Gland nut structure for solid rocket engine

Abstract

The invention provides a gland nut structure for a solid rocket engine. The gland nut structure comprises a gland nut body, a matching thread, a pressing matching surface and a mounting notch, the matching threads are formed in the gland nut body and used for being in threaded connection with a combustion chamber shell. The pressing matching surface is arranged on the inner side of the gland thread body and is used for pressing and connecting the top seat to the end part of the combustion chamber shell; the installation notch is formed in the gland thread body, and whether the top seat and the combustion chamber shell are pressed in place or not is detected at the installation notch through a detection tool. The overall reliability of the solid rocket engine is improved, and the overall undetectable and undetectable items of the solid rocket engine are reduced.

Description

Technical Field

[0001] The present application relates to the technical field of solid rocket engines, and in particular to a gland nut structure for solid rocket engines. Background Art

[0002] The solid rocket engine is composed of a charge combustion chamber, a front head, a nozzle, and an ignition device. For a solid rocket engine with a small front opening and a fixed head ignition position and an engine angular position, the head front head usually adopts a top seat + gland nut structure. Common top seat and gland nut structures are as follows: Figure 1 shown.

[0003] like Figure 1 As shown, the top seat 2 is first installed into the front machine mouth of the charge combustion chamber 1 of the small-opening solid rocket engine. By rotating the top seat angle, the top seat 2 structure and the solid rocket engine body structure form a certain angle. After that, the gland nut 3 is connected to the combustion chamber shell through a thread, thereby pressing the top seat 2 to ensure the sealing of the solid rocket engine. Figure 1 The 4 platforms shown are the steps for tightening the gland nut with the wrench.

[0004] Figure 1 The main shortcomings of the scheme shown are as follows:

[0005] The gland nut 3 is connected to the combustion chamber shell through threads, and the top seat 2 is completely pressed onto the charge combustion chamber 1. Since the gland nut 3 is tightly fitted to the top seat 2 and the combustion chamber shell, it is impossible to check whether the gland nut is tightened in place, which reduces the overall reliability of the solid rocket engine and increases the number of undetectable and unmeasurable items.

[0006] Therefore, the technical problem that urgently needs to be solved is: how to provide a gland nut structure for a solid rocket engine to improve the overall reliability of the solid rocket engine and reduce the overall undetectable and unmeasurable items of the solid rocket engine. Summary of the invention

[0007] The purpose of the present application is to provide a gland nut structure for a solid rocket engine, so as to improve the overall reliability of the solid rocket engine and reduce the overall undetectable and unmeasurable items of the solid rocket engine.

[0008] In order to achieve the above-mentioned purpose, the present application provides a gland nut structure for a solid rocket engine, which structure includes: a gland nut body, a mating thread, a tightening fit surface and an installation notch; the mating thread is opened on the gland nut body, and the mating thread is used to be threadedly connected to the combustion chamber shell; the tightening fit surface is arranged on the inner side of the gland thread body, and the tightening fit surface is used to tighten the top seat to the end of the combustion chamber shell; the installation notch is opened on the gland thread body, and a detection tool is used to detect whether the top seat and the combustion chamber shell are pressed into place at the installation notch.

[0009] The gland nut structure for a solid rocket engine as described above, wherein the gland nut body includes a circular ring portion and an end cover; the circular ring portion is connected to the end cover; the circular ring portion is sleeved on the end of the combustion chamber shell; and the end cover is limited on the outer end surface of the combustion chamber shell.

[0010] The gland nut structure for a solid rocket engine as described above, wherein the annular portion has a cavity inside, the mating thread is arranged in the cavity and is located on the inner wall of the annular portion; the end of the combustion chamber shell extends into the cavity; the mating thread is threadedly connected to the outer wall of the combustion chamber shell.

[0011] The gland nut structure for a solid rocket engine as described above, wherein the compression fit surface is located on a side of the end cover close to the combustion chamber casing.

[0012] The gland nut structure for a solid rocket engine as described above, wherein the end cover is provided with a through opening along its axial direction.

[0013] The gland nut structure for a solid rocket engine as described above, wherein the diameter of the through opening is smaller than the diameter of the clamping end face of the top seat.

[0014] In the gland nut structure for a solid rocket engine as described above, the annular portion is provided with a set screw mounting hole along a direction perpendicular to its axis; a set screw is installed in the set screw mounting hole.

[0015] The gland nut structure for a solid rocket engine as described above, wherein the installation notch is provided at the connection between the annular portion and the end cover; the installation notch passes through from the end of the end cover to the cavity along the axial direction of the end cover.

[0016] The gland nut structure for a solid rocket engine as described above, wherein the mounting notches include a plurality of notches; the plurality of mounting notches are spaced apart along the circumferential direction of the end cover.

[0017] The gland nut structure for a solid rocket engine as described above, wherein the gland nut body is in a circular ring shape.

[0018] The beneficial effects achieved by this application are as follows:

[0019] (1) In the present application, four notches are opened at the compression top seat position on the front end face of the solid rocket engine gland nut for the installation tooling interface of the gland nut. Through the notch, a vernier caliper is used to check the distance from the right end face of the gland nut to the right end face of the combustion chamber shell to detect whether the gland nut is installed and compressed in place, which effectively reduces the undetectable and unmeasurable items of whether the solid rocket engine gland nut is installed in place and improves the overall reliability of the solid engine.

[0020] (2) The gland nut structure for solid rocket engines proposed in this application can improve the reliability of the overall structure of the solid rocket engine after final assembly, and reduce the risk of failure of the overall sealing structure of the solid rocket engine due to the gland nut not being tightened after the final assembly of the solid rocket engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present application. For those skilled in the art, other drawings can also be obtained based on these drawings.

[0022] Figure 1 It is a structural schematic diagram of a gland nut in the prior art.

[0023] Figure 2 This is a schematic diagram of the gland nut structure for the solid rocket engine according to an embodiment of the present application.

[0024] Figure 3 This is a front view of the gland nut structure for the solid rocket engine according to an embodiment of the present application.

[0025] Figure 4 This is a schematic diagram of the installation of the gland nut structure for the solid rocket engine according to an embodiment of the present application.

[0026] Figure numerals: 1-charge combustion chamber; 2-top seat; 3-cover nut; 4-combustion chamber shell; 30-cover nut body; 31-fastening screw mounting hole; 32-matching thread; 33-tightening fitting surface; 34-mounting notch; 35-fastening screw. DETAILED DESCRIPTION

[0027] The following is a clear and complete description of the technical solutions in the embodiments of the present application in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0028] like Figure 2-4 As shown, the present application provides a gland nut structure for a solid rocket engine, which structure includes: a gland nut body 30, a mating thread 32, a tightening fit surface 33 and an installation notch 34; the mating thread 32 is opened on the gland nut body 30, and the mating thread 32 is used for threaded connection with the combustion chamber shell 4; the tightening fit surface 33 is arranged on the inner side of the gland thread body, and the tightening fit surface 33 is used to tighten the top seat to the end of the combustion chamber shell 4; the installation notch 34 is opened on the gland thread body, and a detection tool is used at the installation notch 34 to detect whether the top seat and the combustion chamber shell 4 are tightened in place.

[0029] The gland nut structure of the present application is connected to the combustion chamber shell 4 through a matching thread 32, and the top seat 2 installed at the front end of the combustion chamber shell 4 is tightly pressed into the top seat mounting groove at the front end of the combustion chamber shell 4. Four mounting notches 34 are opened at the right end surface of the gland nut and the pressing position of the top seat 2. The mounting notches 34 serve as matching windows for the gland nut tightening tooling, and are also used to check whether the gland nut is tightened to press the top seat 2 into place (that is, whether the top seat 2 is tightly pressed into the top seat mounting groove at the front end of the combustion chamber shell 4), which greatly improves the structural reliability of the solid rocket engine during the assembly process.

[0030] As a specific embodiment of the present invention, the gland nut body 30 includes a circular ring portion and an end cover; the circular ring portion is connected to the end cover; preferably, the circular ring portion and the end cover are integrally formed. The circular ring portion is sleeved on the end of the combustion chamber housing 4, and the circular ring portion is threadedly connected to the combustion chamber housing 4; the end cover is limited to the outer end surface of the combustion chamber housing 4, and the end cover limits the top seat 2 in the top seat mounting groove in the combustion chamber housing 4.

[0031] As a specific embodiment of the present invention, the annular portion is annular, and has a cavity inside the annular portion, which is used to be sleeved on the end of the combustion chamber housing 4, so that the inner wall of the annular portion is threadedly connected with the outer wall of the combustion chamber housing 4. The matching thread 32 is arranged in the cavity and is located on the inner wall of the annular portion; the end of the combustion chamber housing 4 extends into the cavity; the matching thread 32 is threadedly connected with the outer wall of the combustion chamber housing 4. A stable connection between the gland nut structure and the combustion chamber housing 4 is achieved.

[0032] As a specific embodiment of the present invention, the compression fitting surface 33 is located on the side of the end cover close to the combustion chamber housing 4. Therefore, after the gland nut structure is installed at the end of the combustion chamber housing 4, the compression fitting surface 33 plays a compression role on the top seat 2, so as to press the top seat 2 into the top seat installation groove of the combustion chamber housing 4.

[0033] As a specific embodiment of the present invention, the end cover is provided with a through opening along its axial direction, and the through opening is used to pass through the front end of the top seat 2, that is, the end where the igniter is installed. Preferably, the shape of the through opening is circular.

[0034] As a specific embodiment of the present invention, the diameter of the through opening is smaller than the diameter of the pressing end surface of the top seat, so that the end cover can press and connect the top seat 2 in the top seat mounting groove of the combustion chamber shell 4.

[0035] like Figure 2 and 4 As shown, the annular portion is provided with a set screw installation hole 31 in a direction perpendicular to its axis; a set screw 35 is installed in the set screw installation hole 31. The set screw 35 is used to press against the outer wall of the combustion chamber housing 4, further improving the reliability of the connection between the gland nut structure and the combustion chamber housing 4.

[0036] As a specific embodiment of the present invention, the mounting notch 34 is provided at the connection between the annular portion and the end cap; the mounting notch 34 is along the axial direction of the end cap, and passes through from the end of the end cap to the cavity. The mounting notch 34 includes a plurality of mounting notches 34; the plurality of mounting notches 34 are arranged spaced apart along the circumferential direction of the end cap. Preferably, the mounting notches 34 include 4, and the number of the mounting notches 34 is not limited. The 4 mounting notches 34 of the present application are only a preferred embodiment.

[0037] Specifically, the present application opens four notches at the compression top seat position on the front end face of the solid rocket engine gland nut, which are used for the installation tooling interface of the gland nut. A vernier caliper is used through the notch to check the distance from the right end face of the gland nut to the right end face of the combustion chamber casing 4 to detect whether the gland nut is installed and tightened in place, which effectively reduces the undetectable and unmeasurable items of whether the solid rocket engine gland nut is installed in place and improves the overall reliability of the solid engine.

[0038] As a preferred embodiment of the present invention, the gland nut body 30 is in a circular ring shape.

[0039] It should be explained that the present application is applicable to small and medium-sized solid rocket engines with a small front opening. The present application is effective for solid rocket engines that are ignited at the head and whose head structure needs to be at a certain angular position with the engine body. The installation notch opened on the right end face of the gland nut of the present application needs to be used in conjunction with the gland nut installation tool, and the size of the installation notch can enable the vernier caliper to effectively measure the distance from the right end face of the gland nut to the right end face of the combustion chamber shell 4 (i.e. Figure 4In the present application, thread locking glue is applied to the gland nut thread or a set screw installation hole 31 is drilled at an appropriate position on the gland nut thread circumference, and a set screw 35 is installed in the set screw installation hole 31 to prevent the gland nut from loosening after installation.

[0040] The beneficial effects achieved by this application are as follows:

[0041] (1) In the present application, four notches are opened at the compression top seat position on the front end face of the solid rocket engine gland nut for the installation tooling interface of the gland nut. Through the notch, a vernier caliper is used to check the distance from the right end face of the gland nut to the right end face of the combustion chamber shell to detect whether the gland nut is installed and compressed in place, which effectively reduces the undetectable and unmeasurable items of whether the solid rocket engine gland nut is installed in place and improves the overall reliability of the solid engine.

[0042] (2) The gland nut structure for solid rocket engines proposed in this application can improve the reliability of the overall structure of the solid rocket engine after final assembly, and reduce the risk of failure of the overall sealing structure of the solid rocket engine due to the gland nut not being tightened after the final assembly of the solid rocket engine.

[0043] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, "plurality" means two or more, unless otherwise clearly and specifically defined.

[0044] In the description of the present application, the word "for example" is used to mean "used as an example, illustration or explanation". Any embodiment described as "for example" in the present application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is given to enable any technician in the field to implement and use the present invention. In the following description, details are listed for the purpose of explanation. It should be understood that a person of ordinary skill in the art can recognize that the present invention can be implemented without using these specific details. In other examples, well-known structures and processes will not be elaborated in detail to avoid obscuring the description of the present invention with unnecessary details. Therefore, the present invention is not intended to be limited to the embodiments shown, but is consistent with the widest scope consistent with the principles and features disclosed in the present application.

[0045] The above description is only an embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent substitution, improvement, etc. made within the spirit and principle of the present invention should be included in the scope of the claims of the present invention.

Claims

1. A gland nut structure for a solid rocket engine, characterized in that: The structure comprises: a gland nut body, a matching thread, a pressing matching surface and an installation notch; The matching thread is provided on the gland nut body, and the matching thread is used for threaded connection with the combustion chamber housing; The compression fitting surface is arranged inside the threaded body of the gland, and the compression fitting surface is used to compress and connect the top seat to the end of the combustion chamber housing; The installation notch is formed on the gland threaded body, and a detection tool is used at the installation notch to detect whether the top seat and the combustion chamber shell are pressed into place.

2. The gland nut structure for a solid rocket engine according to claim 1, characterized in that: The gland nut body comprises a circular ring portion and an end cover; The annular portion is connected to the end cover; The annular portion is sleeved on the end of the combustion chamber housing; The end cover is limited at the outer end surface of the combustion chamber shell.

3. The gland nut structure for a solid rocket engine according to claim 2, characterized in that: The annular portion has a cavity inside, and the matching thread is arranged in the cavity and located on the inner wall of the annular portion; The end of the combustion chamber housing extends into the cavity; The matching thread is threadedly connected to the outer wall of the combustion chamber housing.

4. The gland nut structure for a solid rocket engine according to claim 2, characterized in that: The press fit surface is located on a side of the end cover close to the combustion chamber casing.

5. The gland nut structure for a solid rocket engine according to claim 2, characterized in that: The end cover is provided with a through opening along the axial direction thereof.

6. The gland nut structure for a solid rocket engine according to claim 5, characterized in that: The diameter of the through opening is smaller than the diameter of the pressing end surface of the top seat.

7. The gland nut structure for a solid rocket engine according to claim 2, characterized in that: The annular portion is provided with a set screw installation hole along a direction perpendicular to its axis; A set screw is installed in the set screw installation hole.

8. The gland nut structure for a solid rocket engine according to claim 3, characterized in that: The installation notch is provided at the connection between the annular portion and the end cover; The installation notch is along the axial direction of the end cover and penetrates from the end of the end cover to the cavity.

9. The gland nut structure for a solid rocket engine according to claim 8, characterized in that: The installation notch includes a plurality of; A plurality of mounting notches are arranged at intervals along the circumferential direction of the end cover.

10. The gland nut structure for a solid rocket engine according to claim 1, characterized in that: The gland nut body is in a circular ring shape.

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