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

Abstract

The invention relates to a vacuum test device and method for leakproofness detection of a patrol bomb launch canister. The leakproofness qualification 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 invention relates to the technical field of launch tubes, and in particular to a vacuum test device and a test method for detecting the sealing performance of a launch tube of a cruise missile. Background Art

[0002] The individual cruise missile is a short-range weapon carried by a single soldier for over-the-horizon patrol reconnaissance and attacking enemy important equipment or personnel. The launch tube is responsible for launching the individual cruise missile and is also an important protective barrier during the storage and transportation of the cruise missile. The sealing of the launch tube itself directly affects the protective effect of the cruise missile.

[0003] The existing vacuum test device for testing the sealing performance of the cruise missile launch tube is composed of a vacuum pump, pipelines, a manual stop valve, a vacuum test chamber (with a vacuum gauge) and a vacuum test chamber exhaust valve. When assessing the sealing performance of the launch tube, place the launch tube in the vacuum test chamber, close the exhaust valve, start the vacuum pump and control the vacuum test chamber's evacuation rate by controlling the opening of the manual stop valve. When the vacuum indication value reaches the requirement, close the manual stop valve first and then the vacuum pump to maintain the pressure. The sealing performance of the launch tube is judged by observing whether the pressure drop value of the vacuum gauge exceeds the maximum allowable value during the pressure maintenance time.

[0004] The shortcomings of the existing technical solutions are reflected in the following aspects: First, the air extraction rate is adjusted by manually controlling the valve opening, and the air extraction rate is unstable. If the opening is too large, instantaneous closure will aggravate gas vibration, 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 air extraction 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 state of the air extraction rate controlled by manual control of the valve opening is different each time, resulting in inconsistent test states 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 prior art, the present invention provides a vacuum testing device for detecting the sealing performance of a cruise missile launch tube, which overcomes the shortcomings of the prior art 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 invention 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 exhaust direction.

[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 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 on the upper side of the outer wall of the tank body 5.1, and the tank cover 5.4 is locked with the tank body 5.1 by the lock buckle 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 threaded port on one side of the stop valve is fastened and connected to the external thread of the pneumatic quick connector 2, and the internal thread on the other side is fastened and connected 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 threads.

[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 formed by ring welding with 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 the diameter is slightly smaller than the inner diameter of the conductive rubber plate 9.5, so as to protect the launch tube and prevent collision.

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

[0020] S1: Place the launch tube into the vacuum test chamber 9, seal 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-evacuate the vacuum buffer tank until the vacuum gauge 6 shows the required value, and then stop, 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 reached, 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 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 present invention 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 testing efficiency, stable and adjustable air extraction rate, good consistency of testing state and long service life.

[0025] The device of the present invention pre-evacuates the vacuum buffer tank by a vacuum pump, and then the vacuum buffer tank acts as a vacuum generator for testing. One pre-vacuuming can meet the test of multiple products. The larger the volume, the more test products there are, thereby improving the test efficiency.

[0026] The device of the present invention uses the vacuum buffer tank to indirectly serve as a 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 present invention uses a pneumatic flow regulating valve to replace the traditional manual valve to adjust the air extraction rate. The air extraction 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 present invention are cheap and easy to purchase, with a short implementation cycle and low optimization cost. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

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

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

[0033] Among them: 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 pad, 5.4-tank cover, 5.5-copper pad, 9.1-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 present invention relates to a vacuum test device for detecting the sealing property of a cruise missile launch tube. The sealing property of the launch tube is determined by placing the launch tube into a vacuum test chamber to evacuate the chamber and observing the pressure drop of a 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 a certain vacuum degree is reached, 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 gas circuit is realized by the control valve. The vacuum buffer tank acts as a vacuum generator to avoid frequent start and stop of the vacuum pump, thereby extending the service life of the equipment; one evacuation can meet the test requirements of multi-shot products and improve 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 combination with the embodiments of the present invention and the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the obtained embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field belong to the scope of protection of the present invention.

[0036] Working principle of the test device

[0037] The working principle diagram of the vacuum test device of the present invention is as follows Figure 1 As shown. In the figure, the pneumatic hose 3 is connected to the valve and equipment by a pneumatic quick connector 2. The 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 putting 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 reached, 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 then 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.

[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 It is the structure of the vacuum test chamber 9 of the vacuum test device. The front flange 9.6 and the rear flange 9.11 are formed by ring welding with the cylinder, the vacuum gauge seat 9.10 is welded to the corresponding pressure measuring hole of the cylinder 9.8, and a layer of conductive rubber lining with a thickness of about 2 to 3 mm is bonded to the inner surface of the cylinder (for the static protection of pyrotechnics); the sealing ring 9.4 is installed in the sealing grooves of the front and rear flanges; the central openings of the front flange cover 9.2 and the rear flange cover 9.12 are respectively welded to the pipe 9.1, wherein the inner side of the front flange cover 9.2 is bonded with a conductive rubber plate with a thickness of about 2 to 3 mm (to protect the launch tube and prevent collision), and the diameter is slightly smaller than the inner diameter of the conductive rubber plate 9.5; the bolt 9.3 passes through the light holes of the front flange 9.6, the rear flange 9.11 and the front flange cover 9.2 and the rear flange cover 9.12 and is fastened with a nut 9.7; the pipe 9.1 is respectively welded to the central openings of the front flange cover 9.2 and the rear flange cover 9.12.

[0041] Figure 3It is the structure of the vacuum buffer tank 5 and its accessories. An annular sealing rubber pad 5.3 is placed flat on the tank body 5.1, 3 to 4 locks are welded on the upper side of the outer wall of the tank body 5.1, and the tank cover 5.4 is locked with the tank body 5.1 by the lock 5.2; the connecting pipe 9.1 and the vacuum gauge seat 9.10 are welded with the three light holes on the tank cover 5.4; the internal threaded port on one side of the stop valve 4 is fastened with the external thread of the pneumatic quick connector 2, and the internal thread on the other side is fastened with the external thread of the connecting pipe 9.1; the internal threaded port on one side of the stop valve 11 is fastened with the external thread of the pneumatic quick connector 2, and the internal thread on the other side is fastened with the external thread of the connecting pipe 9.1; a copper pad 5.5 is arranged at the bottom of the vacuum gauge 6 and is connected to the vacuum gauge seat 9.10 through threads.

[0042] Figure 4 The figure is a diagram of a vacuum test device, which shows the interface relationship of the components such as the vacuum pump 1, the vacuum buffer tank 5, the valve, the pneumatic hose, and the vacuum test chamber 9. In the figure, the pneumatic quick connector 2, the pneumatic hose 3, the stop valve 4, the stop valve 11, the control valve 8, and the exhaust valve 10 are all low-pressure products that are easily available on the market, which can not only meet the use requirements but also reduce the implementation cost.

[0043] The threaded port of the pneumatic quick connector 2 is connected to the exhaust threaded port of the vacuum pump 1; the two ends of the pneumatic flow control valve 7 are connected to the pneumatic quick connector 2 through threaded interfaces; the internal thread of one end of the control valve 8 is connected to the external thread of the connecting pipe 9.1 of the vacuum test chamber 9, and the other end is connected to the pneumatic quick connector 2 through threads; the internal thread on one side of the exhaust valve 10 is connected to the external thread of the connecting pipe 9.1 of the vacuum test chamber 9; the two ends of the pneumatic hose 3 are respectively inserted into the pneumatic quick connector 2; the vacuum gauge 6 is fastened to the vacuum gauge seat 9.10 through threads. At this point, the construction of the vacuum test device is completed.

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

[0045] Obviously, those skilled in the art can 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 these 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 also intended to include these modifications and variations.

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

[0047] The invention has been successfully used for the sealing test 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 start and stop of the equipment is reduced, and the consistency of the test state is good.

Claims

1. A vacuum test device for detecting the sealing performance of a cruise missile launch tube, characterized in that: The device is composed of an exhaust valve (10), a test chamber (9), a control valve (8), a pneumatic flow control valve (7), a stop valve 2 (11), a vacuum buffer tank (5), a stop valve 1 (4), and a vacuum pump (1) which are connected in sequence according to the exhaust direction. 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; 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 control 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 pneumatic quick connectors (2).

2. The vacuum test device for detecting the sealing performance of the 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); the tank cover (5.4) and the tank body (5.1) are locked by the lock buckle (5.2); a 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 test device for detecting the sealing performance of the 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 pipe (9.1).

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

5. The vacuum test device for detecting the sealing performance of the 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 formed by ring welding with 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); and the bolts and nuts cooperate to fix the flange and the flange cover.

6. The vacuum test device for detecting the sealing performance of the cruise missile launch tube according to claim 5 is 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 pyrotechnics from static electricity.

7. The vacuum test device for detecting the sealing performance of the cruise missile launch tube according to claim 5 is 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.

8. The test method of the vacuum test device for detecting the sealing performance of the cruise missile launch tube according to claim 1 is characterized in that: The specific steps are as follows: S1: Place the launch tube into the vacuum test chamber (9), seal 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-evacuate the vacuum buffer tank until the vacuum gauge (6) indicates the required value, and then stop and close the stop valve (4); 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 reaches the vacuum degree required by the product, close the control valve (8). After the pressure holding time is reached, record the pressure drop value of the vacuum gauge; S3: Open the exhaust valve (10), remove the rear flange of the vacuum test chamber (9), and then take out the test product.

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