical insulation layer molding center bottom mold (13) and the integrated cylindrical insulation layer molding forming mold (14) is consistent with the inner surface of the integrated cylindrical insulation layer. After the integrated cylindrical insulation layer molding lower mold (11) and the integrated cylindrical insulation layer molding upper mold (12) are connected, a cavity is formed to accommodate the punch assembly. The inner surface of the cavity is consistent with the outer surface of the integrated cylindrical insulation layer. An annular groove is opened at the tail of the center hole of the integrated cylindrical insulation layer molding center bottom mold (13), which cooperates with the annular boss at the tail of the integrated cylindrical insulation layer molding center rod (16); an inner ring groove and an outer ring groove are opened on the front end face of the integrated cylindrical insulation layer molding center bottom mold (13), which cooperate with the rear end bosses of the integrated cylindrical insulation layer molding center mold (15) and the integrated cylindrical insulation layer molding forming mold (14), respectively; the front end diameter of the integrated cylindrical insulation layer molding center mold (15) is increased and an annular boss is opened, which forms a limit after docking with the front end annular groove of the integrated cylindrical insulation layer molding forming mold (14); the integrated cylindrical insulation layer molding center rod (16) is inserted into the center hole of the integrated cylindrical insulation layer molding lower mold (11) for alignment and passes through the center through hole of the integrated cylindrical insulation layer molding upper mold (12) for alignment.

10. The method for manufacturing the integrated thermal insulation layer structure of a solid rocket motor according to claim 9, characterized in that, The integrated cylindrical insulation layer (4) is formed by pressing an integrated cylindrical insulation layer with an integrated molding die, which is implemented in the following manner: The bottom mold (13) of the integrated cylindrical insulation layer molding center is fitted onto the center rod (16) of the integrated cylindrical insulation layer molding center, ensuring that the rear annular groove of the bottom mold (13) is positioned and aligned with the annular boss of the center rod (16); the molding die (14) of the integrated cylindrical insulation layer is fitted onto the center rod (16), ensuring that the rear boss of the molding die (14) is positioned and aligned with the front outer ring groove of the bottom mold (13); the molding die (14) of the integrated cylindrical insulation layer is then fitted onto the center rod (16), ensuring that the rear boss of the molding die (14) is positioned and aligned with the front outer ring groove of the bottom mold (13); the molding die (14) of the integrated cylindrical insulation layer is then fitted onto the center rod (16). The mold (15) is fitted onto the integrated cylindrical insulation layer molding center rod (16) to ensure that the rear end boss of the integrated cylindrical insulation layer molding center mold (15) is positioned and aligned with the front end inner ring groove of the integrated cylindrical insulation layer molding center bottom mold (13), and the front end annular boss is positioned and aligned with the front end annular groove of the integrated cylindrical insulation layer molding mold (14). The material with EPDM rubber as the base is laid on the annular groove on the outer surface of the integrated cylindrical insulation layer molding mold (14) and the outer surface of the integrated cylindrical insulation layer molding center bottom mold (13). Then, the whole thing is placed into the integrated cylindrical insulation layer molding lower mold (11), and the integrated cylindrical insulation layer molding upper mold (12) is used for pressure pre-forming to make the integrated cylindrical insulation layer (4).

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