Spacecraft two-phase fluid loop pump valve assembly performance test system and method

Abstract

The invention relates to a spacecraft two-phase fluid loop pump valve assembly performance testing system and method, and belongs to the technical field of pump valve testing. Comprising a valve group, a liquid storage device, a first valve, a mechanical pump, a second valve, a third valve, a flow regulating valve, a first heat exchanger, a sixth valve, a fourth valve and a fifth valve, the valve group, the liquid storage device, the first valve, the mechanical pump, the second valve, the flow regulating valve, the first heat exchanger and the sixth valve are sequentially connected, and the sixth valve is connected with the mechanical pump. One end of the third valve is connected with the mechanical pump, the other end of the third valve is connected with the second valve, the two ends of the flow adjusting valve are connected with the fourth valve and the fifth valve respectively, and the fourth valve and the fifth valve are connected with a tested piece. The device is reasonable in structural design and high in standardization degree, can be applied to the performance test of the high-low temperature alternating environment of 5-236 DEG C, is convenient to repair and maintain, and can be used for effectively verifying the performance indexes of various tested pieces.

Description

Technical Field

[0001] The invention relates to a pump valve component performance testing system, belonging to the technical field of pump valve testing. Background Art

[0002] The pump and valve products of the thermal control high-temperature fluid circuit of spacecraft need to be run-in tested under high temperature and high pressure conditions to test the flow resistance and operation stability of the pump and valve products under on-orbit operation conditions. For example, high-temperature mechanical pumps, filters, one-way valves, pressure sensors, liquid addition and discharge valves, and self-locking valves need to complete performance verification under high temperature before delivery. However, the existing technology is mostly tested at room temperature and low temperature, which cannot meet the requirements of high temperature verification performance indicators of pump and valve components and single-unit products.

[0003] Therefore, it is urgent to propose a spacecraft two-phase fluid circuit pump valve assembly performance testing system and method to solve the above technical problems. Summary of the invention

[0004] In order to solve the above problems, a spacecraft two-phase fluid circuit pump valve assembly performance test system and method are provided. A brief overview of the invention is given below to provide a basic understanding of certain aspects of the invention. It should be understood that this overview is not an exhaustive overview of the invention. It is not intended to identify the key or important parts of the invention, nor is it intended to limit the scope of the invention.

[0005] The technical solution of the present invention:

[0006] A performance test system for a spacecraft two-phase fluid circuit pump and valve assembly comprises a valve group, a liquid reservoir, a first valve, a mechanical pump, a second valve, a third valve, a flow regulating valve, a first heat exchanger, a sixth valve, a fourth valve and a fifth valve. The valve group, the liquid reservoir, the first valve, the mechanical pump, the second valve, the flow regulating valve, the first heat exchanger and one end of the sixth valve are connected in sequence, the other end of the sixth valve is connected to the mechanical pump, one end of the third valve is connected to the input end of the mechanical pump, that is, the mechanical pump, the second valve and the third valve connected in series are connected in parallel, the other end of the third valve is connected to the output end of the second valve, the two ends of the flow regulating valve are respectively connected to one end of the fourth valve and the fifth valve, the other ends of the fourth valve and the fifth valve are connected to a tested object, that is, the fourth valve, the tested object and the fifth valve connected in series are connected in parallel with the flow regulating valve.

[0007] Preferably, a second heat exchanger is further included, one end of the second heat exchanger is connected to the output end of the first heat exchanger, and the other end of the second heat exchanger is connected to the input end of the mechanical pump, that is, the second heat exchanger is connected in parallel with the sixth valve.

[0008] Preferably: the first heat exchanger is a high-temperature heat exchanger, and the second heat exchanger is a cooling heat exchanger, which are used for heating and cooling respectively.

[0009] Preferably: the valve group includes a valve and a pressure regulating valve, the valve and the pressure regulating valve are both connected to the input end of the liquid reservoir, the valve is used as a vacuum valve or a filling valve, when used as a vacuum valve, it is connected to the vacuum pump, when used as a filling valve, it is connected to the water tank, the pressure regulating valve is connected to the high-pressure gas tank, and the high-pressure gas tank can be filled with liquid nitrogen.

[0010] Preferably: it also includes a flow meter, which is a Coriolis flow meter and is arranged at the input end of the first heat exchanger; ensuring that the pipeline between the high-temperature heat exchanger and the condenser (cooling heat exchanger) is filled with water.

[0011] Preferably: it also includes a safety valve and a first pressure sensor, and the upper end of the liquid reservoir is provided with a safety valve and a first pressure sensor; the liquid reservoir (liquid storage tank) plays a role of safety protection and pressure regulation, and the safety valve on the liquid reservoir automatically releases the pressure when the pressure is higher than 4MPA.

[0012] Preferably: it also includes a detection valve, one end of which is connected to the input end of the tested piece, and the detection valve is used as a vacuum valve or a filling valve. When used as a vacuum valve, the other end of the detection valve is connected to a vacuum pump, and when used as a filling valve, it is connected to a water tank.

[0013] Preferably, a filter is also included, the sixth valve, the second heat exchanger, and the output end of the first valve are connected to one end of the filter, and the mechanical pump and the input end of the third valve are connected to the other end of the filter.

[0014] Preferably: the input end and the output end of the liquid reservoir are respectively provided with a first temperature sensor and a second temperature sensor, the input end of the filter is provided with a second pressure sensor, the third pressure sensor, the mechanical pump, the second valve, and the fourth pressure sensor connected in series are connected in parallel with the first valve, one end of the tested piece is sequentially provided with a third temperature sensor and a fifth pressure sensor, the other end of the tested piece is sequentially provided with a fourth temperature sensor and a sixth pressure sensor, the two ends of the first heat exchanger are respectively provided with a fifth temperature sensor and a sixth temperature sensor, the sixth valve connected in parallel and the two ends of the second heat exchanger are respectively provided with a seventh temperature sensor and an eighth temperature sensor for detecting temperature and pressure; the tested piece is connected to a pipeline of a spacecraft two-phase fluid circuit pump and valve assembly performance test system through an interface, the tested piece is connected to the third temperature sensor and the fourth temperature sensor at both ends through an interface, the interface is a 60° ball head sealing joint, a 60° spherical pipe connector outer sleeve nut and a 60° spherical pipe connector welding nozzle, and the tested piece is a spacecraft two-phase fluid circuit pump and valve assembly, including a filter, a one-way valve, a pressure sensor or a liquid addition and discharge valve.

[0015] A method for testing the performance of a spacecraft two-phase fluid circuit pump and valve assembly, using a spacecraft two-phase fluid circuit pump and valve assembly performance testing system (hereinafter referred to as the system), comprises the following steps:

[0016] Step 1: Before filling the system, evacuate the system through the valve, and then fill the system with water. The water is not completely filled. It is necessary to ensure that the pipeline between the high-temperature heat exchanger and the condenser is filled with water, and then close the valve;

[0017] Step 2: Close the first valve and adjust the pressure in the liquid reservoir (temperature control liquid reservoir) through the pressure regulating valve;

[0018] Step 3: Open the first valve, the second valve, and the sixth valve, and keep the third valve, the fourth valve, and the fifth valve closed. Use a commercially available high-temperature mechanical pump to drive the working fluid to flow in the loop. Use the first heat exchanger to heat the working fluid to a specified temperature. If the temperature exceeds the specified temperature, close the sixth valve to reduce the temperature to the specified test temperature.

[0019] Step 4: Make the second valve in the closed state, make the first valve, the third valve, the fourth valve, the fifth valve, and the sixth valve in the open state, use the flow control valve to adjust the pipeline flow, and perform a performance test on the tested part (tested high-temperature pump) at a specified temperature;

[0020] The third valve is closed, and the first valve, the second valve, the fourth valve, the fifth valve and the sixth valve are opened. The flow rate of the pipeline is adjusted using a flow regulating valve, and the performance test of the component under test is performed at a specified temperature.

[0021] The present invention has the following beneficial effects:

[0022] The invention has a reasonable structural design and a high degree of standardization, can be applied to performance testing in a high-low temperature alternating environment of 5 to 236°C, is easy to repair and maintain, and can effectively verify the performance indicators of various tested parts;

[0023] The liquid reservoir of the present invention plays a role of safety protection and pressure regulation. When the pressure is higher than 4MPA, the safety valve on the liquid reservoir automatically releases the pressure to ensure the safety of people and property.

[0024] The invention is easy to operate, can be put into operation after simple training, and has high testing efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 The present invention is a structural schematic diagram of a spacecraft two-phase fluid circuit pump and valve assembly performance test system.

[0026] Figure 2 It is a structural diagram of a 60° spherical pipe connector ball joint.

[0027] Figure 3 This is a structural diagram of a 60° spherical pipe connector outer nut.

[0028] Figure 4This is a structural diagram of a 60° spherical pipe connector welding nozzle.

[0029] In the figure: 1-valve group, 2-liquid reservoir, 3-first valve, 4-mechanical pump, 5-second valve, 6-third valve, 7-flow regulating valve, 8-first heat exchanger, 9-sixth valve, 10-second heat exchanger, 11-fourth valve, 12-fifth valve, 13-test piece, 14-filter, 15-flow meter, 16-detection valve, 110-valve, 120-pressure regulating valve, 21-safety valve, 22-first pressure sensor, T-temperature sensor, ×-pressure sensor. DETAILED DESCRIPTION

[0030] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is described below by the specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.

[0031] Specific implementation method 1: Combination Figure 1-4 The present embodiment is described. A performance test system for a two-phase fluid circuit pump and valve assembly of a spacecraft in the present embodiment includes a valve group 1, a liquid reservoir 2, a first valve 3, a mechanical pump 4, a second valve 5, a third valve 6, a flow regulating valve 7, a first heat exchanger 8, a sixth valve 9, a fourth valve 11 and a fifth valve 12. The valve group 1, the liquid reservoir 2, the first valve 3, the mechanical pump 4, the second valve 5, the flow regulating valve 7, the first heat exchanger 8 and one end of the sixth valve 9 are connected in sequence. The basic parameters of the flow resistance valve (flow regulating valve 7) are: the shell material of the flow resistance valve is 316 stainless steel, the working temperature is 20℃~250℃, the pressure is greater than 8Mpa, and the leakage rate is not large. At 1X10-7Pa·m3 / s, the other end of the sixth valve 9 is connected to the mechanical pump 4, one end of the third valve 6 is connected to the input end of the mechanical pump 4, that is, the mechanical pump 4, the second valve 5 and the third valve 6 are connected in parallel in series, the other end of the third valve 6 is connected to the output end of the second valve 5, the two ends of the flow control valve 7 are respectively connected to one end of the fourth valve 11 and the fifth valve 12, the other ends of the fourth valve 11 and the fifth valve 12 are connected to the measured object 13, that is, the fourth valve 11, the measured object 13, the fifth valve 12 and the flow control valve 7 are connected in parallel in series, and the components of the system are connected by pipelines, and the pipelines are made of stainless steel or titanium alloy with an inner diameter of 12mm and an outer diameter of 14mm;

[0032] It also includes a second heat exchanger 10, one end of which is connected to the output end of the first heat exchanger 8, and the other end of which is connected to the input end of the mechanical pump 4, that is, the second heat exchanger 10 is connected in parallel with the sixth valve 9; the second heat exchanger 10 is a condenser and a water cooler, the return liquid temperature of the water cooler is ≥150°C, and the cooling power is ≥10kW;

[0033] The first heat exchanger 8 is a high-temperature heat exchanger (heater), and the second heat exchanger 10 is a cooling heat exchanger, which are used for heating and cooling respectively; the heating power of the first heat exchanger 8 is not less than 6kW, the material working temperature requirement is 300°C, the outer wall pressure requirement of the heat exchanger is 6.5MPa, and the heating amount is continuously adjustable; the mechanical pump 4 is used to drive the working medium to flow in the circuit, and the basic technical requirements of the high-temperature mechanical pump are: flow rate not less than 200L / h, pump head not less than 40m, power consumption ≤600W, working temperature of 20°C to 280°C, pressure requirement of 6.5MPa, and the material in contact with the working medium is 316 stainless steel or titanium alloy;

[0034] The valve group 1 includes a valve 110 and a pressure regulating valve 120. Both the valve 110 and the pressure regulating valve 120 are connected to the input end of the liquid reservoir 2. The valve 110 is used as a vacuum valve or a filling valve. When used as a vacuum valve, it is connected to a vacuum pump. When used as a filling valve, it is connected to a water tank. The pressure regulating valve 120 is connected to a high-pressure gas tank, and the high-pressure gas tank may be filled with liquid nitrogen.

[0035] It also includes a flow meter 15, which is a Coriolis flow meter, and is arranged at the input end of the first heat exchanger 8; it ensures that the pipeline between the high-temperature heat exchanger and the condenser (cooling heat exchanger) is filled with water; it can withstand a high temperature of 280°C, has a design pressure of 6.5Mpa, a flow range of 25-250L / h, an accuracy of 1% full scale, and a diameter of DN15;

[0036] It also includes a safety valve 21 and a first pressure sensor 22. The upper end of the liquid reservoir 2 is provided with a safety valve 21 and a first pressure sensor 22. The liquid reservoir 2 (liquid storage tank) plays a role of safety protection and pressure regulation. The safety valve on the liquid reservoir automatically releases the pressure when the pressure is higher than 4MPA. The lower outlet of the temperature-controlled liquid reservoir (liquid reservoir 2) is connected to the fluid circuit through a pipeline. The upper part of the liquid reservoir is designed with a filling interface, a vacuum interface, and a safety valve interface. The liquid reservoir is made of 316 stainless steel or titanium alloy and welded. The volume of the liquid reservoir is 5L, the working temperature is 20℃~250℃, the pressure requirement of the liquid reservoir is 6.5MPa, and the leakage rate of the liquid reservoir is not more than 1x10-Pa·m' / s. The liquid reservoir has temperature measurement, pressure measurement, heating and temperature control measures, and the temperature control power is <3.0kW.

[0037] It also includes a detection valve 16, one end of which is connected to the input end of the tested object 13, and the detection valve 16 is used as a vacuum valve or a filling valve. When used as a vacuum valve, the other end is connected to a vacuum pump, and when used as a filling valve, it is connected to a water tank;

[0038] It also includes a filter 14, a sixth valve 9, a second heat exchanger 10, and an output end of the first valve 3 connected to one end of the filter 14, and an input end of the mechanical pump 4 and the third valve 6 connected to the other end of the filter 14; the inlet and outlet of the filter are connected to the pipeline of the fluid circuit by a ferrule or a plunger joint; the basic parameters of the filter are as follows: the filter end cover and the shell are made of 00Cr17Ni14M02 (316L) or titanium alloy processed and welded, the filter element assembly is made of 022Cr17Ni12M02 stainless steel wire mesh, and the filtration accuracy of the filter element is better than 50um; the design pressure of the filter is 6.5MPa; the filter leakage rate is not more than 1X10 -7 Pa·m 3 / s

[0039] The input and output ends of the liquid reservoir 2 are respectively provided with a first temperature sensor and a second temperature sensor, the input end of the filter 14 is provided with a second pressure sensor, the third pressure sensor, the mechanical pump 4, the second valve 5, and the fourth pressure sensor are connected in series in parallel with the first valve 3, one end of the measured object 13 is sequentially provided with a third temperature sensor and a fifth pressure sensor, the other end of the measured object 13 is sequentially provided with a fourth temperature sensor and a sixth pressure sensor, the two ends of the first heat exchanger 8 are respectively provided with a fifth temperature sensor and a sixth temperature sensor, the sixth valve 9 and the second heat exchanger 10 are respectively provided with a seventh temperature sensor and an eighth temperature sensor for detecting temperature and pressure, the system design pressure is 6.5MPa, the heat transfer capacity is>6kW, the working temperature of all pressure sensors is up to 300℃, the range is 0~7.0MPa, the accuracy is 0.1% full scale, and the leakage rate is not more than 1×10 -7 Pa·m 3 / s, all temperature sensors have a range of 0 to 300°C, and an accuracy better than ±0.5°C;

[0040] The connection with the pump and valve products is connected by a hose. The space can be used to secure the pump and valve components and each stand-alone product. The interface is a 60° ball head sealing joint. The joint form is as shown in the figure below. The product end is equipped with a ball head (such as Figure 2 and 3 ), the interface at the test equipment end is a spherical cone structure (such as Figure 4 ); 60° ball head sealing joint, outer nut, welding nozzle type is shown in the figure below, the interface size is DN12, for specific dimensions, see Q / Y 945.10-2018 "60° Spherical Pipe Connector Ball Joint", Q / Y

[0041] 945.12-2018 "60° Spherical Pipe Connector Jacket Nut", Q / Y 945.7-2018 "60° Spherical Pipe Connector Welding Nozzle", have a high degree of standardization, the tested parts can be disassembled and replaced, and effective high-temperature testing of various tested parts 13 can be achieved. The structural design is reasonable, easy to operate and control costs, and has good adaptability.

[0042] Specific implementation method 2: Combination Figure 1 The present embodiment is described. The present embodiment is a method for testing the performance of a two-phase fluid circuit pump and valve assembly in a spacecraft, characterized in that: a system for testing the performance of a two-phase fluid circuit pump and valve assembly in a spacecraft (hereinafter referred to as the system) is used, comprising a valve group 1, a liquid reservoir 2, a first valve 3, a mechanical pump 4, a second valve 5, a third valve 6, a flow regulating valve 7, a first heat exchanger 8, a sixth valve 9, a fourth valve 11 and a fifth valve 12. The valve group 1, the liquid reservoir 2, the first valve 3, the mechanical pump 4, the second valve 5, the flow regulating valve 7, the first heat exchanger 8, the sixth valve 9, the fourth valve 11 and the fifth valve 12 The heat exchanger 8 and one end of the sixth valve 9 are connected in sequence, the other end of the sixth valve 9 is connected to the mechanical pump 4, one end of the third valve 6 is connected to the input end of the mechanical pump 4, that is, the mechanical pump 4, the second valve 5 and the third valve 6 connected in series are connected in parallel, the other end of the third valve 6 is connected to the output end of the second valve 5, the two ends of the flow control valve 7 are respectively connected to one end of the fourth valve 11 and the fifth valve 12, the other ends of the fourth valve 11 and the fifth valve 12 are connected to the measured object 13, that is, the fourth valve 11, the measured object 13, the fifth valve 12 and the flow control valve 7 connected in series are connected in parallel;

[0043] It also includes a second heat exchanger 10, one end of the second heat exchanger 10 is connected to the output end of the first heat exchanger 8, and the other end of the second heat exchanger 10 is connected to the input end of the mechanical pump 4, that is, the second heat exchanger 10 is connected in parallel with the sixth valve 9;

[0044] The first heat exchanger 8 is a high-temperature heat exchanger, and the second heat exchanger 10 is a cooling heat exchanger, which are used for heating and cooling respectively;

[0045] The valve group 1 includes a valve 110 and a pressure regulating valve 120. Both the valve 110 and the pressure regulating valve 120 are connected to the input end of the liquid reservoir 2. The valve 110 is used as a vacuum valve or a filling valve. When used as a vacuum valve, it is connected to a vacuum pump. When used as a filling valve, it is connected to a water tank. The pressure regulating valve 120 is connected to a high-pressure gas tank, and the high-pressure gas tank may be filled with liquid nitrogen.

[0046] It also includes a flow meter 15, which is a Coriolis flow meter, and the flow meter 15 is arranged at the input end of the first heat exchanger 8; ensure that the pipeline between the high-temperature heat exchanger and the condenser (cooling heat exchanger) is filled with water;

[0047] It also includes a safety valve 21 and a first pressure sensor 22. The upper end of the liquid reservoir 2 is provided with a safety valve 21 and a first pressure sensor 22. The liquid reservoir 2 (liquid storage tank) plays a role of safety protection and pressure regulation. When the pressure is higher than 4MPA, the safety valve on the liquid reservoir automatically releases the pressure.

[0048] It also includes a detection valve 16, one end of which is connected to the input end of the tested object 13, and the detection valve 16 is used as a vacuum valve or a filling valve. When used as a vacuum valve, the other end is connected to a vacuum pump, and when used as a filling valve, it is connected to a water tank;

[0049] It also includes a filter 14, the sixth valve 9, the second heat exchanger 10, and the output end of the first valve 3 are connected to one end of the filter 14, and the input end of the mechanical pump 4 and the third valve 6 are connected to the other end of the filter 14;

[0050] The input end and the output end of the liquid storage device 2 are respectively provided with a first temperature sensor and a second temperature sensor, the input end of the filter 14 is provided with a second pressure sensor, the third pressure sensor, the mechanical pump 4, the second valve 5, and the fourth pressure sensor are connected in series in parallel with the first valve 3, one end of the measured object 13 is sequentially provided with a third temperature sensor and a fifth pressure sensor, the other end of the measured object 13 is sequentially provided with a fourth temperature sensor and a sixth pressure sensor, the two ends of the first heat exchanger 8 are respectively provided with a fifth temperature sensor and a sixth temperature sensor, the sixth valve 9, the second valve 10, and the second valve 11 are connected in parallel. The heat exchanger 10 is provided with a seventh temperature sensor and an eighth temperature sensor at both ends thereof, respectively, for detecting temperature and pressure; the tested piece 13 is connected to a pipeline of a spacecraft two-phase fluid circuit pump valve assembly performance test system through an interface, and the tested piece 13 is connected to a third temperature sensor and a fourth temperature sensor at both ends through an interface, and the interface is a 60° ball head sealing joint, a 60° spherical pipe connector outer sleeve nut and a 60° spherical pipe connector welding nozzle, and the tested piece 13 is a spacecraft two-phase fluid circuit pump valve assembly, including a filter, a one-way valve, a pressure sensor or a liquid addition and discharge valve;

[0051] System controls include:

[0052] 1) Power supply control;

[0053] 2) Mechanical pump start / stop;

[0054] 3) Liquid reservoir temperature control: temperature control power 3kW, temperature control accuracy ±1℃;

[0055] 4) Pressure signal acquisition: Collect pressure sensor signals, with the acquisition time interval not exceeding 2s;

[0056] 5) Temperature signal acquisition: collect all temperature values ​​with an acquisition time interval of 2s;

[0057] 6) Flow signal collection;

[0058] 7) With overpressure and overtemperature protection function;

[0059] 8) Capable of collecting, displaying and storing temperature, pressure and other data;

[0060] The method comprises the following steps:

[0061] Step 1: Before filling the system, evacuate the system first, evacuate the system through valve 110, and then fill the system with water. The water is not completely filled. It is necessary to ensure that the pipeline between the high-temperature heat exchanger and the condenser (cooling heat exchanger) is filled with water, and then close valve 110; Before filling the system, evacuate the system first, evacuate the system through valve 110, and then fill the system with water to make the water cover the heater, and ensure that the pipeline between the high-temperature heat exchanger and the condenser (cooling heat exchanger) is filled with water; For safety reasons, the entire test system cannot be completely filled with water. During the test, the position that is not filled with water is saturated steam; The reason is that the density of water at different temperatures is different, and the volume of water will expand at high temperatures. If the system pipeline is filled with water, there is no expansion in the pipeline, which is prone to safety accidents;

[0062] Step 2: close the first valve 3 and adjust the pressure in the liquid reservoir 2 (temperature control liquid reservoir) through the pressure regulating valve 120;

[0063] Step 3: Open the first valve 3, the second valve 5, and the sixth valve 9, and keep the third valve 6, the fourth valve 11, and the fifth valve 12 in a closed state. Use a commercially available high-temperature mechanical pump 4 to drive the working fluid to flow in the loop. Use the first heat exchanger 8 to heat the working fluid to a specified temperature. If the temperature exceeds the specified temperature, close the sixth valve 9 to lower the temperature to the specified test temperature. This prevents the temperature from being too high, which may lead to a decrease in detection accuracy and detection failure, without the need to restart or shut down for waiting. The working fluid is deionized water, and the operating temperature is 20°C to 280°C.

[0064] Step 4: The second valve 5 is closed, the first valve 3, the third valve 6, the fourth valve 11, the fifth valve 12, and the sixth valve 9 are opened, the flow rate of the pipeline is adjusted using the flow regulating valve 7, and the performance test of the tested component 13 (the tested high-temperature pump) is performed at a specified temperature;

[0065] Or the third valve 6 is closed, the first valve 3, the second valve 5, the fourth valve 11, the fifth valve 12, and the sixth valve 9 are opened, the flow regulating valve 7 is used to adjust the pipeline flow, and the performance test of the component under test is performed at a specified temperature.

[0066] It should be noted that in the above embodiments, as long as the technical solutions are not contradictory, they can be arranged and combined, and those skilled in the art can exhaust all possibilities based on the mathematical knowledge of arrangement and combination. Therefore, the present invention will no longer describe the technical solutions after arrangement and combination one by one, but it should be understood that the technical solutions after arrangement and combination have been disclosed by the present invention.

[0067] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A spacecraft two-phase fluid circuit pump valve assembly performance test system, characterized by: The invention comprises a valve group (1), a liquid reservoir (2), a first valve (3), a mechanical pump (4), a second valve (5), a third valve (6), a flow regulating valve (7), a first heat exchanger (8), a sixth valve (9), a fourth valve (11) and a fifth valve (12); the valve group (1), the liquid reservoir (2), the first valve (3), the mechanical pump (4), the second valve (5), the flow regulating valve (7), the first heat exchanger (8) and the sixth valve (9) are connected in sequence; the sixth valve (9) is connected to the mechanical pump (4); one end of the third valve (6) is connected to the mechanical pump (4); the other end of the third valve (6) is connected to the second valve (5); two ends of the flow regulating valve (7) are respectively connected to the fourth valve (11) and the fifth valve (12); the fourth valve (11) and the fifth valve (12) are connected to the tested object (13).

2. A spacecraft two-phase fluid circuit pump valve assembly performance test system according to claim 1, characterized in that: It also includes a second heat exchanger (10), one end of the second heat exchanger (10) is connected to the first heat exchanger (8), and the other end of the second heat exchanger (10) is connected to the mechanical pump (4).

3. A spacecraft two-phase fluid circuit pump valve assembly performance test system according to claim 2, characterized in that: The first heat exchanger (8) is a high-temperature heat exchanger, and the second heat exchanger (10) is a cooling heat exchanger.

4. A spacecraft two-phase fluid circuit pump valve assembly performance test system according to claim 2, characterized in that: The valve group (1) comprises a valve (110) and a pressure regulating valve (120); the valve (110) and the pressure regulating valve (120) are both connected to the input end of the liquid storage device (2); and the valve (110) is used as a vacuum valve or a filling valve.

5. A spacecraft two-phase fluid circuit pump valve assembly performance test system according to claim 4, characterized in that: It also includes a flow meter (15), which is arranged at the input end of the first heat exchanger (8).

6. A spacecraft two-phase fluid circuit pump valve assembly performance test system according to claim 5, characterized in that: It also comprises a safety valve (21) and a first pressure sensor (22). The upper end of the liquid storage container (2) is provided with the safety valve (21) and the first pressure sensor (22).

7. A spacecraft two-phase fluid circuit pump valve assembly performance test system according to claim 6, characterized in that: It also comprises a detection valve (16), which is connected to the tested object (13), and the detection valve (16) is used as a vacuum valve or a filling valve.

8. A spacecraft two-phase fluid circuit pump valve assembly performance test system according to claim 7, characterized in that: It also includes a filter (14), a sixth valve (9), a second heat exchanger (10), and a first valve (3) connected to one end of the filter (14), and a mechanical pump (4) and a third valve (6) connected to the other end of the filter (14).

9. A spacecraft two-phase fluid circuit pump valve assembly performance test system according to claim 8, characterized in that: The input end and output end of the liquid storage device (2) are respectively provided with a first temperature sensor and a second temperature sensor, the input end of the filter (14) is provided with a second pressure sensor, a third pressure sensor, a mechanical pump (4), a second valve (5), and a fourth pressure sensor are sequentially connected in series and connected in parallel with the first valve (3), one end of the tested object (13) is sequentially provided with a third temperature sensor and a fifth pressure sensor, the other end of the tested object (13) is sequentially provided with a fourth temperature sensor and a sixth pressure sensor, the two ends of the first heat exchanger (8) are respectively provided with a fifth temperature sensor and a sixth temperature sensor, and the two ends of the parallel sixth valve (9) and the second heat exchanger (10) are respectively provided with a seventh temperature sensor and an eighth temperature sensor, for detecting temperature and pressure.

10. A method for testing the performance of a two-phase fluid circuit pump and valve assembly in a spacecraft, characterized in that: A spacecraft two-phase fluid circuit pump valve assembly performance test system according to any one of claims 1 to 9 comprises the following steps: Step 1: Before filling the system, evacuate the system through valve (110), and then fill the system with water. The water is not completely filled. It is necessary to ensure that the pipeline between the high-temperature heat exchanger and the condenser is filled with water, and then close the valve (110); Step 2: closing the first valve (3) and adjusting the pressure in the liquid storage container (2) through the pressure regulating valve (120); Step 3: Open the first valve (3), the second valve (5), and the sixth valve (9), and keep the third valve (6), the fourth valve (11), and the fifth valve (12) in a closed state, use the mechanical pump (4) to drive the working fluid to flow in the loop, use the first heat exchanger (8) to heat the working fluid to a specified temperature, and if the temperature exceeds the specified temperature, close the sixth valve (9) to reduce the temperature to the specified test temperature; Step 4: The second valve (5) is closed, the first valve (3), the third valve (6), the fourth valve (11), the fifth valve (12), and the sixth valve (9) are opened, the flow rate of the pipeline is adjusted using the flow control valve (7), and the performance test of the tested component (13) is performed at a specified temperature; The third valve (6) is closed, the first valve (3), the second valve (5), the fourth valve (11), the fifth valve (12) and the sixth valve (9) are opened, the flow rate of the pipeline is adjusted using the flow regulating valve (7), and the performance test of the component under test is performed at a specified temperature.

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