CN220890344U

CN220890344U - Solid rocket engine ignition test device

Info

Publication number: CN220890344U
Application number: CN202322937450.0U
Authority: CN
Inventors: 赵钊; 陈子豪; 韩文超; 张学学; 王路
Original assignee: Wuhan Guide Infrared Co Ltd
Current assignee: Wuhan Guide Infrared Co Ltd
Priority date: 2023-10-31
Filing date: 2023-10-31
Publication date: 2024-05-03
Anticipated expiration: 2033-10-31

Abstract

The utility model relates to the technical field of solid rocket engine tests, in particular to a solid rocket engine ignition test device, which comprises: barrel-shaped cavity, test end cover and piston mechanism. The testing end cover is arranged at the opening of the barrel-shaped cavity and is provided with a mounting hole for mounting the igniter; the piston mechanism comprises a piston and an adjusting component, the piston is slidably arranged in the barrel-shaped cavity and forms a testing cavity with the testing end cover, and the adjusting component is connected with the piston and is used for adjusting the position of the piston in the barrel-shaped cavity so as to adjust the volume of the testing cavity. The ignition test device can solve the problems of high cost, long development period and low efficiency caused by the fact that each engine in the prior art needs to be designed and processed.

Description

Solid rocket engine ignition test device

Technical Field

The utility model relates to the technical field of solid rocket engine tests, in particular to a solid rocket engine ignition test device.

Background

The solid rocket engine has wide application in the field of missile and mainly comprises an igniter, a charge, a combustion chamber, a spray pipe, a blocking cover and the like.

When designing a solid rocket engine igniter, theoretical calculation is needed to determine the ignition energy and the structural form of the igniter, and then the igniter is verified through an engine ignition test. However, it is often difficult to meet the use requirements once, and many theoretical calculations and engine ignition test verification are required.

In order to reduce the number of repeated calculation and test verification, reduce the development cost and shorten the development period, an ignition test device is designed, the technical state of the igniter is determined by carrying out a closed ignition test on the ignition test device, and meanwhile, the igniter can be checked through the ignition test device in the follow-up checking work of the igniter.

In the airtight ignition test of an igniter, the cavity volume of the ignition device is required to be the same as that of a real engine, so that different engines are required to design and produce different ignition test devices. This causes problems of long development period and high development cost. In addition, in order to ensure structural strength, the test device mostly adopts metal materials, but the metal materials conduct heat quickly, and the influence on the pressure testing precision in the test is larger.

After the airtight ignition test is finished, high-temperature and high-pressure gas still exists in the ignition test device, and the high-temperature and high-pressure gas possibly sprays to operators in the process of disassembling the tester, so that the high-temperature and high-pressure gas has higher potential safety hazard. The engines cannot be commonly used due to different volumes in cavities, and the traditional ignition test device is low in efficiency. Each engine needs to be designed and processed with a set of ignition test device, and has high cost, long development period and low efficiency.

Disclosure of utility model

Aiming at the defects in the prior art, the utility model aims to provide a solid rocket engine ignition test device which can solve the problems of high cost, long development period and low efficiency caused by the fact that each engine in the prior art needs to be designed and processed with one set of ignition test device.

In order to achieve the above purpose, the utility model adopts the following technical scheme:

the utility model provides a solid rocket engine ignition test device, which comprises:

a barrel-shaped cavity;

The testing end cover is covered at the opening of the barrel-shaped cavity and is provided with a mounting hole for mounting an igniter;

the piston mechanism comprises a piston and an adjusting component, the piston is slidably arranged in the barrel-shaped cavity and forms a testing cavity with the testing end cover, and the adjusting component is connected with the piston and is used for adjusting the position of the piston in the barrel-shaped cavity so as to adjust the volume of the testing cavity.

In some alternatives, the piston comprises:

The piston head is provided with a sealing groove on the outer side wall contacted with the inner wall of the barrel-shaped cavity, and a sealing ring is clamped in the sealing groove;

And the first heat insulation layer is arranged on one side of the piston head, which is close to the test end cover.

In some alternatives, the piston head has a receiving chamber therein, a bottom of the barrel chamber has a threaded bore, and the adjustment assembly includes:

the thrust bearing is clamped in the accommodating cavity and is coaxially arranged with the barrel-shaped cavity;

And one end of the driving rod is connected with the thrust bearing, and the other end of the driving rod penetrates through the bottom of the barrel-shaped cavity and is matched with the threaded hole.

In some alternative schemes, the accommodating cavity is a step cavity, a stress baffle is arranged in a small-diameter cavity of the step cavity, a through hole is formed in the middle of the stress baffle, two sides of the stress baffle are respectively provided with a thrust bearing, the end parts of the driving rods penetrate through the two thrust bearings, a sealing cover plate is arranged in a large-diameter cavity of the step cavity, the end parts of the small-diameter cavity are covered, and the first heat insulation layer is arranged on the outer side of the sealing cover plate.

The solid rocket engine ignition test apparatus according to claim, wherein the end portion of the driving rod connected with the thrust bearing is provided with a clamping block, and the clamping block is clamped with the driving rod and is positioned on the outer side of the thrust bearing between the sealing cover plate and the stress partition plate.

In some alternative solutions, the driving rod is further provided with a supporting protrusion, and the supporting protrusion is clamped on the outer side of the other thrust bearing.

In some alternatives, the drive rod is provided with a drive handle through an end of the barrel cavity.

In some alternatives, a second insulating layer is disposed within the barrel cavity.

In some alternative solutions, a pressure sensor is provided on the test end cover, and is used for detecting the pressure in the test cavity.

In some alternative solutions, the test end cover is further provided with a pressure release valve, which is used for releasing pressure in the test cavity.

Compared with the prior art, the utility model has the advantages that: according to the scheme, the igniter is arranged in the test cavity, the adjusting component adjusts the position of the piston in the barrel-shaped cavity, so that the volume of the test cavity is adjusted, and the test device can be suitable for igniters of various different models. Different simulation test devices are not required to be redesigned and processed aiming at rocket engine igniters with different free volumes, so that the efficiency is improved, and the cost is lower.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic diagram of a solid rocket engine ignition test device in an embodiment of the utility model;

FIG. 2 is a schematic view of a barrel cavity according to an embodiment of the present utility model;

FIG. 3 is a schematic diagram of a piston mechanism according to an embodiment of the present utility model;

Fig. 4 is a schematic structural diagram of a test end cap according to an embodiment of the present utility model.

In the figure: 1. a barrel-shaped cavity; 11. a second insulating layer; 12. a cylindrical housing; 13. an end cap; 2. testing the end cover; 21. a pressure relief valve; 22. a third insulating layer; 23. a sealing gasket; 3. a piston mechanism; 31. a piston; 311. a piston head; 312. a seal ring; 313. a first insulating layer; 314. a stress separator; 315. sealing the cover plate; 32. an adjustment assembly; 321. a thrust bearing; 322. a driving rod; 3221. a drive section; 3222. a connection section; 323. a clamping block; 324. the supporting bulge; 325. a drive handle; 4. a pressure sensor; 5. an igniter; 51. an electrical connector.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments of the present application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.

Embodiments of the present utility model are described in further detail below with reference to the accompanying drawings.

As shown in fig. 1, the present utility model provides a solid rocket engine ignition test device, comprising: a barrel-shaped cavity 1, a test end cover 2 and a piston mechanism 3.

The testing end cover 2 is covered at the opening of the barrel-shaped cavity 1, and the testing end cover 2 is provided with a mounting hole for mounting the igniter 5; the piston mechanism 3 comprises a piston 31 and an adjusting component 32, the piston 31 is slidably arranged in the barrel-shaped cavity 1 and forms a testing cavity with the testing end cover 2, and the adjusting component 32 is connected with the piston 31 and is used for adjusting the position of the piston 31 in the barrel-shaped cavity 1 so as to adjust the volume of the testing cavity.

When the solid rocket engine ignition test device is used, the electric connector 51 is installed in the installation hole through the installation hole arranged on the test end cover 2, the igniter 5 is connected with the electric connector 51, the test end cover 2 is covered at the opening of the barrel-shaped cavity 1 and sealed, the piston 31 is slidably arranged in the barrel-shaped cavity 1, and a test cavity is formed between the piston 31 and the test end cover 2. The igniter 5 is arranged in the testing cavity, and the position of the piston 31 in the barrel-shaped cavity 1 is adjusted through the adjusting component 32 so as to adjust the volume of the testing cavity, so that the testing device is applicable to igniters 5 of various types. Different simulation test devices are not required to be redesigned and processed aiming at rocket engine igniters with different free volumes, so that the efficiency is improved, and the cost is lower.

In this example, the sealing of the test end cap 2 at the opening of the barrel-shaped cavity 1 achieves the sealing effect by an axially sealing ring.

As shown in fig. 3, in some alternative embodiments, the piston 31 includes: the piston head 311 and the first heat insulation layer 313, wherein a sealing groove is arranged on the outer side wall of the piston head 311, which is contacted with the inner wall of the barrel-shaped cavity 1, and a sealing ring 312 is clamped in the sealing groove; a first insulating layer 313 is provided on the side of the piston head 311 adjacent the test end cap 2.

In this embodiment, by arranging the sealing groove on the outer side wall where the piston head 311 contacts with the inner wall of the barrel-shaped cavity 1 and clamping the sealing ring 312 in the sealing groove, in this embodiment, two annular sealing grooves are arranged on the piston head 311 and are arranged at intervals along the moving direction of the piston head 311, so that the tightness of the testing cavity can be ensured, and the accuracy of the test can be improved.

In addition, a first heat insulation layer 313 is arranged on one side of the piston head 311, which is close to the test end cover 2, so that heat dissipation of the test device is reduced, and pressure testing precision of the test device can be greatly improved.

In some alternative embodiments, the piston head 311 has a receiving cavity therein, the bottom of the barrel cavity 1 has a threaded hole, and the adjustment assembly 32 includes: thrust bearing 321 and drive rod 322.

The thrust bearing 321 is clamped in the accommodating cavity and is coaxially arranged with the barrel-shaped cavity 1; one end of the driving rod 322 is connected with the thrust bearing 321, and the other end passes through the bottom of the barrel-shaped cavity 1 and is matched with the threaded hole.

In this embodiment, a receiving cavity is provided in the piston head 311, a thrust bearing 321 is installed, one end of a driving rod 322 is connected with the thrust bearing 321, the other end passes through the bottom of the barrel-shaped cavity 1 and is matched with a threaded hole at the bottom of the barrel-shaped cavity 1, the driving rod 322 is rotated, and the driving rod 322 can move relative to the barrel-shaped cavity 1 to push the piston head 311 to move in the barrel-shaped cavity 1, so that the volume of the testing cavity is adjusted. The central axis of the threaded engagement of the drive rod 322 with the bottom of the barrel cavity 1 and the central axis of the engagement of the piston head 311 with the barrel cavity 1 are less subject to misalignment, and further the piston head 311 rotates with the drive rod 322 to provide greater resistance to travel. In this example, by arranging the accommodating cavity in the piston head 311 and installing the thrust bearing 321, the thrust bearing 321 is connected with the driving rod 322, and the driving rod 322 is rotated, and the advancing process only pushes the piston head 311 to advance, so that the resistance is reduced, and meanwhile, the installation precision requirement is greatly reduced.

In some alternative embodiments, the accommodating cavity is a step cavity, the small-diameter cavity of the step cavity is provided with a stress partition plate 314, the middle part of the stress partition plate 314 is provided with a through hole, two sides are provided with a thrust bearing 321, the end part of the driving rod 322 passes through the two thrust bearings 321, the large-diameter cavity of the step cavity is provided with a sealing cover plate 315, the end part of the small-diameter cavity is covered with the sealing cover plate, and the first heat insulation layer 313 is arranged outside the sealing cover plate 315.

In this embodiment, the stress separation plate 314 is disposed in the small diameter cavity of the step cavity, a through hole is disposed in the middle of the stress separation plate 314, and a thrust bearing 321 is disposed at two sides of the stress separation plate 314, and the end portion of the driving rod 322 passes through the two thrust bearings 321, so that the driving rod 322 can be rotated, the piston head 311 is pushed to advance only during the advancing process, the piston head 311 is not driven to rotate, and when the piston head 311 is pushed to advance or retreat, the thrust bearing 321 at two sides of the stress separation plate 314 transmits force to the stress separation plate 314, and the stress separation plate 314 transmits force to the whole piston head 311 again, so that the influence with other parts of the piston head 311 is avoided. The accommodating cavity is arranged in a step cavity, the sealing cover plate 315 is arranged in the large-diameter cavity of the step cavity in a matched mode, the end part of the small-diameter cavity is covered, the first heat insulation layer 313 is arranged on the outer side of the sealing cover plate 315, and the installation of the two thrust bearings 321 is facilitated.

In some alternative embodiments, the end of the driving rod 322 that is connected to the thrust bearing 321 is provided with a clamping block 323, and the clamping block 323 is clamped to the driving rod 322 and is located outside the thrust bearing 321 between the sealing cover plate 315 and the stress barrier 314.

In this embodiment, the clamping block 323 is disposed at the end of the driving rod 322 and is clamped with the driving rod 322, and is located outside the thrust bearing 321, when in installation, the thrust bearing 321 is installed between the sealing cover plate 315 and the stress partition 314, and then the driving rod 322 passes through the thrust bearing 321, so that the clamping block 323 is clamped at the end of the driving rod 322, and finally the sealing cover plate 315 and the first heat insulation layer 313 are installed.

In some alternative embodiments, the driving rod 322 is further provided with a supporting protrusion 324, and the supporting protrusion 324 is clamped on the outer side of the other thrust bearing 321.

In this embodiment, the driving rod 322 is further provided with a supporting protrusion 324 that is clamped on the outer side of the other thrust bearing 321, so as to prevent the thrust bearing 321 from falling off, and facilitate the driving rod 322 to transmit the axial force to the piston head 311 through the thrust bearing 321.

In addition, the driving rod 322 includes a driving section 3221 and a connecting section 3222, the driving section 3221 is provided with external threads, the driving section 3221 is matched with an internal threaded hole arranged at the bottom of the barrel-shaped cavity 1, the supporting protrusion 324 is arranged on the connecting section 3222, and the driving section 3221 is connected with the connecting section 3222.

As shown in fig. 2, the barrel cavity 1 includes a cylindrical housing 12 and an end cap 13, and the end cap 13 is provided at an end of the cylindrical housing 12 and is connected to the cylindrical housing 12 by bolts.

In some alternative embodiments, the drive rod 322 is provided with a drive handle 325 through the end of the barrel cavity 1.

In this example, the driving lever 322 passes through the end of the barrel-shaped cavity 1 and is provided with the driving handle 325, the driving handle 325 is mutually perpendicular with the driving lever 322, the driving lever 322 can be conveniently rotated, and the adjusting piston 31 is driven to move in the barrel-shaped cavity 1 so as to adjust the volume of the testing cavity and adapt to different test requirements.

In some alternative embodiments, a second insulating layer 11 is provided inside the barrel-shaped cavity 1.

In this example, the second heat insulation layer 11 is arranged in the barrel-shaped cavity 1, so that heat dissipation of the test device is reduced, and pressure testing precision of the test device can be improved greatly. A third insulating layer 22 is also provided on the inside of the test end cap 2. The first thermal insulation layer 313, the second thermal insulation layer 11 and the third thermal insulation layer 22 are made of high silica/phenolic materials, and other hard thermal insulation materials can be used.

Most materials (barrel-shaped cavity 1, test end cover 2, piston head 311, driving rod 322 and the like) of the ignition test device are made of ultra-high strength steel (30 CrMnSiA), so that the structure thickness is reduced, the quality is reduced, and the operation simplicity is improved. In order to avoid deformation of the piston rod under the action of repeated use and larger axial force, the driving rod 322 and the end cover of the barrel-shaped cavity 1 adopt wear-resistant T10 tool steel, and T-shaped threads with larger tooth thickness are matched between the driving rod 322 and the end cover of the barrel-shaped cavity 1.

In some alternative embodiments, a pressure sensor 4 is provided on the test end cap 2 for detecting the pressure in the test chamber.

After the test is finished, certain high-temperature and high-pressure gas still exists in the test cavity, the pressure sensor 4 can detect the pressure in the test cavity, certain danger caused by opening the test end cover 2 in a bubbling way is avoided, and the pressure sensor can also be used as test data.

In some alternative embodiments, as shown in fig. 4, a pressure relief valve 21 is further provided on the test end cap 2 for venting the test chamber.

In this embodiment, the position of installing the pressure relief valve 21 on the test end cover 2 is provided with a stepped hole, the small hole of the stepped hole is close to one side of the test cavity, the large hole of the stepped hole is used for installing the pressure relief valve 21, and the pressure relief valve 21 is arranged in the large hole of the stepped hole in a threaded connection mode. The end of the pressure relief valve 21 is also provided with a sealing gasket 23 in the large hole of the stepped hole, and in order to ensure sealing effectiveness, the sealing gasket 23 is made of red copper material with higher compressibility, and sealing element materials such as stainless steel can also be used.

After the test is finished, certain high-temperature and high-pressure gas still exists in the test cavity, the pressure sensor 4 can detect the pressure in the test cavity, if the pressure sensor 4 is detached firstly, the gas can leak from the detaching position, the leakage direction and the time are uncertain, and meanwhile, the pressure sensor 4 is easily outwards flown out under the action of the pressure, so that the potential safety hazard is high. Through spanner rotation, loosen relief valve 21 (relief valve 21 passes through the raw material area with the big hole threaded connection of the shoulder hole on the test end cover 2 and seals), sealing washer 23 compression disappears, and gaseous coming out from the test chamber is discharged through the side direction relief hole, finally reaches directional, safe exhaust's purpose.

In addition, two other stepped holes are also provided in the test end cap 2, in the same way as the electrical connectors 51 for mounting the pressure sensor 4 and the igniter 5.

In summary, the igniter 5 is disposed in the testing cavity, and the adjusting component 32 adjusts the position of the piston 31 in the barrel-shaped cavity 1 to adjust the volume of the testing cavity, so that the testing device is suitable for igniters 5 of various types. Different simulation test devices are not required to be redesigned and processed aiming at rocket engine igniters with different free volumes, so that the efficiency is improved, and the cost is lower. In addition, the heat insulation material is arranged in the test device, so that the heat dissipation of the test device is reduced, and the pressure testing precision of the test device can be greatly improved. The test safety is improved. Meanwhile, the purpose of quick, directional and safe pressure relief after the simulation test is finished is achieved through a simple pressure relief device. Improved safety of simulation tests.

In the description of the present application, it should be noted that the azimuth or positional relationship indicated by the terms "upper", "lower", etc. are based on the azimuth or positional relationship shown in the drawings, and are merely for convenience of describing the present application and simplifying the description, and are not indicative or implying that the apparatus or element in question must have a specific azimuth, be constructed and operated in a specific azimuth, and thus should not be construed as limiting the present application. Unless specifically stated or limited otherwise, the terms "mounted," "connected," and "coupled" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.

It should be noted that in the present application, relational terms such as "first" and "second" and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element. The foregoing is only a specific embodiment of the application to enable those skilled in the art to understand or practice the application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A solid rocket engine ignition test device, comprising:

A barrel-shaped cavity (1);

the testing end cover (2) is covered at the opening of the barrel-shaped cavity (1), and the testing end cover (2) is provided with a mounting hole for mounting the igniter (5);

The piston mechanism (3) comprises a piston (31) and an adjusting component (32), wherein the piston (31) is slidably arranged in the barrel-shaped cavity (1) and a test cavity is formed between the piston and the test end cover (2), and the adjusting component (32) is connected with the piston (31) and used for adjusting the position of the piston (31) in the barrel-shaped cavity (1) so as to adjust the volume of the test cavity.

2. A solid rocket engine ignition test device according to claim 1, wherein said piston (31) comprises:

The piston head (311) is provided with a sealing groove on the outer side wall contacted with the inner wall of the barrel-shaped cavity (1), and a sealing ring (312) is clamped in the sealing groove;

And the first heat insulation layer (313) is arranged on one side of the piston head (311) close to the test end cover (2).

3. A solid rocket engine ignition test device according to claim 2, wherein the piston head (311) is provided with a receiving chamber, the bottom of the barrel-shaped chamber (1) is provided with a threaded hole, and the adjusting assembly (32) comprises:

A thrust bearing (321) which is clamped in the accommodating cavity and is coaxially arranged with the barrel-shaped cavity (1);

and one end of the driving rod (322) is connected with the thrust bearing (321), and the other end of the driving rod penetrates through the bottom of the barrel-shaped cavity (1) and is matched with the threaded hole.

4. A solid rocket engine ignition test device according to claim 3, wherein the accommodating cavity is a step cavity, a stress baffle (314) is arranged in a small-diameter cavity of the step cavity, a through hole is arranged in the middle of the stress baffle (314), thrust bearings (321) are arranged on two sides of the stress baffle, the end part of the driving rod (322) penetrates through the two thrust bearings (321), a sealing cover plate (315) is arranged in a large-diameter cavity of the step cavity, the end part of the small-diameter cavity is covered, and the first heat insulation layer (313) is arranged on the outer side of the sealing cover plate (315).

5. The solid rocket engine ignition test device according to claim 4, wherein a clamping block (323) is arranged at the end part of the driving rod (322) connected with the thrust bearing (321), and the clamping block (323) is clamped with the driving rod (322) and is positioned outside the thrust bearing (321) between the sealing cover plate (315) and the stress partition plate (314).

6. A solid rocket engine ignition test device according to claim 5, wherein said driving rod (322) is further provided with a holding protrusion (324), said holding protrusion (324) being engaged with the outer side of the other thrust bearing (321).

7. A solid rocket engine ignition test device according to claim 3, wherein the drive rod (322) is provided with a drive handle (325) through the end of the barrel-shaped cavity (1).

8. A solid rocket engine ignition test device according to claim 3, wherein a second insulating layer (11) is provided in the barrel-shaped cavity (1).

9. A solid rocket engine ignition test device according to claim 1, wherein a pressure sensor (4) is arranged on the test end cover (2) and is used for detecting the pressure in the test cavity.

10. A solid rocket engine ignition test device according to claim 1, wherein the test end cap (2) is further provided with a pressure relief valve (21) for relieving pressure in the test cavity.