Pressure measuring combined structure suitable for submerged solid orbit control engine thin-wall skin

Abstract

The invention relates to a pressure measuring combined structure suitable for a thin-wall skin of a submerged solid orbit control engine, and belongs to the field of submerged solid orbit control engines. Wherein the pressure measuring joint is axially and vertically arranged in a combustion chamber shell of an external orbit control engine; the outer wall of the axial bottom end of the pressure measuring connector is sleeved with the pressure measuring connector protection sleeve. A step through hole is formed in the axis of the pressure measuring joint; the pressure measuring plug coaxially extends into the step through hole of the pressure measuring joint from the top; the pressure measuring hole outer plug is arranged at the top of the pressure measuring plug, and the top of the pressure measuring hole outer plug extends out of the pressure measuring connector; the pressure measuring hole supporting seat is arranged on the outer wall of the butt joint position of the pressure measuring hole outer plug and the pressure measuring connector. The skin is horizontally laid on the upper surface of the pressure measuring hole supporting seat; according to the invention, the technical problem of the traditional pressure measuring structure in the aspect of internal and external thermal ablation resistance is effectively solved, and the working reliability of the solid orbit control engine and the environmental tolerance under high-temperature and high-heat flow are improved.

Description

Technical Field

[0001] This invention belongs to the field of submersible solid rocket motors and relates to a pressure measurement assembly structure suitable for thin-walled skin of submersible solid rocket motors. Background Technology

[0002] The pressure testing assembly is one of the most important components in the overall design of a submersible solid rocket motor. As a mechanical assembly for airtightness testing of the submersible solid rocket motor, it must ensure the reliability of the pressure testing assembly during the overall motor pressure testing process, and also guarantee its ablation resistance, safety, and environmental tolerance under the conditions of high internal and external heat and high heat flux after pressure testing. Currently, there is no detailed design scheme for the pressure testing assembly; the proposal for the pressure testing assembly is still in the functional description stage. Summary of the Invention

[0003] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a pressure measurement combination structure suitable for the thin-walled skin of submersible solid rocket motors. This effectively solves the technical difficulties of traditional pressure measurement structures in resisting internal and external thermal erosion, and improves the working reliability and environmental tolerance of solid rocket motors under high temperature and high heat flux.

[0004] The solution of the present invention is:

[0005] A pressure measurement assembly structure suitable for thin-walled skin of submersible solid rocket motor includes skin, pressure measurement port plug, pressure measurement port support, pressure measurement connector, pressure measurement plug, and pressure measurement connector protective sleeve;

[0006] The pressure testing connector is vertically installed axially within the combustion chamber housing of the external rail-controlled engine; a protective sleeve for the pressure testing connector is fitted onto the outer wall of the axial bottom end of the pressure testing connector; a stepped through hole is provided at the axis of the pressure testing connector; a pressure testing plug extends coaxially from the top into the stepped through hole of the pressure testing connector; an outer plug for the pressure testing hole is located on top of the pressure testing plug, and the top of the outer plug for the pressure testing hole extends beyond the pressure testing connector; a pressure testing hole support is located on the outer wall of the mating point between the outer plug for the pressure testing hole and the pressure testing connector; and a skin is laid horizontally on the upper surface of the pressure testing hole support.

[0007] The aforementioned pressure measurement assembly structure for thin-walled skin of submersible solid orbit control engines also includes a first sealing ring and a second sealing ring.

[0008] The first sealing ring is located at the junction of the outer wall of the pressure measuring plug and the inner wall of the pressure measuring connector; the second sealing ring is located at the junction of the outer wall of the pressure measuring connector and the inner wall of the external rail control engine combustion chamber housing.

[0009] In the aforementioned pressure measurement assembly structure applicable to the thin-walled skin of a submersible solid orbit control engine, the skin is a thin-walled, uniform-thickness circular ring structure formed by spinning high-strength alloy steel; the skin is the external load-bearing component of the pressure measurement assembly structure, and a Φ16mm through hole is opened on the skin.

[0010] In the aforementioned pressure measurement assembly structure applicable to the thin-walled skin of a submersible solid rocket motor, the pressure measurement hole plug is a cylindrical structure with an external thread and a tooling groove at the head; wherein, the thread length is 5.8mm and the height is 11.5mm; the outer diameter is a straight thread specification of M14×1.5-6g, and the outer diameter of the unthreaded part is 12.4mm; the tooling groove is 1mm deep, 8mm long, and 2mm wide; the pressure measurement hole plug is made of ablation-resistant high-silica phenolic resin as the base material.

[0011] In the aforementioned pressure measurement assembly structure applicable to the thin-walled skin of a submersible solid rocket motor, the pressure measurement hole support is a variable cross-section stepped hole structure with internal threads at the head; the outer circle of the pressure measurement hole support is arc-shaped with an arc diameter of 298.4 mm, the same as the inner diameter of the skin; the total height is 7.7 mm, the thread length is 4.2 mm, the thread specification is M14×1.5-7H, the maximum outer diameter is 24 mm, and the diameters of the two stepped holes below the thread are 17.2 mm and 20 mm, respectively; the outer circle of the pressure measurement hole support has two notches as mounting holes; the pressure measurement hole support uses TC4 titanium alloy as the base material to provide a mounting base for the skin and an installation interface for the pressure measurement hole plug.

[0012] In the aforementioned pressure measurement assembly structure applicable to the thin-walled skin of a submersible solid rocket motor, the pressure measuring connector is a multi-step circular rotating body with a variable diameter, a total height of 21mm, and a maximum outer diameter of 20mm. The head of the pressure measuring connector adopts a hexahedral structure; the maximum outer diameter of the hexahedron is 17mm, and the inner diameter is 14mm; the width between each face is 18mm, and the height of the hexahedron is 6.5mm. The stepped through-hole of the pressure measuring connector is a variable-diameter cylindrical inner hole, with diameters from top to bottom of 20mm, 17mm, and 1... 6mm; at the step with diameters of 20mm and 17mm, the inner wall is designed with an internal thread of M10×1.25-7H; the thread length is 6mm, and the inner diameter excluding the thread is 8.6mm; the middle of the pressure testing connector is provided with a sealing ring mounting groove, the groove width is 2.5mm, the height is 1.4mm, and the bottom diameter of the groove is 14.2mm; the 16mm diameter position in the pressure testing connector is the thread section, the thread specification is M16×1.5-6h, and the thread length is 6.2mm.

[0013] In the aforementioned pressure measurement assembly structure applicable to the thin-walled skin of a submersible solid rocket motor, the bottom of the pressure measurement connector is a variable cross-section boss with a height of 4mm, an outer diameter of 7mm, and an inner diameter of 3mm. An annular groove is designed in the middle of the boss, with a groove width of 1.5mm and an outer diameter of 6mm at the bottom. The top of the pressure measurement connector is connected to the outer plug of the pressure measurement hole, and the bottom is connected to the combustion chamber shell of the external rocket motor. Together with the second sealing ring, it ensures pressure measurement and sealing when the external rocket motor is working.

[0014] In the aforementioned pressure testing assembly structure applicable to the thin-walled skin of a submersible solid rocket motor, the pressure testing plug is made of stainless steel; the height of the pressure testing plug is 12.6mm, and the thread specification is M10×1.25-6h; the end face of the pressure testing plug is designed with a hexagonal tooling groove with a groove width of 5mm and a groove depth of 4mm; the pressure testing plug, together with the first sealing ring and the pressure testing connector, forms a sealing structure.

[0015] In the aforementioned pressure testing assembly structure applicable to the thin-walled skin of a submersible solid rocket motor, the pressure testing connector protective sleeve is a bowl-shaped structure; a variable diameter groove structure is provided at the axis of the pressure testing connector protective sleeve; the maximum outer diameter is 10mm, and the height is 6mm; the inner diameter of the variable diameter groove is 7mm, 8mm, 7mm, and 3mm from top to bottom, forming a stepped structure; the steps enable the putty to cooperate with the variable cross-section boss designed at the bottom of the pressure testing connector, so that the annular groove designed at the middle position of the bottom boss of the pressure testing connector and the annular groove with a diameter of 8mm in the middle of the pressure testing connector protective sleeve cooperate; an effective connection is formed at the annular groove by the overall adhesive force of the heat-resistant high-temperature putty; the pressure testing connector protective sleeve is a phenolic woven cotton rod.

[0016] The pressure measurement assembly structure described above, applicable to the thin-walled skin of a submersible solid rocket motor, is assembled as follows:

[0017] First, install the pressure testing connector protective sleeve and the pressure testing connector. During installation, apply an appropriate amount of high-temperature resistant putty between the annular groove of the pressure testing connector boss and the annular groove inside the pressure testing connector protective sleeve, and rotate them simultaneously to ensure the putty is tightly connected. After the putty has cured, install the pressure testing connector and the second sealing ring onto the external rail control engine combustion chamber housing. At the same time, apply an appropriate amount of high-temperature resistant putty to the 17.2mm position of the pressure testing hole support and install it onto the pressure testing connector. After adjusting the two notches of the pressure testing hole support to the required position using a tool, attach the skin to the upper surface of the pressure testing hole support. Finally, install the pressure testing plug and the first sealing ring.

[0018] The advantages of this invention compared to the prior art are:

[0019] (1) The present invention has a simple structure and good processing and installation process. Under the condition of making full use of the limited external structural dimensions, it proposes an overall design scheme for the pressure measurement combination structure of the thin-walled skin of the submersible solid orbit control engine, which meets the requirements of the field for reliable and safe use of the pressure measurement combination structure.

[0020] (2) This invention effectively solves the technical problems of traditional pressure measurement structures in resisting internal and external thermal erosion, and improves the working reliability of solid orbit control engines and their environmental tolerance under high temperature and high heat flux.

[0021] (3) The pressure testing connector of the present invention is a variable diameter multi-step circular structure with a hexahedral structure at the head. It is the main connecting component for connecting the submerged solid track control engine and the skin structure. The middle is designed with a through hole, which, together with the sealing ring, is used for the track control engine to be installed on the combustion chamber shell of the track control engine to ensure pressure testing and sealing when the track control engine is working. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall pressure measurement assembly structure of the present invention;

[0023] Figure 2 This is a schematic diagram of the pressure measuring hole plug of the present invention;

[0024] Figure 3 This is a schematic diagram of the pressure measuring hole support base of the present invention;

[0025] Figure 4 This is a schematic diagram of the pressure testing connector of the present invention. Detailed Implementation

[0026] The present invention will be further described below with reference to the embodiments.

[0027] This invention proposes a pressure measurement assembly structure suitable for the thin-walled skin of submersible solid rocket motors. The structure is simple, has good processing and installation capabilities, and effectively solves the technical problems of traditional pressure measurement structures in resisting internal and external thermal erosion. It improves the working reliability of solid rocket motors and their environmental tolerance under high temperature and high heat flux conditions.

[0028] A pressure measurement assembly structure suitable for thin-walled skin of a submersible solid rocket motor is characterized by comprising: skin 1, pressure measurement port plug 2, pressure measurement port support 3, pressure measurement connector 4, pressure measurement plug 5, pressure measurement connector protective sleeve 6, first sealing ring 7, and second sealing ring 8. The pressure measurement connector 4 is vertically mounted axially within the combustion chamber housing of the external rocket motor; the pressure measurement connector protective sleeve 6 is fitted onto the outer wall of the axial bottom end of the pressure measurement connector 4; a stepped through hole is provided at the axis of the pressure measurement connector 4; the pressure measurement plug 5 extends coaxially from the top into the stepped through hole of the pressure measurement connector 4; the pressure measurement port plug 2 is located on top of the pressure measurement plug 5, and the top of the pressure measurement port plug 2 extends beyond the pressure measurement connector 4; the pressure measurement port support 3 is located on the outer wall of the mating point between the pressure measurement port plug 2 and the pressure measurement connector 4; and the skin 1 is horizontally laid on the upper surface of the pressure measurement port support 3. The first sealing ring 7 is located at the junction of the outer wall of the pressure measuring plug 5 and the inner wall of the pressure measuring connector 4; the second sealing ring 8 is located at the junction of the outer wall of the pressure measuring connector 4 and the inner wall of the external rail control engine combustion chamber housing.

[0029] Skin 1 is a thin-walled, uniform-thickness circular ring structure formed by spinning high-strength alloy steel; Skin 1 is an external load-bearing component of the pressure measurement assembly structure, and a Φ16mm through hole is opened on Skin 1.

[0030] like Figure 2 As shown, the pressure testing hole plug 2 is a cylindrical structure with an external thread and a tooling groove on the head; the thread length is 5.8mm and the height is 11.5mm; the outer diameter is a straight thread specification of M14×1.5-6g, and the outer diameter of the unthreaded part is 12.4mm; the tooling groove is 1mm deep, 8mm long and 2mm wide; the pressure testing hole plug 2 is made of ablation-resistant high-silica phenolic resin as the base material.

[0031] The main function of the pressure measuring hole plug 2 is to withstand the external aerodynamic heat of the pressure measuring assembly structure during the flight of the aircraft, and to ensure the stability of the internal thermal environment of the submersible solid orbit control engine.

[0032] like Figure 3 As shown, the pressure testing hole support 3 is a variable cross-section stepped hole structure with internal threads at the head; the outer circle of the pressure testing hole support 3 is arc-shaped with an arc diameter of 298.4 mm, which is the same as the inner diameter of the skin 1; the total height is 7.7 mm, the thread length is 4.2 mm, the thread specification is M14×1.5-7H, the maximum outer circle diameter is 24 mm, and the diameters of the two stepped holes below the thread are 17.2 mm and 20 mm, respectively; the outer circle of the pressure testing hole support 3 is provided with two notches as mounting holes; the pressure testing hole support 3 uses TC4 titanium alloy as the base material to provide a mounting base for the skin 1 and a mounting interface for the pressure testing hole plug 2.

[0033] like Figure 4As shown, the pressure testing connector 4 is a multi-step circular rotating body with a variable diameter, a total height of 21mm, and a maximum outer diameter of 20mm. The head of the pressure testing connector 4 adopts a hexahedral structure; the maximum outer diameter of the hexahedron is 17mm, and the inner diameter is 14mm; the width between each face is 18mm, and the height of the hexahedron is 6.5mm. The stepped through hole of the pressure testing connector 4 is a variable diameter cylindrical inner hole, with diameters of 20mm, 17mm, and 16mm from top to bottom. At the steps with diameters of 20mm and 17mm, the inner wall is designed with an internal thread of M10×1.25-7H; the thread length is 6mm, and the inner hole diameter excluding the thread is 8.6mm. A sealing ring mounting groove is provided in the middle of the pressure testing connector 4, with a groove width of 2.5mm, a height of 1.4mm, and a bottom diameter of 14.2mm. The 16mm diameter section in the pressure testing connector 4 is a threaded section with a thread specification of M16×1.5-6h and a thread length of 6.2mm. The bottom of the pressure testing connector 4 is a variable cross-section boss with a height of 4mm, an outer diameter of 7mm, and an inner diameter of 3mm. An annular groove is designed in the middle of the boss with a width of 1.5mm and an outer diameter of 6mm at the bottom. The top of the pressure testing connector 4 is connected to the pressure testing hole plug 2, and the bottom is connected to the combustion chamber shell of the external rail control engine. Together with the second sealing ring 8, it ensures pressure testing and sealing when the external rail control engine is working.

[0034] The pressure testing connector 4 is the main connecting component that connects the submerged solid track control engine to the skin structure. The upper end is connected to the pressure testing hole plug 2, and the lower end is connected to the combustion chamber shell of the submerged solid track control engine. Together with the second sealing ring 8, it ensures pressure testing and sealing during the operation of the track control engine.

[0035] The pressure measuring plug 5 of the present invention is made of stainless steel; the height of the pressure measuring plug 5 is 12.6mm, and the thread specification is M10×1.25-6h; the end face of the pressure measuring plug 5 is designed with a hexagonal tooling groove with a groove width of 5mm and a groove depth of 4mm; the pressure measuring plug 5, together with the first sealing ring 7 and the pressure measuring connector 4, forms a sealing structure.

[0036] The pressure testing connector protective sleeve 6 has a bowl-shaped structure; a variable diameter groove structure is provided at the axis of the pressure testing connector protective sleeve 6; the maximum outer diameter is 10mm and the height is 6mm; the inner diameter of the variable diameter groove is 7mm, 8mm, 7mm and 3mm from top to bottom, forming a stepped structure; the steps enable the putty to cooperate with the variable cross-section boss designed at the bottom of the pressure testing connector 4, so that the annular groove designed at the middle position of the bottom boss of the pressure testing connector 4 and the annular groove with a diameter of 8mm in the middle of the pressure testing connector protective sleeve 6 cooperate; an effective connection is formed at the annular groove by the overall adhesive force of the heat-resistant high-temperature putty; the pressure testing connector protective sleeve 6 is a phenolic woven cotton rod.

[0037] The central step of the pressure testing connector protective sleeve 6 is designed to work with the variable cross-section boss at the bottom of the pressure testing connector 4 using putty. This allows the annular groove in the middle of the bottom boss of the pressure testing connector 4 to match the 1.5mm long annular groove in the middle of the pressure testing connector protective sleeve 6 (8mm long). The overall adhesive force of the heat-resistant high-temperature putty at the annular groove forms an effective connection, ensuring the structural integrity and thermal protection reliability of the pressure testing assembly structure during the operation of the solid rocket motor. The material of the pressure testing connector protective sleeve 6 is phenolic woven cotton cloth rod.

[0038] The assembly process of the pressure testing assembly structure is as follows:

[0039] First, install the pressure testing connector protective sleeve 6 and the pressure testing connector 4. During installation, apply an appropriate amount of high-temperature resistant putty between the annular groove of the boss on the pressure testing connector 4 and the annular groove inside the pressure testing connector protective sleeve 6, while rotating them to ensure the putty is tightly connected. After the putty cures, install the pressure testing connector 4 and the second sealing ring 8 onto the external rail control engine combustion chamber shell. Simultaneously, apply an appropriate amount of high-temperature resistant putty to the 17.2mm position of the pressure testing hole support 3 and install it onto the pressure testing connector 4. Using a tool, adjust the two notches of the pressure testing hole support 3 to the required position for mounting holes, and then attach the skin 1 to the upper surface of the pressure testing hole support 3. Finally, install the pressure testing plug 5 and the first sealing ring 7. This ultimately forms a reliable pressure testing assembly structure suitable for the thin-walled skin of a submerged solid rocket motor.

[0040] This invention has a simple structure and good processing and installation capabilities. It proposes an overall design scheme for a pressure measurement assembly structure of a thin-walled skin for a submersible solid rocket motor while making full use of the limited external structural dimensions. This meets the requirements of the field for reliable and safe use of pressure measurement assembly structures.

[0041] This invention effectively solves the technical problems of traditional pressure measurement structures in resisting internal and external thermal erosion, and improves the working reliability of solid orbit control engines and their environmental tolerance under high temperature and high heat flux.

[0042] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present 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 technical solutions of the present invention.

Claims

1. A pressure measurement assembly structure suitable for thin-walled skin of submersible solid rocket motors, characterized in that: Includes skin (1), pressure test hole plug (2), pressure test hole support (3), pressure test connector (4), pressure test plug (5), and pressure test connector protective sleeve (6); Among them, the pressure measuring connector (4) is vertically installed in the outer combustion chamber shell of the external rail control engine; the pressure measuring connector protective sleeve (6) is fitted on the outer wall of the bottom axial end of the pressure measuring connector (4); a stepped through hole is provided at the axis of the pressure measuring connector (4); the pressure measuring plug (5) extends coaxially from the top into the stepped through hole of the pressure measuring connector (4); the pressure measuring hole outer plug (2) is set on the top of the pressure measuring plug (5), and the top of the pressure measuring hole outer plug (2) extends out of the pressure measuring connector (4); the pressure measuring hole support (3) is set on the outer wall of the joint between the pressure measuring hole outer plug (2) and the pressure measuring connector (4); the skin (1) is laid horizontally on the upper surface of the pressure measuring hole support (3).

2. The pressure measurement assembly structure for thin-walled skin of a submersible solid rocket motor according to claim 1, characterized in that: It also includes a first sealing ring (7) and a second sealing ring (8); The first sealing ring (7) is located at the junction of the outer wall of the pressure measuring plug (5) and the inner wall of the pressure measuring connector (4); the second sealing ring (8) is located at the junction of the outer wall of the pressure measuring connector (4) and the inner wall of the external rail control engine combustion chamber housing.

3. The pressure measurement assembly structure for thin-walled skin of a submersible solid rocket motor according to claim 1, characterized in that: The skin (1) is a thin-walled, uniform-thickness circular ring structure formed by spinning high-strength alloy steel; the skin (1) is an external load-bearing component of the pressure measurement assembly structure, and a through hole of Φ16mm is opened on the skin (1).

4. The pressure measurement assembly structure for thin-walled skin of a submersible solid rocket motor according to claim 1, characterized in that: The pressure testing hole plug (2) is a cylindrical structure with an external thread and a tooling groove on the head; the thread length is 5.8 mm and the height is 11.5 mm; the outer diameter is M14×1.5-6g for straight thread and 12.4 mm for the unthreaded part; the tooling groove is 1 mm deep, 8 mm long and 2 mm wide; the pressure testing hole plug (2) is made of ablation-resistant high-silica phenolic resin as the base material.

5. The pressure measurement assembly structure for thin-walled skin of a submersible solid rocket motor according to claim 1, characterized in that: The pressure testing hole support (3) is a variable cross-section stepped hole structure with internal threads at the head; the outer circle of the pressure testing hole support (3) is arc-shaped with an arc diameter of 298.4 mm, which is the same as the inner diameter of the skin (1); the total height is 7.7 mm, the thread length is 4.2 mm, the thread specification is M14×1.5-7H, the maximum outer circle diameter is 24 mm, and the diameters of the two stepped holes below the thread are 17.2 mm and 20 mm, respectively; the outer circle of the pressure testing hole support (3) is provided with two notches as mounting holes; the pressure testing hole support (3) is made of TC4 titanium alloy as the base material, which provides a mounting base for the skin (1) and a mounting interface for the pressure testing hole plug (2).

6. The pressure measurement assembly structure for thin-walled skin of a submersible solid rocket motor according to claim 1, characterized in that: The pressure testing connector (4) is a multi-step circular rotating body with a variable diameter, a total height of 21mm, and a maximum outer diameter of 20mm. The head of the pressure testing connector (4) adopts a hexahedral structure. The maximum outer diameter of the hexahedron is 17mm, and the inner diameter is 14mm. The width between each face is 18mm, and the height of the hexahedron is 6.5mm. The stepped through hole of the pressure testing connector (4) is a variable diameter cylindrical inner hole with diameters of 20mm, 17mm, and 16mm from top to bottom. At the 17mm diameter step, the inner wall is designed with an internal thread of M10×1.25-7H; the thread length is 6mm, and the inner diameter excluding the thread is 8.6mm; the middle of the pressure testing connector (4) is provided with a sealing ring installation groove, the groove width is 2.5mm, the height is 1.4mm, and the bottom diameter of the groove is 14.2mm; the 16mm diameter position in the pressure testing connector (4) is the thread section, the thread specification is M16×1.5-6h, and the thread length is 6.2mm.

7. The pressure measurement assembly structure for thin-walled skin of a submersible solid rocket motor according to claim 6, characterized in that: The bottom of the pressure testing connector (4) is a variable cross-section boss with a height of 4mm, an outer diameter of 7mm, and an inner diameter of 3mm. An annular groove is designed in the middle of the boss with a groove width of 1.5mm and an outer diameter of 6mm at the bottom. The top of the pressure testing connector (4) is connected to the pressure testing hole plug (2), and the bottom is connected to the combustion chamber shell of the external rail control engine. Together with the second sealing ring (8), it ensures pressure testing and sealing when the external rail control engine is working.

8. The pressure measurement assembly structure for thin-walled skin of a submersible solid rocket motor according to claim 1, characterized in that: The pressure measuring plug (5) is made of stainless steel; the height of the pressure measuring plug (5) is 12.6mm, and the thread specification is M10×1.25-6h; the end face of the pressure measuring plug (5) is designed with a hexagonal tooling groove with a groove width of 5mm and a groove depth of 4mm; the pressure measuring plug (5), together with the first sealing ring (7) and the pressure measuring connector (4), forms a sealing structure.

9. The pressure measurement assembly structure for thin-walled skin of a submersible solid rocket motor according to claim 1, characterized in that: The pressure testing connector protective sleeve (6) has a bowl-shaped structure; a variable diameter groove structure is provided at the axis of the pressure testing connector protective sleeve (6); the maximum outer diameter is 10mm and the height is 6mm; the inner diameter of the variable diameter groove is 7mm, 8mm, 7mm and 3mm from top to bottom, forming a stepped structure; the steps enable the putty to cooperate with the variable cross-section boss designed at the bottom of the pressure testing connector (4), so that the annular groove designed at the middle position of the bottom boss of the pressure testing connector (4) and the annular groove with a diameter of 8mm in the middle of the pressure testing connector protective sleeve (6) cooperate; an effective connection is formed at the annular groove by the overall adhesive force of the heat-resistant high-temperature putty; the pressure testing connector protective sleeve (6) is a phenolic woven cotton rod.

10. The pressure measurement assembly structure for thin-walled skin of a submersible solid rocket motor according to claim 1, characterized in that: The assembly process of the pressure testing assembly structure is as follows: First, install the pressure testing connector protective sleeve (6) and the pressure testing connector (4); during the installation process, apply an appropriate amount of high-temperature resistant putty between the annular groove of the boss of the pressure testing connector (4) and the annular groove inside the pressure testing connector protective sleeve (6), and rotate them at the same time to make the putty between them tightly connected; after the putty is cured, install the pressure testing connector (4) and the second sealing ring (8) on the outer rail control engine combustion chamber shell; at the same time, apply an appropriate amount of high-temperature resistant putty to the position of the 17.2mm position of the pressure testing hole support seat (3) and install it on the pressure testing connector (4); after adjusting the two notches of the pressure testing hole support seat (3) to the required position using tooling, attach the skin (1) to the upper surface of the pressure testing hole support seat (3); finally, install the pressure testing plug (5) and the first sealing ring (7).

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