Hydraulic test tool for jet pipe shell of solid rocket engine

Abstract

The utility model relates to the field of solid rocket engines, in particular to a solid rocket engine jet pipe shell hydraulic pressure test tool which comprises a combustion chamber shell simulation part, a sealing ring, a clamping ring, an ignition hole plug, an ignition hole sealing gasket, a jet pipe tail sealing ring, a jet pipe tail plug, a pressure measuring hole plug and a pressure measuring hole sealing ring. The spray pipe shell is in butt joint with the combustion chamber shell simulation piece; the sealing ring is located between the spray pipe shell and the combustion chamber shell simulation piece; the clamping ring is connected with the spray pipe shell and the combustion chamber shell simulation piece; the ignition hole plug is installed in an ignition hole of the spray pipe shell, and the ignition hole sealing gasket is located between the ignition hole plug and the ignition hole. The pressure measuring hole plug is installed in a pressure measuring hole of the spray pipe shell, and the pressure measuring hole sealing ring is located between the pressure measuring hole plug and the pressure measuring hole. The spray pipe tail plug is provided with a water inlet hole and installed in the spray outlet of the spray pipe shell, and the spray pipe tail sealing ring is located between the spray pipe tail plug and the spray outlet. The device can be used for carrying out a hydrostatic test on the spray pipe shell.

Description

Technical Field

[0001] The present application relates to the field of solid rocket engines, and particularly to a water pressure test tooling for a nozzle housing of a solid rocket engine. Background Art

[0002] Solid rocket engines are simple in structure, convenient to maintain, high in reliability, and easy to operate, and are widely used in missile power systems. The nozzle is an energy conversion device of a solid rocket engine, which converts the heat of the gas generated by the combustion of the propellant into kinetic energy, thereby generating thrust. During the operation of a solid rocket engine, the nozzle housing is a load-bearing member of the nozzle assembly, and its structural integrity is crucial for the normal operation of the engine. Regarding the structural integrity of the nozzle housing during the operation of a solid rocket engine, although commercial finite element simulation software can currently be used for calculation and analysis, and the simulation accuracy can meet the requirements of engineering applications, many factors will affect the load-bearing of the nozzle housing from raw materials to the final product forming. Therefore, it is usually stipulated in engineering that the nozzle housing needs to pass a water pressure test for acceptance before delivery.

[0003] Therefore, how to conduct a water pressure test on the nozzle housing to effectively evaluate the structural integrity of the nozzle housing during the operation of the engine is a technical problem that needs to be solved urgently by those skilled in the art at present. Summary of the Utility Model

[0004] The present application provides a water pressure test tooling for a nozzle housing of a solid rocket engine, which can be used for the water pressure test of nozzle housings of various types of solid rocket engines. Its structure is simple and reliable, and the connection and sealing methods of each interface are consistent with those of the solid rocket engine, and it can effectively evaluate the structural integrity of the nozzle housing during the operation of the engine.

[0005] To solve the above technical problems, the present application provides the following technical solutions:

[0006] A hydrostatic test tooling for the nozzle shell of a solid rocket motor, comprising: a combustion chamber shell simulation part, a sealing ring, a snap ring, an ignition hole plug, an ignition hole gasket, a nozzle tail sealing ring, a nozzle tail plug, a pressure measuring hole plug and a pressure measuring hole sealing ring; the combustion chamber shell simulation part has a cavity concave forward from its rear end, and the front end of the nozzle shell is butted against the rear end of the combustion chamber shell simulation part; the sealing ring is located between the front end of the nozzle shell and the rear end of the combustion chamber shell simulation part; the snap ring connects the front end of the nozzle shell and the rear end of the combustion chamber shell simulation part; the ignition hole plug is installed into the ignition hole of the nozzle shell, and the ignition hole gasket is located between the ignition hole plug and the inner wall of the ignition hole; the pressure measuring hole plug is installed in the pressure measuring hole of the nozzle shell, and the pressure measuring hole sealing ring is located between the pressure measuring hole plug and the inner wall of the pressure measuring hole; the nozzle tail plug has a water inlet hole penetrating through both ends, and the nozzle tail plug is installed into the nozzle outlet at the rear end of the nozzle shell, and the nozzle tail sealing ring is located between the nozzle tail plug and the nozzle outlet of the nozzle shell.

[0007] The hydrostatic test tooling for the nozzle shell of a solid rocket motor as described above, wherein, preferably, the combustion chamber shell simulation part is of a rotary body structure.

[0008] The hydrostatic test tooling for the nozzle shell of a solid rocket motor as described above, wherein, preferably, the inner surface of the cavity of the combustion chamber shell simulation part is an ellipsoidal or spherical surface.

[0009] The hydrostatic test tooling for the nozzle shell of a solid rocket motor as described above, wherein, preferably, the part of the rear end of the combustion chamber shell simulation part close to the cavity is recessed inward to form a butting surface for butting against the front end surface of the nozzle shell.

[0010] The hydrostatic test tooling for the nozzle shell of a solid rocket motor as described above, wherein, preferably, the butting surface of the combustion chamber shell simulation part also protrudes outward with a sealing protrusion, and the front end surface of the nozzle shell is recessed inward with a sealing groove, and the sealing protrusion extends into the sealing groove.

[0011] The hydrostatic test tooling for the nozzle shell of a solid rocket motor as described above, wherein, preferably, the front end surface of the nozzle shell has a nozzle shell sealing groove, and the nozzle shell sealing groove is away from the axis of the nozzle shell relative to the sealing groove, and the sealing ring is arranged in the nozzle shell sealing groove.

[0012] The hydrostatic test tooling for the nozzle shell of a solid rocket motor as described above, wherein, preferably, the side wall of the combustion chamber shell simulation part has a circumferential positioning groove, and the positioning groove is located at the rear side of the butting surface of the combustion chamber shell simulation part, the outer side of the snap ring is clamped into the positioning groove, and the inner side of the snap ring abuts against the rear side surface of the front end of the nozzle shell.

[0013] The hydrostatic test tooling for the nozzle housing of a solid rocket motor as described above, wherein preferably, the ignition hole plug is stepped, the small-diameter section of the ignition hole plug has an ignition hole sealing groove, the ignition hole gasket is arranged in the ignition hole sealing groove, and the small-diameter section of the ignition hole plug is inserted and installed into the ignition hole.

[0014] The hydrostatic test tooling for the nozzle housing of a solid rocket motor as described above, wherein preferably, the pressure measurement hole plug is stepped, the small-diameter section of the pressure measurement hole plug has a pressure measurement hole sealing groove, the pressure measurement hole sealing ring is arranged in the pressure measurement hole sealing groove, and the small-diameter section of the pressure measurement hole plug is inserted and installed into the pressure measurement hole.

[0015] The hydrostatic test tooling for the nozzle housing of a solid rocket motor as described above, wherein preferably, the nozzle tail plug is three-stepped, the large-diameter section of the nozzle tail plug has a nozzle tail sealing groove, the nozzle tail sealing ring is arranged in the nozzle tail sealing groove, and the large-diameter section of the nozzle tail plug is inserted and installed into the nozzle outlet of the nozzle housing.

[0016] Beneficial effects:

[0017] The hydrostatic test tooling for the nozzle housing of the solid rocket motor of the present application can be used for the hydrostatic test of nozzle housings of various types of solid rocket motors. It has the characteristics of simple structure, high reliability, and comprehensive simulation of reality, and can effectively evaluate the structural integrity of the nozzle housing during the operation of the motor. Description of the drawings

[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments recorded in the present application. For those of ordinary skill in the art, other drawings can also be obtained based on these drawings.

[0019] Figure 1 is a cross-sectional view of the hydrostatic test tooling for the nozzle housing of the solid rocket motor provided by the present application;

[0020] Figure 2 is a three-dimensional view of the hydrostatic test tooling for the nozzle housing of the solid rocket motor provided by the present application;

[0021] Wherein, 1 - combustion chamber housing simulation part, 2 - sealing ring, 3 - snap ring, 4 - ignition hole plug, 5 - ignition hole gasket, 6 - nozzle tail sealing ring, 7 - nozzle tail plug, 8 - pressure measurement hole plug, 9 - pressure measurement hole sealing ring. Detailed implementation manners

[0022] Embodiments of the present application will be described in detail below. Examples of the embodiments are shown in the accompanying drawings, where like or similar reference numerals denote like or similar elements or elements having the same or similar functions throughout. Additionally, spatial relationship terms such as "upper", "lower", "left", "right", "front", "rear", etc. are used to facilitate the description and explain the positional relationship between two components. The embodiments described below by referring to the accompanying drawings are exemplary and are only used to explain the present application and should not be construed as a limitation to the present application.

[0023] As Figure 1 and Figure 2 shown, the present application provides a hydrostatic test tooling for the nozzle shell of a solid rocket motor, including: a combustion chamber shell simulation part 1, a sealing ring 2, a snap ring 3, an ignition hole plug 4, an ignition hole gasket 5, a nozzle tail sealing ring 6, a nozzle tail plug 7, a pressure measurement hole plug 8, and a pressure measurement hole sealing ring 9.

[0024] The nozzle shell to be subjected to the hydrostatic test penetrates from front to back, and the nozzle shell has ignition holes and pressure measurement holes that penetrate inside and outside. Optionally, the ignition holes and pressure measurement holes are located in the convergent section of the nozzle shell. Optionally, the ignition holes and pressure measurement holes are symmetrically distributed with respect to the axis of the nozzle shell. Optionally, the side walls of the ignition holes and pressure measurement holes bulge outwards to facilitate the installation of the ignition hole plug 4 and the nozzle tail plug 7.

[0025] Among them, the combustion chamber shell simulation part 1 has a cavity that is concave forward from its rear end. The front end of the nozzle shell is docked with the rear end of the combustion chamber shell simulation part 1 to close the cavity of the combustion chamber shell simulation part 1; and the sealing ring 2 is located between the front end of the nozzle shell and the rear end of the combustion chamber shell simulation part 1 to seal the docking part between the nozzle shell and the combustion chamber shell simulation part 1; the snap ring 3 connects the front end of the nozzle shell and the rear end of the combustion chamber shell simulation part 1 to fix the front end of the nozzle shell and the rear end of the combustion chamber shell simulation part 1. This can make the connection and sealing method between the rear end of the combustion chamber shell simulation part 1 and the front end of the nozzle shell consistent with that of the solid rocket motor.

[0026] Optionally, the combustion chamber shell simulation part 1 is of a rotational body structure. Optionally, the material of the combustion chamber shell simulation part 1 is the same as that of the combustion chamber shell of the solid rocket motor. Optionally, the inner surface of the cavity of the combustion chamber shell simulation part 1 is an ellipsoidal or spherical surface, and the outer surface of the combustion chamber shell simulation part 1 is a plane.

[0027] Optionally, a part of the rear end of the combustion chamber housing simulation part 1 close to the cavity is recessed inward to form a docking surface for contacting and docking with the front end surface of the nozzle housing. Optionally, a sealing protrusion protrudes outward on the docking surface of the combustion chamber housing simulation part 1, and a sealing groove is recessed inward on the front end surface of the nozzle housing. The sealing protrusion extends into the sealing groove to achieve a sealing effect. Optionally, the front end surface of the nozzle housing further has a nozzle housing sealing groove, and the nozzle housing sealing groove is farther from the axis of the nozzle housing than the sealing groove. The sealing ring 2 is arranged in the nozzle housing sealing groove. After the front end surface of the nozzle housing contacts and docks with the docking surface of the combustion chamber housing simulation part 1, the sealing ring 2 is squeezed to achieve a sealing effect.

[0028] Optionally, the side wall of the combustion chamber housing simulation part 1 has a circumferential positioning groove, and the positioning groove is located at the rear side of the docking surface of the combustion chamber housing simulation part 1. The outer side (the side far from the axis of the nozzle housing) of the snap ring 3 is clamped into the positioning groove, and the inner side (the side close to the axis of the nozzle housing) of the snap ring 3 abuts against the rear side surface of the front end of the nozzle housing, so as to realize the fixed connection between the front end of the nozzle housing and the rear end of the combustion chamber housing simulation part 1.

[0029] The ignition hole plug 4 is installed in the ignition hole to close the ignition hole; the ignition hole gasket 5 is located between the ignition hole plug 4 and the inner wall of the ignition hole to seal the connection between the ignition hole plug 4 and the ignition hole. The pressure measurement hole plug 8 is installed in the pressure measurement hole to close the pressure measurement hole; the pressure measurement hole sealing ring 9 is located between the pressure measurement hole plug 8 and the inner wall of the pressure measurement hole to seal the connection between the pressure measurement hole plug 8 and the pressure measurement hole. In this way, the connection and sealing method between the ignition hole plug 4 and the nozzle housing can be kept consistent with the connection and sealing method between the electric ignition tube of the solid rocket motor and the nozzle housing, and similarly, the connection and sealing method between the pressure measurement hole plug 8 and the nozzle housing can be kept consistent with the connection and sealing method between the pressure sensor of the solid rocket motor and the nozzle housing.

[0030] Optionally, the ignition hole plug 4 is in a stepped shape, and the small-diameter section of the ignition hole plug 4 is inserted and installed into the ignition hole. Optionally, the small-diameter section of the ignition hole plug 4 has an ignition hole sealing groove, and the ignition hole gasket 5 is arranged in the ignition hole sealing groove. After the small-diameter section of the ignition hole plug 4 is inserted and installed into the ignition hole, the ignition hole gasket 5 is squeezed to achieve a sealing effect. Similarly optionally, the pressure measurement hole plug 8 is in a stepped shape, and the small-diameter section of the pressure measurement hole plug 8 is inserted and installed into the pressure measurement hole. Optionally, the small-diameter section of the pressure measurement hole plug 8 has a pressure measurement hole sealing groove, and the pressure measurement hole sealing ring 9 is arranged in the pressure measurement hole sealing groove. After the small-diameter section of the pressure measurement hole plug 8 is inserted and installed into the pressure measurement hole, the pressure measurement hole sealing ring 9 is squeezed to achieve a sealing effect.

[0031] The nozzle tail plug 7 has a water inlet hole that penetrates both ends, and the nozzle tail plug 7 is installed into the nozzle outlet at the rear end of the nozzle housing to seal the nozzle outlet of the nozzle housing; the nozzle tail sealing ring 6 is located between the nozzle tail plug 7 and the nozzle outlet of the nozzle housing to seal the connection between the nozzle tail plug 7 and the nozzle outlet of the nozzle housing.

[0032] Optionally, the nozzle tail plug 7 has three stepped shapes, and the large-diameter section of the nozzle tail plug 7 is inserted and installed into the nozzle outlet of the nozzle housing, and the small-diameter section of the nozzle tail plug 7 is used to connect the water inlet pipe. Optionally, the large-diameter section of the nozzle tail plug 7 has a nozzle tail sealing groove, and the nozzle tail sealing ring 6 is arranged in the nozzle tail sealing groove. After the large-diameter section of the nozzle tail plug 7 is inserted and installed into the nozzle outlet of the nozzle housing, the nozzle tail sealing ring 6 is squeezed to play a sealing role.

[0033] During general assembly, install the nozzle tail sealing ring 6 in the nozzle tail sealing groove outside the nozzle tail plug 7 and apply a small amount of grease. Then insert the nozzle tail plug 7 into the nozzle outlet at the rear end of the nozzle housing. Then install the sealing ring 2 at the sealing groove of the nozzle housing and apply a small amount of grease. Then install the nozzle housing and the combustion chamber housing simulation part 1 together with the snap ring 3. Finally, install the ignition hole plug 4 and the ignition hole sealing ring 5 in the ignition hole, and install the pressure measurement hole plug 8 and the pressure measurement hole sealing ring 9 in the pressure measurement hole.

[0034] When performing a hydrostatic test on the nozzle housing, first fill the cavity formed by the combustion chamber housing simulation part 1 and the nozzle housing with water through the water inlet hole of the nozzle tail plug 7. Then connect the water inlet hole of the nozzle tail plug 7 to the water inlet pipe. Finally, pressurize through a pump to gradually increase the water pressure to the required pressure to assess the structural integrity of the nozzle housing.

[0035] The hydrostatic test tooling for the nozzle housing of the solid rocket engine of the present application can be used for the hydrostatic test of the nozzle housing of various types of solid rocket engines. It has the characteristics of simple structure and high reliability, and can also make the connection and sealing methods of each interface consistent with the solid rocket engine, and can effectively assess the structural integrity of the nozzle housing during the operation of the engine.

[0036] For those skilled in the art, it is obvious that the present application is not limited to the details of the above exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or basic characteristics of the present application. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present application is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present application. Any reference signs in the claims should not be regarded as limiting the claimed rights.

[0037] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only contains an independent technical solution. This narrative manner of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A hydrostatic test tooling for the nozzle shell of a solid rocket motor, characterized in that, Including: A combustion chamber housing simulation piece, a sealing ring, a snap ring, an ignition hole plug, an ignition hole gasket, a nozzle tail sealing ring, a nozzle tail plug, a pressure measuring hole plug, and a pressure measuring hole sealing ring; The combustion chamber housing simulation piece has a cavity that is concave forward from its rear end, and the front end of the nozzle housing is butted against the rear end of the combustion chamber housing simulation piece; the sealing ring is located between the front end of the nozzle housing and the rear end of the combustion chamber housing simulation piece; the snap ring connects the front end of the nozzle housing and the rear end of the combustion chamber housing simulation piece; The ignition hole plug is installed into the ignition hole of the nozzle housing, and the ignition hole gasket is located between the ignition hole plug and the inner wall of the ignition hole; the pressure measuring hole plug is installed in the pressure measuring hole of the nozzle housing, and the pressure measuring hole sealing ring is located between the pressure measuring hole plug and the inner wall of the pressure measuring hole; The nozzle tail plug has a water inlet hole penetrating through both ends, and the nozzle tail plug is installed into the nozzle outlet at the rear end of the nozzle housing, and the nozzle tail sealing ring is located between the nozzle tail plug and the nozzle outlet of the nozzle housing.

2. The hydrostatic test tooling for the nozzle housing of a solid rocket motor according to claim 1, wherein The combustion chamber housing simulation piece is of a rotary body structure.

3. The hydrostatic test tooling for the nozzle housing of a solid rocket motor according to claim 1 or 2, characterized in that, The inner surface of the cavity of the combustion chamber housing simulation piece is an ellipsoidal or spherical surface.

4. The hydrostatic test tooling for the nozzle housing of a solid rocket motor according to claim 1 or 2, characterized in that The part of the rear end of the combustion chamber housing simulation piece close to the cavity is recessed inward to form a butting surface for butting against the front end surface of the nozzle housing.

5. The hydrostatic test tooling for the nozzle housing of a solid rocket motor according to claim 4, characterized in that, The butting surface of the combustion chamber housing simulation piece also protrudes outward with a sealing protrusion, and the front end surface of the nozzle housing is recessed inward with a sealing groove, and the sealing protrusion extends into the sealing groove.

6. The hydrostatic test tooling for the nozzle housing of a solid rocket motor according to claim 5, characterized in that, The front end surface of the nozzle housing has a nozzle housing sealing groove, and the nozzle housing sealing groove is farther from the axis of the nozzle housing than the sealing groove, and the sealing ring is arranged in the nozzle housing sealing groove.

7. The hydrostatic test tooling for the nozzle housing of a solid rocket motor according to claim 1 or 2, characterized in that, The side wall of the combustion chamber housing simulation piece has a circumferential positioning groove, and the positioning groove is located behind the butting surface of the combustion chamber housing simulation piece. The outer side of the snap ring is clamped into the positioning groove, and the inner side of the snap ring abuts against the rear side surface of the front end of the nozzle housing.

8. The hydrostatic test tooling for the nozzle housing of a solid rocket motor according to claim 1 or 2, characterized in that, The ignition hole plug is in a stepped shape. The small-diameter section of the ignition hole plug has an ignition hole sealing groove, and the ignition hole gasket is arranged in the ignition hole sealing groove. The small-diameter section of the ignition hole plug is inserted and installed into the ignition hole.

9. The hydrostatic test tooling for the nozzle housing of a solid rocket motor according to claim 1 or 2, characterized in that The pressure measuring hole plug is in a stepped shape. The small-diameter section of the pressure measuring hole plug has a pressure measuring hole sealing groove, and the pressure measuring hole sealing ring is arranged in the pressure measuring hole sealing groove. The small-diameter section of the pressure measuring hole plug is inserted and installed into the pressure measuring hole.

10. The hydrostatic test tooling for the nozzle housing of a solid rocket motor according to claim 1 or 2, characterized in that, The nozzle tail plug is in a three-step shape. The large-diameter section of the nozzle tail plug has a nozzle tail sealing groove, and the nozzle tail sealing ring is arranged in the nozzle tail sealing groove. And the large-diameter section of the nozzle tail plug is inserted and installed into the nozzle outlet of the nozzle housing.

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