Thermal vacuum and thermal cycle test system for space micropump

Abstract

The invention discloses a thermal vacuum and thermal cycle test system for a space micropump, and aims to solve the problems that a medium leaks in a high and low temperature test process of an existing test system, the space micropump cannot operate normally after air enters a test loop, and even the test cannot be carried out. The device comprises a thermal circulation assembly, a transfer injection tank, a connecting piece, a first hand valve, a first pressure gauge, a vacuum pump, a second hand valve, a second pressure gauge, a pressure reducer and an air source, the thermal circulation assembly is connected with the first hand valve and the second hand valve through the connecting piece, the first hand valve is connected with the first pressure gauge through a connecting pipeline, and the first pressure gauge is connected with the vacuum pump through a pipeline; the second hand valve is connected with a long guide pipe connector of the transfer injection tank through a pipeline, a short guide pipe connector of the transfer injection tank is connected with a second pressure gauge through a pipeline, and the second pressure gauge is connected to a pressure reducer which is connected with an air source. The sealing device is simple in structure, easy to machine and high in sealing reliability. The device is used for high and low temperature test performance testing of the space micropump and the pump valve assembly.

Description

Technical Field

[0001] The invention relates to a test system for a space micro pump, in particular to a thermal vacuum and thermal cycle test system for a space micro pump. The invention belongs to the field of aerospace technology. Background Art

[0002] Chang'e-7 is China's probe that conducts a comprehensive exploration mission of the lunar topography, material composition, and space environment. In order to verify the environmental adaptability of its space micropumps and pump-valve components, it is necessary to assess the thermal cycle, thermal vacuum, and cycle aging performance of the products. The existing test system uses a spherical-conical structure. Due to the large number of sealed spherical-conical structures and low reliability, medium leakage problems may occur during the test process, and the space micropump cannot operate normally, and the test may even be unable to proceed. In addition, the flow resistance requirements cannot be met during the test, and the vacuum pumping and medium filling functions cannot be taken into account.

[0003] Therefore, in order to meet the needs of thermal testing of pump and valve components, a test system that can meet the flow resistance requirements, ensure that there will be no leakage of the medium, and take into account the vacuum pumping and medium filling work is urgently needed. After the filling is completed, the seal can be separated and the product and circuit can be thermally tested separately. Summary of the invention

[0004] The present invention aims to solve the problems that the existing test system may leak medium during high and low temperature tests, the space micropump cannot operate normally after the test system is air-intaken, and even the test cannot be carried out, and the flow resistance requirements cannot be met during the test, and the vacuum pumping and medium filling functions cannot be taken into account. A space micropump thermal vacuum and thermal cycle test system is proposed.

[0005] The technical solution adopted by the present invention to solve the above problems is:

[0006] The invention comprises a thermal cycle component, a transfer tank, a connecting piece, a first hand valve, a first pressure gauge, a vacuum pump, a second hand valve, a second pressure gauge, a pressure reducer and a gas source. The thermal cycle component is respectively connected with the first hand valve and the second hand valve through the connecting piece, the first hand valve is connected with the first pressure gauge through a connecting pipeline, and the first pressure gauge is connected with the vacuum pump through a pipeline; the second hand valve is connected with a long conduit joint of the transfer tank through a pipeline, the short conduit joint of the transfer tank is connected with the second pressure gauge through a pipeline, the second pressure gauge is connected with the pressure reducer, and the pressure reducer is connected with the gas source.

[0007] Further, the thermal cycle component includes a first double O-ring joint, an elbow, a throttling assembly, a long tube, a second double O-ring joint, a first joint seat, a three-way tube, an exhaust valve, a third double O-ring joint, a second joint seat and a fourth double O-ring joint. The first double O-ring joint is connected to the throttling assembly through the elbow, the throttling assembly is connected to one end of the long tube, the other end of the long tube is connected to the second double O-ring joint, the second double O-ring joint is connected to the left port of the three-way tube through the first joint seat; the right port of the three-way tube is connected to the third double O-ring joint, the third double O-ring joint is connected to the fourth double O-ring joint through the second joint seat, the upper port of the three-way tube is connected to the exhaust valve, and the exhaust valve is connected to the connecting piece.

[0008] Furthermore, the throttling assembly is composed of a plurality of throttling elements welded in sequence.

[0009] Furthermore, the transfer tank includes a tank body, an end cover, a short tube, a long tube and a sealing ring. The end cover is connected to the upper end of the tank body by bolts, and the end cover and the tank body are sealed by a sealing ring; the lower end of the long tube passes through the end cover and is inserted into the tank body, the short tube is inserted on the end cover, and the lower end of the short tube is located at the upper port position of the tank body.

[0010] Furthermore, the first double O-ring joint includes a joint body, a nut and two O-rings, the nut is sleeved on the right end of the joint body, two O-rings are arranged between the nut and the right end of the joint body, and the two O-rings are arranged in sequence from left to right.

[0011] The beneficial effects of the present invention are:

[0012] 1. The present invention utilizes a combination of throttling elements to implement thermal testing of space micropumps with different flow rates and lifts, and always ensures that the space micropump operates at the rated operating point;

[0013] 2. The present invention uses a filling and exhaust valve to ensure the isolation of the product circuit under test from the filling and vacuuming pipelines during the vacuuming and filling process, thereby ensuring the internal sealing of the circuit;

[0014] 3. The present invention adopts double O-ring joints to ensure reliable sealing, and no leakage will occur during the high and low temperature alternation process. At the same time, it is convenient to disassemble the product and the test pipeline, and the operation is simple;

[0015] 4. The present invention can be widely applied to space micropump thermal tests under various media and various working pressures, and has great market competitiveness. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0017] Figure 2 is a schematic diagram of the structure of the thermal cycle assembly;

[0018] Figure 3 It is a structural schematic diagram of the transfer tank;

[0019] Figure 4 It is a structural diagram of a double O-ring connector.

[0020] In the figure, thermal cycle component 1, transfer tank 2, connector 3, first hand valve 4, first pressure gauge 5, vacuum pump 6, second hand valve 7, second pressure gauge 8, pressure reducer 9, gas source 10, first double O-ring joint 1-1, elbow 1-2, first throttling element 1-3, second throttling element 1-4, long tube 1-5, second double O-ring joint 1-6, first joint seat 1-7, three-way pipe 1-8, adding and discharging valve 1-9, third double O-ring joint 1-10, second joint seat 1-11, fourth double O-ring joint 1-12, tank body 2-1, end cover 2-2, short conduit 2-3, long conduit 2-4, sealing ring 2-5, joint body 1-1-1, nut 1-1-2, O-ring sealing ring 1-1-3. DETAILED DESCRIPTION

[0021] The present embodiment describes a space micro pump thermal vacuum and thermal cycle test system, such as Figure 1 As shown, the test system includes a thermal cycle component 1, a transfer tank 2, a connector 3, a first hand valve 4, a first pressure gauge 5, a vacuum pump 6, a second hand valve 7, a second pressure gauge 8, a pressure reducer 9 and a gas source 10.

[0022] like Figure 2 As shown, the thermal cycle assembly 1 includes a first double O-ring joint 1-1, an elbow 1-2, a throttling assembly, a long tube 1-5, a second double O-ring joint 1-6, a first joint seat 1-7, a three-way pipe 1-8, an addition and discharge valve 1-9, a third double O-ring joint 1-10, a second joint seat 1-11 and a fourth double O-ring joint 1-12. The first double O-ring joint 1-1 is connected to the throttling assembly through the elbow, the throttling assembly is connected to one end of the long tube 1-5, and the throttling assembly is connected to the elbow 1-2 and the long tube 1-5. All joints are connected by welding; the other end of the long tube 1-5 is welded to the second double O-ring joint 1-6, and the second double O-ring joint 1-6 is welded to the left port of the three-way pipe 1-8 through the first joint seat 1-7; the right port of the three-way pipe 1-8 is welded to the third double O-ring joint 1-10, and the third double O-ring joint 1-10 is welded to the fourth double O-ring joint 1-12 through the second joint seat 1-11, and the upper port of the three-way pipe 1-8 is welded to the addition and discharge valve 1-9, and the addition and discharge valve 1-9 is connected to the connecting piece 1-3.

[0023] The use of the filling and drain valves 1-9 can ensure the isolation of the product circuit under test from the filling and vacuum pipelines during the vacuuming and filling processes, especially the removal of the pipelines after filling to ensure the internal sealing of the circuit.

[0024] like Figure 3As shown, the transfer tank 2 includes a tank body 2-1, an end cover 2-2, a short conduit 2-3, a long conduit 2-4 and a sealing ring 2-5. The end cover 2-2 is connected to the upper end of the tank body 2-1 by bolts, and the end cover 2-2 and the tank body 2-1 are sealed by the sealing ring 2-5; the lower end of the long conduit 2-4 passes through the end cover 2-2 and is inserted into the tank body 2-1, the short conduit 2-3 is inserted on the end cover 2-2, and the lower end of the short conduit 2-3 is located at the upper port position of the tank body 2-1.

[0025] The connector 3 includes a pipeline joint and a tee, one end of the pipeline joint is connected to the addition and discharge valve 1-9, and the other end is connected to the tee, and the other two ends of the tee are respectively connected to the first hand valve 4 and the second hand valve 7. The first hand valve 4 is connected to the first pressure gauge 5 through a connecting pipeline, and the first pressure gauge 5 is connected to the vacuum pump 6 through a pipeline; the second hand valve 7 is connected to the long conduit 2-4 of the transfer tank 2 through a pipeline, and the short conduit 2-3 of the transfer tank 2 is connected to the second pressure gauge 8 through a pipeline, and the second pressure gauge 8 is connected to the pressure reducer 9, and the pressure reducer 9 is connected to the gas source 10.

[0026] Preferably, the throttling element is composed of a gradual tube structure, and the two ends of the tube body gradually narrow from wide to narrow towards the middle, which can avoid the low pressure area caused by excessive flow rate and cause the medium to vaporize. The entire throttling assembly is composed of multiple throttling elements welded together, and the flow resistance of multiple throttling elements is combined into the head of the product under test, so that the product under test can maintain working at the rated working condition.

[0027] Figure 2 In the figure, the inner diameter of the first throttling element 1-3 is 1 mm, and the flow resistance is 50 kPa, the inner diameter of the second throttling element is 2 mm, and the flow resistance is 15 kPa, and the two throttling elements are welded together.

[0028] Preferably, Figure 4 As shown, the first double O-ring joint 1-1 includes a joint body 1-1-1, a nut 1-1-2 and two O-rings 1-1-3, the nut 1-1-2 is mounted on the right end of the joint body 1-1-1, and two O-rings 1-1-3 are arranged between the nut 1-1-2 and the right end of the joint body 1-1-1, and the two O-rings 1-1-3 are arranged in sequence from left to right.

[0029] The first double O-ring connector 1-1, the second double O-ring connector 1-6, the third double O-ring connector 1-10 and the fourth double O-ring connector 1-12 adopt the same structure; the first connector seat 1-7 and the second connector seat 1-11 adopt the same structure. The two O-rings 1-1-3 between the second double O-ring connector 1-6 and the first connector seat 1-7, and between the third double O-ring connector 1-10 and the second connector seat 1-11 can achieve reliable sealing of the connector position without leakage, and facilitate the disassembly of the product and the test pipeline.

[0030] When installing the double O-ring joint and the joint seat, insert the right end of the joint body into the left end of the joint seat and weld them together. The two O-rings are located between the joint body and the joint seat, and the joint position of the two is sealed reliably without leakage. Finally, tighten the nut on the outer periphery of the joint seat to tighten it.

[0031] Preferably, the material of the O-ring is EPDM rubber, which can meet the high and low temperature requirements of the thermal test, while ensuring reliable sealing without leakage; in addition, the use of a plunger joint facilitates disassembly of the product and the test pipeline, and the operation is simple.

[0032] The present invention can be designed according to different combinations of throttling elements to achieve rated operating point operation of the pump product under test, while the sealing is reliable and no leakage will occur during thermal cycle and other test processes. The system has a simple structure, is easy to process, has high sealing reliability, and has certain advantages in being promoted and applied in thermal testing of power components such as space micropumps. The present invention can withstand a test environment of -35 to 70°C and can meet a variety of harsh space environments. At the same time, the present invention can be widely promoted and applied to thermal testing of space micropumps under various media and various working pressures, and has huge market competitiveness.

[0033] How it works

[0034] 1. Vacuum the system;

[0035] The integrated pump-valve assembly 11 to be tested is connected to the test system through the first double O-ring connector 1-1 and the fourth double O-ring connector 1-12. After the connection, the first hand valve 4 connected to the vacuum pump 6 is opened, the second hand valve 7 connected to the transfer tank 2 is closed, the addition and discharge valve 1-9 is opened, and the vacuum pump 6 is turned on, so that the loop system and the product to be tested can be vacuumed;

[0036] 2. Fill the circuit and the product under test;

[0037] When the vacuum degree in the system reaches below 0.1Pa, close the first hand valve 4 connected to the vacuum pump 6, open the second hand valve 7 connected to the transfer tank 2, use the gas source 10 to pressurize the transfer tank 2, and let the liquid medium inside the transfer tank 2 slowly flow into the loop until the medium completely fills the loop and the product under test. After filling, the pressure of the gas source 10 can be adjusted to pressurize the entire loop and the product under test, and to achieve performance testing under different background pressures.

[0038] 3. Heat test after separation:

[0039] Close the filling and discharging valves 1-9, dismantle the vacuum and filling pipelines, and the remaining fluid circuits and the product under test can be subjected to thermal tests separately.

[0040] 4. Pump operation:

[0041] When the pump is running, the flow resistance of the throttling element is consistent with the head of the pump's rated operating point, which can ensure that the pump always operates at the rated operating point.

[0042] The present invention can realize the thermal test of the space micro pump of the power component, and can be applied not only to the thermal test of the thermal control mechanical pump, but also to the thermal test test system of the on-orbit filling pump.

[0043] The above is only a preferred embodiment of the present invention and does not limit the present invention in any form. Although the present invention has been disclosed as a preferred embodiment as above, it is not used to limit the present invention. Any technician familiar with this profession can make some changes or modify the technical contents disclosed above into equivalent embodiments without departing from the scope of the technical solution of the present invention. However, any simple modification, equivalent replacement and improvement made to the above embodiments without departing from the content of the technical solution of the present invention, based on the technical essence of the present invention, within the spirit and principles of the present invention, still fall within the protection scope of the technical solution of the present invention.

Claims

1. A space micro pump thermal vacuum and thermal cycle test system, characterized in that: The test system comprises a thermal cycle component (1), a transfer tank (2), a connecting piece (3), a first hand valve (4), a first pressure gauge (5), a vacuum pump (6), a second hand valve (7), a second pressure gauge (8), a pressure reducer (9) and a gas source (10). The thermal cycle component (1) is connected to the first hand valve (4) and the second hand valve (7) respectively through the connecting piece (3); the first hand valve (4) is connected to the first pressure gauge (5) through a connecting pipeline; the first pressure gauge (5) is connected to the vacuum pump (6) through a pipeline; the second hand valve (7) is connected to the long conduit joint of the transfer tank (2) through a pipeline; the short conduit joint of the transfer tank (2) is connected to the second pressure gauge (8) through a pipeline; the second pressure gauge (8) is connected to the pressure reducer (9); and the pressure reducer (9) is connected to the gas source (10).

2. A space micro pump thermal vacuum and thermal cycle test system according to claim 1, characterized in that: The thermal cycle assembly (1) comprises a first double O-ring joint (1-1), an elbow (1-2), a throttling assembly, a long tube (1-5), a second double O-ring joint (1-6), a first joint seat (1-7), a three-way pipe (1-8), an addition and discharge valve (1-9), a third double O-ring joint (1-10), a second joint seat (1-11) and a fourth double O-ring joint (1-12). The first double O-ring joint (1-1) is connected to the throttling assembly via the elbow, the throttling assembly is connected to one end of the long tube (1-5), and the long tube (1-5) is connected to the throttling assembly via the elbow. ) is connected to a second double O-ring joint (1-6), the second double O-ring joint (1-6) is connected to the left port of the three-way pipe (1-8) through a first joint seat (1-7); the right port of the three-way pipe (1-8) is connected to a third double O-ring joint (1-10), the third double O-ring joint (1-10) is connected to a fourth double O-ring joint (1-12) through a second joint seat (1-11), the upper port of the three-way pipe (1-8) is connected to a charging and discharging valve (1-9), and the charging and discharging valve (1-9) is connected to a connecting piece (1-3).

3. A space micro pump thermal vacuum and thermal cycle test system according to claim 2, characterized in that: The throttling assembly is composed of a plurality of throttling elements welded in sequence.

4. A space micro pump thermal vacuum and thermal cycle test system according to claim 1, characterized in that: The transfer tank (2) comprises a tank body (2-1), an end cover (2-2), a short conduit (2-3), a long conduit (2-4) and a sealing ring (2-5); the end cover (2-2) is connected to the upper end of the tank body (2-1) by bolts, and the end cover (2-2) and the tank body (2-1) are sealed by the sealing ring (2-5); the lower end of the long conduit (2-4) passes through the end cover (2-2) and is inserted into the tank body (2-1); the short conduit (2-3) is inserted on the end cover (2-2), and the lower end of the short conduit (2-3) is located at the upper port position of the tank body (2-1).

5. A space micro pump thermal vacuum and thermal cycle test system according to claim 1, characterized in that: The first double O-ring joint (1-1) comprises a joint body (1-1-1), a nut (1-1-2) and two O-rings (1-1-3); the nut (1-1-2) is sleeved on the right end of the joint body (1-1-1); two O-rings (1-1-3) are arranged between the nut (1-1-2) and the right end of the joint body (1-1-1); the two O-rings (1-1-3) are arranged in sequence from left to right.

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