Solid rocket engine airtightness detection device and system

Abstract

The invention belongs to the technical field of solid rocket engine detection, and particularly provides a solid rocket engine airtightness detection tool and system.The solid rocket engine airtightness detection tool comprises a front baffle, the front baffle is arranged at a front end opening of an engine and used for sealing the front end opening of the engine and limiting movement of a pull rod, and a through hole for the pull rod to penetrate through is formed in a rear baffle; the rear baffle is arranged at a rear port of the engine, external threads are arranged at the tail end of the pull rod, internal threads are arranged on the inner wall of the locking sleeve, the locking sleeve is in threaded connection with the tail end of the pull rod and then compresses the rear baffle, and an adapter is arranged on the rear baffle. The detection tool and system are convenient to connect with the solid rocket engine, are convenient to install, and improve the airtightness detection efficiency.

Description

Technical Field

[0001] The present invention belongs to the technical field of solid rocket engine detection, and in particular, relates to a solid rocket engine airtightness detection device and system. Background Art

[0002] Because the solid rocket engine needs to embed the cable into the insulation layer for production, and the cable needs to pass through the front and rear cable ports, in order to ensure its airtightness, the engine needs to be tested for airtightness after the insulation is made. At present, there is no corresponding equipment for the airtightness test. The only method used is to connect the insulation tooling with the airtight adapter tooling and then install a pressure gauge on the adapter tooling to perform pressurized airtightness testing. This method has poor sealing performance, resulting in multiple sealing processes for each joint; the airtightness test can only be judged by the pressure indication value after the airtightness time is reached; there is no process record for the airtightness test, and personnel need to observe on site; the airtightness test tooling is heavy, inconvenient to install, and there is a risk of damaging the cable. Summary of the invention

[0003] The technical problem to be solved by the present invention is to provide a solid rocket engine airtightness detection tool and system, which is convenient for connection with the solid rocket engine, convenient for installation, and improves the airtightness detection efficiency.

[0004] In order to solve the above technical problems, the technical solution adopted by the present invention is: a solid rocket engine airtightness detection tooling, including a front baffle, which is arranged at the front port of the engine, the front baffle is used to close the front port of the engine and limit the movement of the pull rod, and the rear baffle is provided with a through hole for the pull rod to pass through, the rear baffle is arranged at the rear port of the engine, the tail end of the pull rod is provided with an external thread, the inner wall of the locking sleeve is provided with an internal thread, the locking sleeve is threadedly connected to the tail end of the pull rod to tighten the rear baffle, and the rear baffle is provided with an adapter.

[0005] In a preferred solution, the front baffle is a "T"-shaped structure, a first sealing groove is arranged at the position where the front baffle contacts the inner wall of the front port of the engine, and a first sealing ring is arranged in the first sealing groove.

[0006] In a preferred solution, the front baffle is connected to the engine via bolts.

[0007] In a preferred solution, the front baffle is provided with a through hole for the pull rod to pass through, and a pressure plate is provided at the front end of the pull rod, which is pressed on one side of the front baffle to limit the movement of the pull rod; or, the front baffle is connected to the pull rod to limit the movement of the pull rod.

[0008] In a preferred solution, a second sealing ring is provided between the front baffle and the pressure plate, and a second sealing groove cooperating with the second sealing ring is provided on the front baffle or the pressure plate.

[0009] In a preferred solution, a third sealing ring is provided between the locking sleeve and the rear baffle, and a third sealing groove cooperating with the third sealing ring is provided on the locking sleeve or the rear baffle.

[0010] In a preferred solution, one side of the rear baffle is provided with a protrusion and a groove that cooperate with the outer edge of the rear port of the engine.

[0011] In a preferred solution, the rear baffle is provided with a threaded hole that cooperates with the adapter.

[0012] The present invention also provides a solid rocket engine airtightness detection system, including the above-mentioned solid rocket engine airtightness detection tooling, and also including an airtightness detection device, the airtightness detection device includes an air source, the air source is connected to an air intake pipe, the air intake pipe is provided with an air intake solenoid valve and a pressure sensor, the air intake pipe is connected to a pressure measuring tube and an exhaust pipe, the exhaust pipe is provided with an exhaust solenoid valve, and the pressure measuring tube is connected to an adapter.

[0013] In a preferred embodiment, the gas source includes an air compressor and an air storage tank, and the air outlets of the air compressor and the air storage tank are connected to the air inlet pipeline.

[0014] The solid rocket engine airtightness detection tool and system provided by the present invention have the following beneficial effects: 1. The tooling is tightened by tightening the front and rear openings of the shell. The pull rod passes directly through the middle of the engine to tighten the two sealing baffles. A adapter is set on the rear baffle to connect with the airtight device. The entire tooling has good airtightness and is easy and quick to install.

[0015] 2. The airtightness detection time is shortened from the original 4h to 2h, the efficiency is increased by 1 times, and it is convenient for data recording and judgment of detection results. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present invention will be further described below in conjunction with the accompanying drawings and embodiments: Figure 1 It is a structural schematic diagram of the solid rocket engine airtightness detection tooling of the present invention; Figure 2 It is an enlarged view of point A in the figure; Figure 3 for Figure 1 The enlarged view of point B in the middle; Figure 4 for Figure 1 Enlarged view of point C in the middle Figure 5 It is a schematic structural diagram of the airtightness detection device of the present invention; Figure 6 It is a schematic diagram of the principle structure of the airtightness detection device of the present invention; In the figure: front baffle 1, first sealing groove 101, engine 2, pull rod 3, rear baffle 4, protrusion 401, groove 402, threaded hole 403, locking sleeve 5, adapter 6, pressure plate 7, first sealing ring 8, second sealing ring 9, second sealing groove 10, third sealing ring 11, third sealing groove 12, exhaust solenoid valve 13, air source 14, air compressor 1401, air storage tank 1402, intake pipe 15, intake solenoid valve 16, pressure sensor 17, pressure measuring tube 18, exhaust pipe 19. DETAILED DESCRIPTION

[0017] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0018] Embodiment 1: like Figures 1 to 4 As shown, a solid rocket engine air tightness detection tool includes a front baffle 1, which is arranged at the front port of the engine 2. In this embodiment, the front baffle 1 is connected to the engine 2 by bolts. The front baffle 1 is used to close the front port of the engine 2 and limit the movement of the pull rod 3.

[0019] In this embodiment, the front baffle 1 is provided with a through hole for the pull rod 3 to pass through, and a pressure plate 7 is provided at the front end of the pull rod 3. The pressure plate 7 is press-fitted on one side of the front baffle 1 to limit the movement of the pull rod 3; or the front baffle 1 is connected to the pull rod 3 to limit the movement of the pull rod 3. The movement of the pull rod 3 is limited by connecting the front baffle 1 to the pull rod 3 or by blocking the pressure plate 7 by the front baffle 1.

[0020] A through hole is provided on the rear baffle 4 for the tie rod 3 to pass through. The rear baffle 4 is arranged at the rear port of the engine 2. The tail end of the tie rod 3 is provided with an external thread, and the inner wall of the locking sleeve 5 is provided with an internal thread. After the locking sleeve 5 is threadedly connected to the tail end of the tie rod 3, the rear baffle 4 is tightened. The front end of the locking sleeve 5 is in an open state and the tail end is closed, which is conducive to closing the through hole on the rear baffle 4 for the tie rod 3 to pass through.

[0021] An adapter 6 is provided on the rear baffle 4. Specifically, a threaded hole 403 cooperating with the adapter 6 is provided on the rear baffle 4, so as to facilitate replacement of the adapter 6 and replacement of the adapter 6 for pipes of different sizes.

[0022] Preferably, the front baffle 1 is a "T"-shaped structure, and a first sealing groove 101 is provided at a position where the front baffle 1 contacts the inner wall of the front port of the engine 2, and a first sealing ring 8 is provided in the first sealing groove 101. By setting the front baffle 1 as a "T"-shaped structure, the front baffle 1 can be partially inserted into the front port of the engine 2, and by providing the first sealing ring 8, the sealing performance is improved.

[0023] A second sealing ring 9 is provided between the front baffle 1 and the pressure plate 7. A second sealing groove 10 cooperating with the second sealing ring 9 is provided on the front baffle 1 or the pressure plate 7. In this embodiment, the second sealing groove 10 is provided on one side of the front baffle 1 and is an annular groove.

[0024] A third sealing ring 11 is provided between the locking sleeve 5 and the rear baffle 4, and a third sealing groove 12 cooperating with the third sealing ring 11 is provided on the locking sleeve 5 or the rear baffle 4. In this embodiment, the third sealing groove 12 is provided on the side of the rear baffle 4 contacting the locking sleeve 5, so as to install the third sealing ring 11.

[0025] By providing the second sealing ring 9, the sealing degree between the front baffle 1 and the pressure plate 7 is improved; by providing the third sealing ring 11, the sealing degree between the locking sleeve 5 and the rear baffle 4 is improved.

[0026] The rear baffle plate 4 is provided with a protrusion 401 and a groove 402 on one side thereof, which are matched with the outer edge of the rear port of the engine 2. By providing the protrusion 401 and the groove 402 on the rear baffle plate 4, the contact area with the rear port of the engine 2 is increased. When in use, after installing a sealing rope in the sealing groove of the rear port of the engine 2, the rear baffle plate 4 is installed at the rear port position of the engine 2.

[0027] The tooling is tightened by tensioning the front and rear openings of the shell, that is, a front baffle 1 and a rear baffle 4 are respectively installed at the front and rear opening ends of the engine as sealing baffles, and a pull rod 3 directly passes through the middle of the engine to tighten the two sealing baffles, and an adapter is provided on the rear baffle 4 to connect with the airtight device.

[0028] The whole tooling has good air tightness and is easy and quick to install.

[0029] Embodiment 2: A solid rocket engine air tightness detection system, comprising the solid rocket engine air tightness detection tooling described in Example 1, and also comprising an air tightness detection device, such as Figure 5 and 6 As shown, the airtight detection device includes an air source 14, the air source 14 is connected to an air intake pipe 15, the air intake pipe 15 is provided with an air intake solenoid valve 16 and a pressure sensor 17, the air intake pipe 15 is connected to a pressure measuring tube 18 and an exhaust pipe 19, the exhaust pipe 19 is provided with an exhaust solenoid valve 20, the pressure measuring tube 18 is connected to the adapter 6, in this embodiment, the pressure measurement accuracy of the pressure sensor 17 can reach 0.001Mpa.

[0030] In this embodiment, the gas source 14 includes an air compressor 1401 and an air storage tank 1402 , and the air outlets of the air compressor 1401 and the air storage tank 1402 are connected to the air inlet pipe 15 .

[0031] During specific implementation, a controller may be provided to facilitate setting of the airtight detection pressure and display of the real-time airtight pressure.

[0032] In specific implementation, after installing the solid rocket engine airtightness detection tooling on the solid rocket engine to be tested, connect the pressure measuring tube 18 to the adapter 6. The pressure measuring tube 18 uses a pressure measuring hose. After setting the detection pressure and its upper and lower limits, the detection pressure holding time and the alarm pressure, the air intake solenoid valve 16 is opened to start the airtightness detection. After reaching the set detection pressure value, the air intake solenoid valve 16 is closed, and the airtightness pressure is displayed in real time. After the set pressure holding time is reached or the alarm pressure is reached, the detection ends. If the pressure does not drop to the alarm pressure value within the set pressure holding time, the test is qualified. If the alarm pressure is reached during the test, the system alarms, indicating that the airtightness test is unqualified. After the test is completed, open the exhaust solenoid valve 20 to exhaust the gas in the solid rocket engine to be tested, and remove the tooling to complete the operation.

[0033] The system's airtightness detection time is shortened from the original 4 hours to 2 hours, and the efficiency is increased by 1 times. The airtightness detection results can be automatically judged, which is convenient for data recording.

[0034] It will be easily understood by those skilled in the art that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A solid rocket engine air tightness detection tool, characterized in that: The invention comprises a front baffle (1), the front baffle (1) being arranged at the front port of the engine (2), the front baffle (1) being used to close the front port of the engine (2) and to limit the movement of the pull rod (3), the rear baffle (4) being provided with a through hole for the pull rod (3) to pass through, the rear baffle (4) being arranged at the rear port of the engine (2), the rear end of the pull rod (3) being provided with an external thread, the inner wall of the locking sleeve (5) being provided with an internal thread, the locking sleeve (5) being threadedly connected to the rear end of the pull rod (3) to press the rear baffle (4), and the rear baffle (4) being provided with an adapter (6).

2. The solid rocket engine airtightness detection tool according to claim 1, characterized in that: The front baffle (1) is a "T"-shaped structure, and a first sealing groove (101) is provided at a position where the front baffle (1) contacts the inner wall of the front port of the engine (2), and a first sealing ring (8) is provided in the first sealing groove (101).

3. The solid rocket engine airtightness detection tool according to claim 1, characterized in that: The front baffle (1) is connected to the engine (2) via bolts.

4. The solid rocket engine airtightness detection tool according to claim 1, characterized in that: The front baffle (1) is provided with a through hole for the pull rod (3) to pass through, and a pressure plate (7) is provided at the front end of the pull rod (3). The pressure plate (7) is pressed onto one side of the front baffle (1) to limit the movement of the pull rod (3); or, the front baffle (1) is connected to the pull rod (3) to limit the movement of the pull rod (3).

5. The solid rocket engine airtightness detection tool according to claim 4, characterized in that: A second sealing ring (9) is provided between the front baffle plate (1) and the pressure plate (7), and a second sealing groove (10) cooperating with the second sealing ring (9) is provided on the front baffle plate (1) or the pressure plate (7).

6. The solid rocket engine airtightness detection tool according to claim 1, characterized in that: A third sealing ring (11) is provided between the locking sleeve (5) and the rear baffle (4), and a third sealing groove (12) cooperating with the third sealing ring (11) is provided on the locking sleeve (5) or the rear baffle (4).

7. The solid rocket engine airtightness detection tool according to claim 1, characterized in that: A protrusion (401) and a groove (402) that cooperate with the outer edge of the rear port of the engine (2) are provided on one side of the rear baffle plate (4).

8. A solid rocket engine airtightness detection device according to claim 1, characterized in that: The rear baffle (4) is provided with a threaded hole (403) that matches the adapter (6).

9. A solid rocket engine air tightness detection system, characterized in that: The invention comprises the solid rocket engine airtightness detection tool as claimed in any one of claims 1 to 8, and also comprises an airtightness detection device, wherein the airtightness detection device comprises an air source (14), the air source (14) is connected to an air intake pipe (15), an air intake solenoid valve (16) and a pressure sensor (17) are provided on the air intake pipe (15), the air intake pipe (15) is connected to a pressure measuring tube (18) and an exhaust pipe (19), an exhaust solenoid valve (13) is provided on the exhaust pipe (19), and the pressure measuring tube (18) is connected to an adapter (6).

10. A solid rocket engine airtightness detection system according to claim 9, characterized in that: The gas source (14) comprises an air compressor (1401) and an air storage tank (1402), and the air outlets of the air compressor (1401) and the air storage tank (1402) are connected to the air inlet pipeline (15).

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