Vacuum test device for detecting leakproofness of launch canister of patrolling bomb

Abstract

The utility model relates to a vacuum test device for leakproofness detection of a patrol bomb launch canister. The leakproofness of the launch canister is judged by putting the launch canister into a vacuum test cavity, vacuumizing and observing the pressure drop of a vacuum gauge. The device is formed by sequentially connecting an exhaust valve, a vacuum test cavity (including a vacuum meter), a control valve, a pneumatic pipeline, a pneumatic flow regulating valve, a switching valve, a vacuum buffer tank (including a stop valve) and a vacuum pump according to the air exhaust direction. During vacuumizing, the vacuum pump is started to vacuumize the vacuum buffer tank, after a certain vacuum degree is achieved, the buffer tank serves as a vacuum generator to vacuumize the vacuum test cavity, the air exhaust rate is adjusted and set through the pneumatic flow adjusting valve, and opening and closing control over an air channel is achieved through the control valve. The vacuum buffer tank serves as a vacuum generator, frequent starting and stopping of a vacuum pump are avoided, and the service life of equipment is prolonged; the test requirements of multiple products can be met through one-time evacuation, and the test efficiency is improved; the air exhaust rate is stable and adjustable, and the consistency of product test states is ensured.

Description

Technical Field

[0001] The utility model relates to the technical field of launch tubes, in particular to a vacuum testing device for detecting the sealing performance of a launch tube of a loitering missile. Background Art

[0002] An individual soldier's cruise missile (ISRM) is a short-range weapon carried by a single soldier for beyond-visual-range patrol reconnaissance and attacking key enemy equipment or personnel. The launch tube is responsible for launching the ISSRM and also serves as a crucial protective barrier during its storage and transportation. The launch tube's sealing directly impacts the missile's protective effectiveness.

[0003] Existing vacuum test equipment for inspecting the leaktightness of cruise missile launch tubes consists of a vacuum pump, piping, a manual shutoff valve, a vacuum test chamber (equipped with a vacuum gauge), and a vacuum test chamber exhaust valve. To assess the leaktightness of a launch tube, the tube is placed in the vacuum test chamber, the exhaust valve is closed, the vacuum pump is started, and the vacuum test chamber's evacuation rate is controlled by adjusting the opening of the manual shutoff valve. When the vacuum indication reaches the required value, the manual shutoff valve is closed, followed by the vacuum pump, to maintain pressure. The tube's leaktightness is determined by observing whether the pressure drop on the vacuum gauge exceeds the maximum allowable value during the hold time.

[0004] The shortcomings of the existing technical solutions are as follows: First, the pumping rate is adjusted by manually controlling the valve opening, and the pumping rate is unstable. If the opening is too large, instantaneous closure will intensify gas vibrations, and the vacuum indication value will drop rapidly, creating the illusion of leakage in the launch tube; if the valve opening is too small, the pumping time will be longer. If the launch tube leaks, the pressure inside the tube and the vacuum test chamber may have reached equilibrium, and the sealing of the launch tube cannot be accurately judged by the vacuum indication value. Second, the manual control of the valve opening to control the pumping rate is different each time, resulting in inconsistent test conditions for the launch tube sealing test. Third, the vacuum pump needs to be started and stopped once for each test. Frequent starts and stops reduce the service life of the vacuum pump and increase maintenance costs. Summary of the Invention

[0005] In view of the shortcomings of the existing technology, the utility model provides a vacuum test device for detecting the sealing of a cruise missile launch tube, which overcomes the shortcomings of the existing technology and has the advantages of high test efficiency, stable and adjustable air extraction rate, good consistency of test state and long equipment service life.

[0006] In order to solve the above technical problems, one of the purposes of the present utility model is to provide a vacuum test device for detecting the sealing performance of a cruise missile launch tube. The device is composed of an exhaust valve 10, a test chamber 9, a control valve 8, a pneumatic flow regulating valve 7, a stop valve 11, a vacuum buffer tank 5, a stop valve 4, and a vacuum pump 1 connected in sequence according to the direction of exhaust.

[0007] The exhaust valve 10 is connected to the test chamber 9 through a connecting pipe, and the other end of the test chamber 9 is connected to the control valve 8 through a connecting pipe;

[0008] The other end of the control valve 8 is connected to the pneumatic flow regulating valve 7 through the pneumatic hose 3;

[0009] The other end of the pneumatic flow regulating valve 7 is connected to the stop valve 11 through the pneumatic hose 3;

[0010] The vacuum buffer tank 5 is connected to the stop valve 4 and the stop valve 11;

[0011] The stop valve 4 is connected to the vacuum pump 1 through a pneumatic hose 3;

[0012] The vacuum buffer tank 5 and the test chamber 9 are both provided with a vacuum gauge 6 , and the interfaces of the vacuum pump 1 , the stop valve 4 , the stop valve 11 , the pneumatic flow regulating valve 7 and the control valve 8 are all provided with a pneumatic quick connector 2 .

[0013] Furthermore, the vacuum buffer tank 5 is composed of a tank body 5.1, a lock 5.2, a sealing rubber gasket 5.3 and a tank cover 5.4. The annular sealing rubber gasket 5.3 is placed flat on the tank body 5.1, 3 to 4 locks are welded to the upper side of the outer wall of the tank body 5.1, and the tank cover 5.4 is locked to the tank body 5.1 by the lock 5.2; the connecting pipe 9.1 connecting the stop valve 4 and the stop valve 11, and the vacuum gauge seat 9.10 are respectively welded to the three light holes on the tank cover 5.4.

[0014] Furthermore, the internal thread on one side of the stop valve is fastened to the external thread of the pneumatic quick connector 2, and the internal thread on the other side is fastened to the external thread of the connecting pipe 9.1.

[0015] Furthermore, a copper pad 5.5 is provided at the bottom of the vacuum gauge 6 and is connected to the vacuum gauge seat 9.10 through a thread.

[0016] Furthermore, the test chamber 9 is composed of a connecting pipe 9.1, a front flange cover 9.2, a front flange 9.6, a rear flange 9.11, a rear flange cover 9.12, bolts 9.3, a sealing ring 9.4, a conductive rubber plate 9.5, a nut 9.7, a cylinder 9.8, a conductive rubber plate lining 9.9 and a vacuum gauge seat 9.10. The front flange 9.6 and the rear flange 9.11 are circumferentially welded to the cylinder 9.8; the vacuum gauge seat 9.10 is welded to the corresponding pressure measuring holes of the cylinder 9.8, and the sealing ring 9.4 is installed in the sealing grooves of the front flange and the rear flange; the central openings of the front flange cover 9.2 and the rear flange cover 9.12 are respectively welded to the connecting pipe 9.1; bolts and nuts cooperate to fix the flange and the flange cover.

[0017] Furthermore, a conductive rubber lining 9.9 with a thickness of about 2 to 3 mm is bonded to the inner surface of the cylinder 9.8 to protect the pyrotechnic device from static electricity.

[0018] Furthermore, a conductive rubber plate 9.5 with a thickness of about 2 to 3 mm is bonded to the inner side of the front flange cover 9.2, and its diameter is slightly smaller than the inner diameter of the conductive rubber plate 9.5 to protect the launch tube and prevent collisions.

[0019] Based on the same concept of the utility model, the utility model also provides a test method for a vacuum test device for detecting the sealing performance of a cruise missile launch tube, the specific steps of which are as follows:

[0020] S1: Place the launch tube into the vacuum test chamber 9, seal the rear flange, close the stop valve 11, control valve 8, and exhaust valve 10, open the stop valve 4, start the vacuum pump 1 to pre-evacuate the vacuum buffer tank until the vacuum gauge 6 shows the required value, then stop and close the stop valve 4;

[0021] S2: Close the exhaust valve 10, adjust the pneumatic flow valve 7 to the set state, open the stop valve 11, and then open the control valve 8. When the vacuum gauge 6 installed on the vacuum test chamber shows the vacuum degree required by the product, close the control valve 8. After the pressure holding time is up, record the pressure drop value of the vacuum gauge;

[0022] S3: Open the exhaust valve 10, remove the rear flange of the vacuum test chamber 9, and then take out the test product.

[0023] The above one or more technical solutions of the present invention have at least one or more of the following technical effects:

[0024] The utility model discloses a vacuum testing device for detecting the sealing performance of a cruise missile launch tube, which is used to assess the sealing performance of the launch tube during the development or batch production stage. The device has the characteristics of high test efficiency, stable and adjustable air extraction rate, good consistency of test state, and long service life.

[0025] The device of the utility model uses a vacuum pump to evacuate the vacuum buffer tank in advance, and then the vacuum buffer tank acts as a vacuum generator for testing. One pre-vacuuming can meet the needs of multiple product tests. The larger the volume, the more products can be tested, thereby improving the test efficiency.

[0026] The utility model uses the vacuum buffer tank to indirectly serve as the vacuum generator, which reduces the starting frequency of the vacuum pump, prolongs the service life of the vacuum pump and its electrical control equipment, and reduces the equipment maintenance cost.

[0027] The device of the utility model uses a pneumatic flow regulating valve to replace the traditional manual valve to adjust the air pumping rate. The air pumping rate is stable and adjustable. Once adjusted, the consistency of the test state of each product can be guaranteed.

[0028] The low-pressure pneumatic hose, pneumatic joint and valve used in the device of the utility model are cheap and easy to purchase, and the implementation cycle is short and the optimization cost is low. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 : Working principle diagram of the vacuum test device for testing the sealing performance of cruise missile launch tubes;

[0030] Figure 2 : Schematic diagram of the vacuum test chamber structure for testing the sealing performance of cruise missile launch tubes;

[0031] Figure 3 : Schematic diagram of the structure of the vacuum buffer tank and its accessories used for the sealing test of the cruise missile launch tube;

[0032] Figure 4 : Schematic diagram of the vacuum test device for testing the sealing performance of cruise missile launch tubes;

[0033] Including: 1-vacuum pump, 2-pneumatic quick connector, 3-pneumatic hose, 4-stop valve 1, 5-vacuum buffer tank, 6-vacuum gauge, 7-pneumatic flow control valve, 8-control valve, 9-test chamber, 10-exhaust valve, 11-stop valve 2, 5.1-tank body, 5.2-lock, 5.3-sealing rubber gasket, 5.4-tank cover, 5.5-copper gasket, 9.1-connecting pipe, 9.2-front flange cover, 9.3-bolt, 9.4-sealing ring, 9.5-conductive rubber sheet, 9.6-front flange, 9.7-nut, 9.8-cylinder, 9.9-conductive rubber sheet lining, 9.10-vacuum gauge seat, 9.11-rear flange, 9.12-rear flange cover. Specific implementation plan

[0034] The utility model relates to a vacuum test device for detecting the sealing performance of a cruise missile launch tube. The sealing performance of the launch tube is determined by placing the launch tube into a vacuum test chamber, evacuating the chamber, and observing the pressure drop of the vacuum gauge. The device is mainly composed of an exhaust valve, a vacuum test chamber (including a vacuum gauge), a control valve, a pneumatic pipeline, a pneumatic flow regulating valve, a switch valve, a vacuum buffer tank (including a stop valve), and a vacuum pump connected in sequence according to the direction of evacuation. When evacuating the chamber, the vacuum pump is started in advance to evacuate the vacuum buffer tank. After reaching a certain vacuum degree, the buffer tank is used as a vacuum generator to evacuate the vacuum test chamber. The evacuation rate is adjusted and set by the pneumatic flow regulating valve, and the opening and closing control of the air path is realized by the control valve. The vacuum buffer tank acts as a vacuum generator, avoiding frequent starting and stopping of the vacuum pump, thereby extending the service life of the equipment; one evacuation can meet the test requirements of multiple products, thereby improving the test efficiency; the evacuation rate is stable and adjustable, ensuring the consistency of the product test state.

[0035] The following is a clear and complete description of the technical solutions in the embodiments of the present invention in conjunction with the embodiments and drawings of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, rather than all the embodiments obtained. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field are within the scope of protection of the present invention.

[0036] Working principle of the test device

[0037] The working principle diagram of the utility model vacuum test device is as follows Figure 1 As shown. In the figure, the pneumatic hose 3 is connected to the valve and equipment using a pneumatic quick connector 2. Its working principle is described in three parts: before the test, during the test, and after the test. The work before the test is to put the product in and pre-vacuum it. The specific process is: after placing the launch tube into the vacuum test chamber 9, close the rear flange, close the stop valve 11, the control valve 8, and the exhaust valve 10, open the stop valve 4, start the vacuum pump 1 to pre-vacuum the vacuum buffer tank until the vacuum gauge 6 shows the required value, then stop and close the stop valve 4; during the test, close the exhaust valve 10, adjust the pneumatic flow valve 7 to the set state, open the stop valve 11, and then open the control valve 8. When the vacuum gauge 6 installed on the vacuum test chamber shows the vacuum degree required by the product, close the control valve 8. After the pressure holding time is up, record the vacuum gauge pressure drop value; after the test, open the exhaust valve 10, remove the rear flange of the vacuum test chamber 9, and take out the test product. If the equipment is not used for a long time, open the stop valves 4 and 11, the control valve 8, and the exhaust valve 10 to exhaust the gas in the pneumatic pipeline, the vacuum buffer tank 5, and the vacuum test chamber 9.

[0038] (2) Specific implementation plan

[0039] The specific implementation of the plan is elaborated in three parts according to the composition of the vacuum test device, including the design of the vacuum test chamber structure, the design of the vacuum buffer tank structure and its accessories, and the design of the overall interface scheme of the vacuum test device.

[0040] Figure 2 This is the structure of the vacuum test chamber 9 of the vacuum test device. Front flange 9.6 and rear flange 9.11 are circumferentially welded to the cylinder. Vacuum gauge holder 9.10 is welded to the corresponding pressure tapping holes in cylinder 9.8. A conductive rubber lining approximately 2-3 mm thick is bonded to the inner surface of the cylinder (to protect against static electricity in pyrotechnic devices). Sealing ring 9.4 is installed in the sealing grooves of the front and rear flanges. The central openings of the front and rear flange covers 9.2 and 9.12 are welded to the connecting pipe 9.1. A conductive rubber sheet approximately 2-3 mm thick is bonded to the inside of front flange cover 9.2 (to protect the launch tube and prevent collisions). The diameter of the sheet is slightly smaller than the inner diameter of the conductive rubber sheet 9.5. Bolts 9.3 pass through the apertures of front flange 9.6, rear flange 9.11, and front and rear flange covers 9.2 and 9.12, and are then secured with nuts 9.7. Connecting pipe 9.1 is welded to the central openings of the front and rear flange covers 9.2 and 9.12, respectively.

[0041] Figure 3This is the structure of the vacuum buffer tank 5 and its accessories. An annular sealing rubber gasket 5.3 is placed flat on the tank body 5.1. Three to four locking latches are welded to the upper side of the outer wall of the tank body 5.1. The tank cover 5.4 is locked to the tank body 5.1 via locking latches 5.2. The connecting pipe 9.1 and the vacuum gauge base 9.10 are welded to the three light holes in the tank cover 5.4. The internal threaded opening on one side of the stop valve 4 is fastened to the external thread of the pneumatic quick connector 2, while the internal thread on the other side is fastened to the external thread of the connecting pipe 9.1. The internal threaded opening on one side of the stop valve 11 is fastened to the external thread of the pneumatic quick connector 2, while the internal thread on the other side is fastened to the external thread of the connecting pipe 9.1. A copper gasket 5.5 is installed at the bottom of the vacuum gauge 6 and is connected to the vacuum gauge base 9.10 via threads.

[0042] Figure 4 This diagram shows the vacuum test setup, illustrating the interfaces between the vacuum pump 1, vacuum buffer tank 5, valves, pneumatic hoses, and vacuum test chamber 9. The pneumatic quick connector 2, pneumatic hose 3, shutoff valve 4, shutoff valve 11, control valve 8, and exhaust valve 10 are all commercially available low-pressure products, meeting operational requirements while reducing implementation costs.

[0043] The threaded port of pneumatic quick connector 2 is connected to the threaded exhaust port of vacuum pump 1; both ends of pneumatic flow control valve 7 are connected to pneumatic quick connector 2 via threaded interfaces; one end of control valve 8 is internally threaded to the external thread of connecting pipe 9.1 of vacuum test chamber 9, and the other end is threaded to pneumatic quick connector 2; one end of exhaust valve 10 is internally threaded to the external thread of connecting pipe 9.1 of vacuum test chamber 9; both ends of pneumatic hose 3 are inserted into pneumatic quick connector 2; and vacuum gauge 6 is screwed into vacuum gauge holder 9.10. At this point, the construction of the vacuum test device is complete.

[0044] The specific implementation of the present invention is not unique in its physical form and may be in accordance with the above-mentioned Figure 1 Any combination of the above working principles does not affect the specific implementation effect of the present invention.

[0045] Obviously, those skilled in the art may make various changes and modifications to the embodiments of the present invention without departing from the spirit and scope of the embodiments of the present invention. Thus, if such modifications and variations of the embodiments of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is intended to include such modifications and variations.

[0046] The pneumatic flow control valve described in this utility model is not limited to a specific product. Pneumatic flow control valves of various specifications can also be connected in parallel to meet the testing requirements of different types of launch tubes. The vacuum buffer tank structure is not limited to that described in this utility model and can be any tank or box with similar functions. A vacuum pump, multiple vacuum buffer tanks, and parallel branches of multiple vacuum test chambers can be used to meet the needs of rapid batch testing.

[0047] This new model has been successfully used to test the sealing performance of a certain type of launch tube. The results show that the operation is simple, the air extraction rate is stable and adjustable, the frequency of frequent equipment starts and stops is reduced, and the test state consistency is good.

Claims

1. A vacuum test device for detecting the sealing performance of a cruise missile launch tube, characterized by: The device is composed of an exhaust valve (10), a test chamber (9), a control valve (8), a pneumatic flow regulating valve (7), a stop valve 2 (11), a vacuum buffer tank (5), a stop valve 1 (4), and a vacuum pump (1) connected in sequence according to the direction of exhaust. The exhaust valve (10) is connected to the test chamber (9) via a connecting pipe, and the other end of the test chamber (9) is connected to the control valve (8) via a connecting pipe; The other end of the control valve (8) is connected to the pneumatic flow regulating valve (7) via a pneumatic hose (3); The other end of the pneumatic flow regulating valve (7) is connected to the stop valve 2 (11) via a pneumatic hose (3); The vacuum buffer tank (5) is connected to the stop valve 1 (4) and the stop valve 2 (11); The stop valve 1 (4) is connected to the vacuum pump (1) via a pneumatic hose (3); The vacuum buffer tank (5) and the test chamber (9) are both provided with a vacuum gauge (6), and the interfaces of the vacuum pump (1), the stop valve 1 (4), the stop valve 2 (11), the pneumatic flow regulating valve (7) and the control valve (8) are all provided with a pneumatic quick connector (2).

2. The vacuum testing device for detecting the sealing performance of a cruise missile launch tube according to claim 1 is characterized in that: The vacuum buffer tank (5) is composed of a tank body (5.1), a lock buckle (5.2), a sealing rubber pad (5.3) and a tank cover (5.4). An annular sealing rubber pad (5.3) is placed flat on the tank body (5.1), 3 to 4 lock buckles are welded to the upper side of the outer wall of the tank body (5.1), and the tank cover (5.4) is locked to the tank body (5.1) by the lock buckle (5.2); a connecting pipe (9.1) connecting the stop valve 1 (4) and the stop valve 2 (11), and a vacuum gauge seat (9.10) are respectively welded to the three light holes on the tank cover (5.4).

3. The vacuum testing device for detecting the sealing performance of a cruise missile launch tube according to claim 2 is characterized in that: The internal thread port on one side of the stop valve is tightly connected to the external thread of the pneumatic quick connector (2), and the internal thread on the other side is tightly connected to the external thread of the connecting pipe (9.1).

4. The vacuum testing device for detecting the sealing performance of a loitering missile launch tube according to any one of claims 2 or 3, characterized in that: A copper pad (5.5) is provided at the bottom of the vacuum gauge (6) and is connected to the vacuum gauge seat (9.10) through a thread.

5. The vacuum testing device for detecting the sealing performance of a cruise missile launch tube according to claim 1 is characterized in that: The test chamber (9) is composed of a connecting pipe (9.1), a front flange cover (9.2), a front flange (9.6), a rear flange (9.11), a rear flange cover (9.12), bolts (9.3), a sealing ring (9.4), a conductive rubber plate (9.5), nuts (9.7), a cylinder (9.8), a conductive rubber plate lining (9.9) and a vacuum gauge seat (9.10). The front flange (9.6) and the rear flange (9.11) are circumferentially welded to the cylinder (9.8); the corresponding pressure measuring holes of the vacuum gauge seat (9.10) and the cylinder (9.8) are welded, and the sealing ring (9.4) is installed in the sealing grooves of the front flange and the rear flange; the central openings of the front flange cover (9.2) and the rear flange cover (9.12) are respectively welded to the connecting pipe (9.1); bolts and nuts cooperate to fix the flange and the flange cover.

6. The vacuum testing device for detecting the sealing performance of a cruise missile launch tube according to claim 5, characterized in that: A conductive rubber lining (9.9) with a thickness of about 2 to 3 mm is bonded to the inner surface of the cylinder (9.8) to protect the pyrotechnic device from static electricity.

7. The vacuum testing device for detecting the sealing performance of a cruise missile launch tube according to claim 5, characterized in that: The inner side of the front flange cover (9.2) is bonded with a conductive rubber plate (9.5) with a thickness of about 2 to 3 mm, and the diameter of the conductive rubber plate (9.5) is slightly smaller than the inner diameter of the conductive rubber plate (9.5) to protect the launch tube and prevent collision.

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