Solid rocket engine igniter performance test tool

Abstract

The utility model provides a solid rocket engine igniter performance test tool, and relates to the technical field of solid rocket engines, the tool comprises a combustion chamber simulation piece, a spray pipe simulation piece, a blanking cap and a sealing ring; the spray pipe simulation piece is connected with the combustion chamber simulation piece; the sealing ring is arranged at the joint of the spray pipe simulation piece and the combustion chamber simulation piece; the blanking cap is connected to a port of the spray pipe simulation piece; a first cavity is formed in the spray pipe simulation piece, a second cavity is formed in the combustion chamber simulation piece, and the first cavity is communicated with the second cavity; the combustion chamber simulation member is provided with an electric ignition tube interface used for installing an electric ignition tube and an igniter interface used for installing an igniter. Each interface of the tool is matched and consistent with the interface of the solid rocket engine, the tool can be used for the performance test of various types of solid rocket engine igniters, and the tool is simple and reliable in structure and can effectively examine the performance of the igniters.

Description

Technical Field

[0001] This application relates to the technical field of solid rocket engines, and particularly to a performance test tooling for a solid rocket engine igniter. Background Technique

[0002] Solid rocket engines have the advantages of simple structure, convenient maintenance, high reliability, and easy operation, and are widely used in missile power systems. The igniter is an important component of a solid rocket engine, and its function is to accurately and reliably ignite the grain, so that the engine enters normal operation according to the predetermined requirements. For the performance analysis of igniters, although there are currently some calculation formulas for estimating the ignition charge, the common feature of these formulas is that they focus on considering one or several factors, and the error of the calculation results is relatively large. Therefore, before delivery, all igniters of solid rocket engines need to pass performance tests for acceptance.

[0003] The patent with the publication number CN217739099U discloses a simple test device for a micro igniter, including a combustion chamber housing. Four first connection holes are uniformly arranged at one end of the combustion chamber housing. A lead hole is arranged inside the first connection hole, an air flow chamber is arranged inside the lead hole, and a charge chamber is arranged inside the air flow chamber. A cover housing is threadedly connected inside the combustion chamber housing, and an igniter body is arranged inside the cover housing. One end of the igniter body is provided with an igniter medicine ring, and a sealing ring is arranged on one side of the igniter medicine ring. However, it is only applicable to micro igniters and cannot be used for performance tests of igniters of various types of solid rocket engines.

[0004] In view of this, the technical problem that needs to be solved urgently at present is: how to propose a general performance test tooling for a solid rocket engine igniter, the interfaces of which are matched and consistent with the interfaces of the solid rocket engine, and can be used for performance tests of igniters of various types of solid rocket engines. The tooling has a simple and reliable structure and can effectively evaluate the performance of the igniter. Utility Model Content

[0005] The purpose of this application is to provide a performance test tooling for a solid rocket engine igniter, the interfaces of which are matched and consistent with the interfaces of the solid rocket engine, and can be used for performance tests of igniters of various types of solid rocket engines. The tooling has a simple and reliable structure and can effectively evaluate the performance of the igniter.

[0006] To achieve the above object, the present application provides a performance test tooling for a solid rocket engine igniter, including: a combustion chamber simulation part, a nozzle simulation part, a plug and a sealing ring; the nozzle simulation part is connected to the combustion chamber simulation part; the sealing ring is arranged at the connection between the nozzle simulation part and the combustion chamber simulation part; the plug is connected to the port of the nozzle simulation part; the nozzle simulation part has a first cavity inside, the combustion chamber simulation part has a second cavity inside, and the first cavity is communicated with the second cavity; the combustion chamber simulation part is provided with an electric igniter interface for installing an electric igniter and an igniter interface for installing an igniter.

[0007] For the performance test tooling of the solid rocket engine igniter as described above, wherein, the combustion chamber simulation part is provided with a pressure measurement interface for installing a pressure sensor, and the pressure measurement interface is communicated with the first cavity and the second cavity.

[0008] For the performance test tooling of the solid rocket engine igniter as described above, wherein, the plug is adhesively bonded to the inner profile of the expansion section of the nozzle simulation part by epoxy glue.

[0009] For the performance test tooling of the solid rocket engine igniter as described above, wherein, the end face where the nozzle simulation part is connected to the combustion chamber simulation part has a sealing groove, and the sealing ring is installed in the sealing groove.

[0010] For the performance test tooling of the solid rocket engine igniter as described above, wherein, the igniter interface and the electric igniter interface are matched with the interfaces used in the solid rocket engine.

[0011] For the performance test tooling of the solid rocket engine igniter as described above, wherein, both the combustion chamber simulation part and the nozzle simulation part are of a rotary body structure.

[0012] For the performance test tooling of the solid rocket engine igniter as described above, wherein, the combustion chamber simulation part and the nozzle simulation part are connected by threads.

[0013] For the performance test tooling of the solid rocket engine igniter as described above, wherein, a free cavity is formed among the combustion chamber simulation part, the nozzle simulation part and the plug.

[0014] For the performance test tooling of the solid rocket engine igniter as described above, wherein, after the igniter is installed at the igniter interface on the combustion chamber simulation part, the high-temperature gas generated by the igniter fills the free cavity, and when the pressure in the free cavity is higher than the opening pressure of the plug, the plug is flushed out by the high-temperature gas in the free cavity.

[0015] The performance test tooling for the solid rocket motor igniter as described above, wherein the pressure sensor installed at the pressure measurement interface measures the real-time pressure in the free cavity.

[0016] The beneficial effects achieved by this application are as follows:

[0017] (1) The performance test tooling for the solid rocket motor igniter of this application, the igniter interface and the electric igniter tube interface match the interfaces used in the solid rocket motor, and can be used for the performance tests of various types of solid rocket motor igniters. It has a simple, reliable structure and can truly simulate the performance test of the igniter, and can effectively evaluate the performance of the igniter. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0019] Figure 1 It is a schematic structural diagram of the performance test tooling for the solid rocket motor igniter according to the embodiment of this application.

[0020] Figure 2 For Figure 1 the schematic diagram of the A-A cross-section in

[0021] Figure 3 For Figure 1 the schematic diagram of the B-B cross-section in

[0022] Reference numerals: 1 - Combustion chamber simulation part; 2 - Nozzle simulation part; 3 - Plug; 4 - Sealing ring; 5 - Electric igniter tube interface; 6 - Igniter interface; 7 - Pressure measurement interface. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0023] The following combines the drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the described embodiments are part of the embodiments of this application, rather than all of them. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative efforts fall within the scope of protection of this application.

[0024] As Figures 1 - 3As shown in the figure, the present application provides a performance test tooling for a solid rocket motor igniter. The tooling includes: a combustion chamber simulation part 1, a nozzle simulation part 2, a plug 3, and a sealing ring 4; the nozzle simulation part 2 is connected to the combustion chamber simulation part 1; the sealing ring 4 is arranged at the connection between the nozzle simulation part 2 and the combustion chamber simulation part 1; the plug 3 is connected to the port of the nozzle simulation part 2; the nozzle simulation part 2 has a first cavity inside, the combustion chamber simulation part 1 has a second cavity inside, and the first cavity is communicated with the second cavity; the combustion chamber simulation part 1 is provided with an electric ignition tube interface 5 for installing an electric ignition tube and an igniter interface 6 for installing an igniter. The combustion chamber simulation part 1 is provided with a pressure measurement interface 7 for installing a pressure sensor, and the pressure measurement interface 7 is communicated with the first cavity and the second cavity.

[0025] As a specific embodiment of the present utility model, the combustion chamber simulation part 1 is of a rotary body structure. The head of the combustion chamber simulation part 1 (i.e., the end of the combustion chamber simulation part 1 away from the nozzle simulation part 2) is provided with an igniter interface 6, an electric ignition tube interface 5, and a pressure measurement interface 7. The pressure measurement interface 7 is located beside the electric ignition tube interface 5. Among them, the igniter interface 6 and the electric ignition tube interface 5 are matched with the interfaces used in the solid rocket motor, and the pressure measurement interface 7 is matched with the pressure sensor interface to ensure reliable connection and sealing.

[0026] As Figure 1 and Figure 2 shown in the figure, the electric ignition tube interface 5 includes two, and both of the two electric ignition tube interfaces 5 are communicated with the igniter interface 6, and the igniter interface 6 is communicated with the cavity inside the combustion chamber simulation part 1.

[0027] As a specific embodiment of the present utility model, the nozzle simulation part 2 is of a rotary body structure, and the profile of the surface where the plug 3 is bonded is matched with the nozzle profile of the solid rocket motor. The combustion chamber simulation part 1 and the nozzle simulation part 2 are connected by threads, and radial sealing is achieved through the sealing ring 4. The free cavity formed by the combustion chamber simulation part 1, the nozzle simulation part 2, the plug 3 and the igniter installed on the combustion chamber simulation part 1 is kept consistent with the initial free cavity of the solid rocket motor. The initial free cavity of the solid rocket motor refers to the space area that is not occupied and can accommodate fluids (such as gases, liquids, etc.) before the start of a specific working state of the motor.

[0028] As Figure 2 shown in the figure, the plug 3 is bonded to the inner profile of the expansion section of the nozzle simulation part 2 by epoxy glue, so that the plug 3 seals the inner profile of the expansion section of the nozzle simulation part 2. When the air pressure inside the combustion chamber simulation part 1 and the nozzle simulation part 2 is greater than the opening pressure of the plug 3, the plug 3 disengages from the inner profile of the expansion section of the nozzle simulation part 2.

[0029] As a preferred embodiment of the present utility model, the end face where the nozzle simulation part 2 is connected to the combustion chamber simulation part 1 has a sealing groove, and the sealing ring 4 is installed in the sealing groove.

[0030] As a preferred embodiment of the present utility model, the combustion chamber simulation part 1 and the nozzle simulation part 2 are threadedly connected. Specifically, one end of the combustion chamber simulation part 1 connected to the nozzle simulation part 2 has internal threads, and one end of the nozzle simulation part 2 connected to the combustion chamber simulation part 1 has external threads. The combustion chamber simulation part 1 is threadedly connected to the external threads of the nozzle simulation part 2 through its internal threads, thereby realizing the fixed connection between the combustion chamber simulation part 1 and the nozzle simulation part 2.

[0031] As a specific embodiment of the present utility model, an annular sealing groove distributed along the circumferential direction is provided on the outer end section of the nozzle simulation part 2. The sealing ring 4 is installed in the sealing groove, and a sealed connection is formed between the sealing ring 4 and the inner end face of the combustion chamber simulation part 1.

[0032] As a specific embodiment of the present utility model, the igniter interface 6 and the electric igniter tube interface 5 are matched with the interfaces used in the solid rocket engine, so that the test tooling for the performance of the fixed rocket engine igniter in this application is applicable to various solid rocket engines.

[0033] As a specific embodiment of the present utility model, a free cavity is formed between the combustion chamber simulation part 1, the nozzle simulation part 2 and the plug 3. After the igniter is installed on the igniter interface 6 on the combustion chamber simulation part 1, the high-temperature gas generated by the igniter fills the free cavity. When the pressure in the free cavity is higher than the opening pressure of the plug 3, the plug 3 is flushed out by the high-temperature gas in the free cavity. The pressure sensor installed at the pressure measurement interface 7 measures the real-time pressure in the free cavity.

[0034] As a specific embodiment of the present utility model, the general assembly state of a test tooling for the performance of a solid rocket engine igniter in this application is to install the igniter at the igniter interface 6 of the combustion chamber simulation part 1, use epoxy glue to bond the plug 3 on the inner profile of the expansion section of the nozzle simulation part 2, then install the sealing ring 4 in the sealing groove of the nozzle simulation part 2 and apply a small amount of lubricating grease, and then threadedly connect the combustion chamber simulation part 1 and the nozzle simulation part 2. Finally, install the electric igniter tube at the electric igniter tube interface 5 of the combustion chamber simulation part 1 and install the pressure sensor at the pressure measurement interface 7.

[0035] As a specific embodiment of the present utility model, during the igniter performance test, the high-temperature gas generated by the igniter fills the free cavity formed after the combustion chamber simulation part 1, the nozzle simulation part 2, the plug 3 and the igniter are installed on the combustion chamber simulation part 1. When the pressure in the free cavity is higher than the opening pressure of the plug 3, immediately the plug 3 is flushed out by the gas. The real-time pressure in the free cavity is measured by the pressure sensor installed at the pressure measurement interface 7 of the combustion chamber simulation part 1 and is used to analyze the performance of the igniter. Reliably and truly simulating the igniter performance test can effectively evaluate the performance of the igniter.

[0036] The beneficial effects achieved by this application are as follows:

[0037] (1) A performance test tooling for an igniter of a solid rocket motor according to the present application. The igniter interface and the electric igniter tube interface are matched with the interfaces used in the solid rocket motor, and it can be used for performance tests of igniters of various types of solid rocket motors. It has a simple and reliable structure and can truly simulate the performance test of the igniter, and can effectively evaluate the performance of the igniter.

[0038] In the description of the present application, the terms "first" and "second" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of the said features. In the description of the present application, "a plurality of" means two or more unless otherwise specifically defined.

[0039] In the description of the present application, the word "for example" is used to mean "serving as an example, illustration, or explanation". Any embodiment described as "for example" in the present application is not necessarily construed as being more preferred or having more advantages than other embodiments. In order for any person skilled in the art to implement and use the present utility model, the following description is given. In the following description, details are set forth for purposes of explanation. It should be understood that those of ordinary skill in the art can recognize that the present utility model can be implemented without using these specific details. In other instances, well-known structures and processes are not elaborated in detail to avoid obscuring the description of the present utility model with unnecessary details. Therefore, the present utility model is not intended to be limited to the embodiments shown, but is consistent with the broadest scope that conforms to the principles and features disclosed in the present application.

[0040] The above is only the embodiment mode of the present utility model and is not used to limit the present utility model. For those skilled in the art, various changes and modifications can be made to the present utility model. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the scope of the claims of the present utility model.

Claims

1. A solid rocket engine igniter performance test tool, characterized in that: The tooling includes: a combustion chamber simulation part, a nozzle simulation part, a plugging cover and a sealing ring; The nozzle simulation part is connected to the combustion chamber simulation part; The sealing ring is arranged at the connection between the nozzle simulation part and the combustion chamber simulation part; The plugging cover is connected to the port of the nozzle simulation part; The nozzle simulation part has a first cavity inside, the combustion chamber simulation part has a second cavity inside, and the first cavity is connected to the second cavity; The combustion chamber simulation component is provided with an electric ignition tube interface for installing the electric ignition tube and an igniter interface for installing the igniter.

2. The solid rocket engine igniter performance test fixture according to claim 1, characterized in that: The combustion chamber simulation component is provided with a pressure measuring interface for installing a pressure sensor, and the pressure measuring interface is communicated with the first cavity and the second cavity.

3. The solid rocket engine igniter performance test fixture according to claim 1, characterized in that: The plugging cover is bonded to the inner surface of the expansion section of the nozzle simulation part by epoxy adhesive.

4. The solid rocket engine igniter performance test fixture according to claim 1, characterized in that: The end surface where the nozzle simulation part is connected to the combustion chamber simulation part has a sealing groove, and the sealing ring is installed in the sealing groove.

5. The solid rocket engine igniter performance test fixture according to claim 1, characterized in that: The igniter interface and the electric ignition tube interface match the interfaces used by solid rocket engines.

6. The solid rocket engine igniter performance test fixture according to claim 1, characterized in that: The combustion chamber simulation part and the nozzle simulation part are both rotating body structures.

7. The solid rocket engine igniter performance test fixture according to claim 1, characterized in that: The combustion chamber simulation part and the nozzle simulation part are threadedly connected.

8. The solid rocket engine igniter performance test fixture according to claim 2, characterized in that: A free cavity is formed between the combustion chamber simulation part, the nozzle simulation part and the plugging cover.

9. The solid rocket engine igniter performance test fixture according to claim 8, characterized in that: After the igniter is installed on the igniter interface on the combustion chamber simulation, the high-temperature combustion gas generated by the igniter fills the free cavity. When the pressure in the free cavity is higher than the opening pressure of the plugging cover, the plugging cover is flushed out by the high-temperature combustion gas in the free cavity.

10. The solid rocket engine igniter performance test fixture according to claim 9, characterized in that: The pressure sensor installed in the pressure measuring interface measures the real-time pressure in the free cavity.

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