CN116046377A - Rocket oxygen safety valve opening and closing performance test system and test method - Google Patents
Rocket oxygen safety valve opening and closing performance test system and test method Download PDFInfo
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- CN116046377A CN116046377A CN202211722646.1A CN202211722646A CN116046377A CN 116046377 A CN116046377 A CN 116046377A CN 202211722646 A CN202211722646 A CN 202211722646A CN 116046377 A CN116046377 A CN 116046377A
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- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 title claims abstract description 159
- 239000001301 oxygen Substances 0.000 title claims abstract description 159
- 229910052760 oxygen Inorganic materials 0.000 title claims abstract description 159
- 238000011056 performance test Methods 0.000 title claims abstract description 144
- 238000010998 test method Methods 0.000 title abstract description 3
- 238000012360 testing method Methods 0.000 claims abstract description 199
- 239000007788 liquid Substances 0.000 claims abstract description 112
- 239000007789 gas Substances 0.000 claims abstract description 92
- 230000001105 regulatory effect Effects 0.000 claims abstract description 88
- 238000000034 method Methods 0.000 claims abstract description 52
- 238000003860 storage Methods 0.000 claims abstract description 34
- 238000001816 cooling Methods 0.000 claims abstract description 13
- 238000010438 heat treatment Methods 0.000 claims abstract description 11
- 238000001514 detection method Methods 0.000 claims description 24
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims description 22
- 230000001276 controlling effect Effects 0.000 claims description 12
- 238000000605 extraction Methods 0.000 claims description 11
- 229910052757 nitrogen Inorganic materials 0.000 claims description 11
- 238000004364 calculation method Methods 0.000 claims description 10
- 239000008367 deionised water Substances 0.000 claims description 10
- 229910021641 deionized water Inorganic materials 0.000 claims description 10
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Chemical compound O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 10
- 230000001133 acceleration Effects 0.000 claims description 5
- 239000011148 porous material Substances 0.000 claims description 5
- 238000004891 communication Methods 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 7
- 239000001307 helium Substances 0.000 description 25
- 229910052734 helium Inorganic materials 0.000 description 25
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 25
- 238000010586 diagram Methods 0.000 description 13
- 238000004088 simulation Methods 0.000 description 5
- 239000003638 chemical reducing agent Substances 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000007599 discharging Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 239000004973 liquid crystal related substance Substances 0.000 description 2
- 238000005086 pumping Methods 0.000 description 2
- 238000010792 warming Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/003—Machine valves
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The embodiment of the invention provides a rocket oxygen safety valve opening and closing performance test system and a test method, wherein the rocket oxygen safety valve opening and closing performance test system comprises: the test tank comprises an upper test tank air pillow and a lower liquid storage tank; an oxygen safety valve communicated with the test tank air pillow; the inlet end of the pressure boosting system is communicated with the air pillow of the test tank, and the outlet end of the pressure boosting system is communicated with the air supply device and comprises a temperature regulating unit and a flow regulating device which are sequentially arranged between the inlet end and the outlet end of the pressure boosting system; the temperature regulating units comprise heating units, cooling units and conventional units which are arranged in parallel, and the three temperature regulating units can respectively perform on-off performance tests of three different states of high temperature, low temperature and normal temperature of the rocket oxygen safety valve. The rocket oxygen safety valve opening and closing performance test system and the rocket oxygen safety valve opening and closing performance test method provided by the embodiment of the invention have the advantages that the test system is simple in structure and low in manufacturing cost, and the accurate control of the flow and the temperature of the pressurized gas can be realized.
Description
Technical Field
The invention relates to the technical field of rocket oxygen safety valve performance test, in particular to a rocket oxygen safety valve opening and closing performance test system and a rocket oxygen safety valve opening and closing performance test method.
Background
The oxygen safety valve is one of the key single machines of the carrier rocket, and is mainly used for protecting the pressure-bearing safety of the low-temperature storage tank in the rocket launching preparation process and the rocket flight process. As an important single point of failure of the carrier rocket, the high accuracy and the opening and closing performance of the oxygen safety valve are important attention indexes of product design. However, during the use process of the oxygen safety valve, the phenomenon that the opening pressure and the closing pressure of the oxygen safety valve are abnormally low and high can occur occasionally; therefore, the qualification rate and the reliability of the oxygen safety valve are required to be improved through a large number of ground oxygen safety valve opening and closing performance test verification.
In the process of implementing the present invention, the inventor finds that at least the following problems exist in the prior art: the existing liquid rocket oxygen safety valve opening and closing performance test system cannot realize the accurate control of the flow and the temperature of the pressurized gas, so that not only is the experimental result influenced, but also an error conclusion can be obtained through the test, and test data with deviation are brought to a designer. The existing oxygen safety valve opening and closing performance test system is complex in structure and large in number of parts, so that the oxygen safety valve opening and closing performance test is high in design, research and development, processing and production cost and the like. Meanwhile, the complex test system makes the test process complex, the uncertainty factor increases, the problems of test failure, error and the like are easy to occur, and the accuracy and reliability of the test result are seriously affected.
Disclosure of Invention
In view of the above, the embodiment of the invention aims to provide a rocket oxygen safety valve opening and closing performance test system and a rocket oxygen safety valve opening and closing performance test method, so as to solve the problems that a test system in the prior art is complex in structure and high in manufacturing cost, and the accurate control of the flow rate and the temperature of pressurized gas cannot be realized.
In a first aspect, an embodiment of the present invention provides a rocket oxygen safety valve opening and closing performance test system, including:
the test tank comprises an upper test tank air pillow and a lower liquid storage tank;
an oxygen safety valve communicated with the test tank air pillow;
the inlet end of the pressure boosting system is communicated with the air pillow of the test tank, and the outlet end of the pressure boosting system is communicated with the air supply device and comprises a temperature regulating unit and a flow regulating device which are sequentially arranged between the inlet end and the outlet end of the pressure boosting system; the temperature regulating units comprise heating units, cooling units and conventional units which are arranged in parallel, and the three temperature regulating units can respectively perform on-off performance tests of three different states of high temperature, low temperature and normal temperature of the rocket oxygen safety valve.
Further, the flow regulating device comprises a first regulating device, a second regulating device and a third regulating device which are arranged in parallel; the first regulating device comprises a first electromagnetic regulating valve and a second electromagnetic regulating valve which are connected in series; the second regulating device comprises a first pressurizing electromagnetic valve and a first pressurizing pore plate which are connected in series; the third adjusting device comprises a second pressurizing electromagnetic valve and a second pressurizing pore plate which are connected in series.
Further, the supercharging system further comprises a flowmeter, a first temperature sensor and a test controller, wherein the flowmeter and the first temperature sensor are respectively arranged on a pipeline between the temperature regulating unit and the flow regulating device, and the test controller is respectively electrically connected with the flowmeter, the first temperature sensor, the first electromagnetic regulating valve and the second electromagnetic regulating valve.
Further, the heating unit comprises a first pressurizing switch, a first warmer, a second warmer and a second pressurizing switch which are sequentially arranged from the inlet end of the pressurizing system to the outlet end of the pressurizing system;
the cooling unit comprises a third supercharging switch, a first cooler, a second cooler and a fourth supercharging switch which are sequentially arranged from the inlet end of the supercharging system to the outlet end of the supercharging system;
the conventional unit includes a fifth boost switch.
Further, the rocket oxygen safety valve opening and closing performance test system further comprises a liquid filling pump controller, a first pressure sensor and a second pressure sensor, wherein the first pressure sensor and the second pressure sensor are electrically connected with the liquid filling pump controller, the first pressure sensor is used for detecting the pressure in the test tank air pillow, and the second pressure sensor is used for detecting the pressure in the liquid storage tank of the test tank.
Further, the rocket oxygen safety valve opening and closing performance test system further comprises a filling device, the filling device comprises a filling tank and an extracting device, an inlet of the extracting device is communicated with an outlet of the filling tank, an outlet of the extracting device is communicated with an inlet of a liquid storage tank of the test tank, and the extracting device is electrically connected with the liquid filling pump controller.
Further, the liquid filling pump controller is used for calculating the liquid level height of the liquid in the liquid storage tank of the test tank and controlling the on-off of the extraction device according to the liquid level height calculation result; the calculation formula of the liquid level height is as follows:
wherein P1 is the pressure in the test tank air pillow detected by the first pressure sensor; p2 is the pressure in the liquid storage tank of the test tank detected by a second pressure sensor; ρ is the liquid density in the liquid reservoir of the test tank; g is gravitational acceleration.
Further, the test controller is used for controlling the opening degree of the first electromagnetic regulating valve and the opening degree of the second electromagnetic regulating valve according to different preset flow ranges when the rocket oxygen safety valve opening and closing performance test is carried out, so that the gas flow of the pressurizing system reaches the preset flow range.
Further, the test controller is configured to receive a temperature detection result of the first temperature sensor and compare the temperature detection result with a preset temperature range when performing a rocket oxygen safety valve performance test with Wen Qibi, and when the temperature detection result is within the preset temperature range, no operation is required, and when the temperature detection result is outside the preset temperature range, perform coarse adjustment on the system temperature by adjusting the first heater, and then perform fine adjustment on the system temperature by adjusting the second heater, so that the system temperature is within the preset temperature range;
the test controller is further used for receiving a temperature detection result of the first temperature sensor and comparing the temperature detection result with a preset temperature range when the rocket oxygen safety valve low-temperature start-stop performance test is carried out, operation is not needed when the temperature detection result is in the preset temperature range, the system temperature is coarsely regulated by regulating the first cooler when the temperature detection result is out of the preset temperature range, and the system temperature is finely regulated by regulating the second cooler, so that the system temperature is in the preset temperature range.
In a second aspect, the embodiment of the invention provides a rocket oxygen safety valve opening and closing performance test method, which is used for the rocket oxygen safety valve opening and closing performance test system, wherein the rocket oxygen safety valve opening and closing performance test method comprises a rocket oxygen safety valve high Wen Qibi performance test method, a rocket oxygen safety valve low-temperature opening and closing performance test method and a rocket oxygen safety valve normal-temperature opening and closing performance test method;
the rocket oxygen safety valve high Wen Qibi performance test method comprises the following steps: filling deionized water into a liquid storage tank of the test tank to a preset liquid level; respectively setting preset ranges of gas temperature and gas flow, and adjusting the gas temperature and the gas flow in the heating unit to enable the gas temperature and the gas flow to reach the preset ranges, and then pressurizing the test tank air pillow; performing a high-temperature start-stop performance test; after changing the preset range value according to actual needs, re-pressurizing the test tank air pillow, and then performing a high-temperature start-stop performance test again until the rocket oxygen safety valve high Wen Qibi performance test is finished;
the rocket oxygen safety valve low-temperature opening and closing performance test method comprises the following steps: filling liquid nitrogen into a liquid storage tank of the test tank to reach a preset liquid level; respectively setting preset ranges of gas temperature and gas flow, and adjusting the gas temperature and the gas flow in the cooling unit to enable the gas temperature and the gas flow to reach the preset ranges, and then pressurizing the test tank air pillow; performing a low-temperature start-stop performance test; the low-temperature start-stop performance test is carried out again after the air pillow of the test tank is pressurized again after the preset range value is changed according to actual requirements, and the low-temperature start-stop performance test of the rocket oxygen safety valve is finished;
The rocket oxygen safety valve normal temperature opening and closing performance test method comprises the following steps: filling deionized water into a liquid storage tank of the test tank to a preset liquid level; setting a preset range of gas flow, and adjusting the gas flow in the conventional unit to enable the gas flow to reach the preset range, and then pressurizing the test tank gas pillow; performing a normal temperature start-stop performance test; and after changing the preset range value according to actual needs, re-pressurizing the test tank air pillow, and then performing a normal-temperature start-stop performance test again until the normal-temperature start-stop performance test of the rocket oxygen safety valve is finished.
The technical scheme has the following beneficial effects: the rocket oxygen safety valve opening and closing performance test system can be used for pressurizing the test tank air pillow through the pressurizing system, and the pressurizing system comprises the temperature adjusting unit and the flow adjusting device, so that the temperature and the flow of the system can be adjusted when the rocket oxygen safety valve is subjected to opening and closing performance test, and the influence of different temperatures and flows on the opening and closing performance of the oxygen safety valve can be determined. The temperature regulating unit comprises a heating unit, a cooling unit and a conventional unit, and the three temperature regulating units can respectively perform on-off performance tests of three different states of high temperature, low temperature and normal temperature of the rocket oxygen safety valve. The rocket oxygen safety valve opening and closing performance test system provided by the embodiment of the invention has the advantages of simple structure, complete functions, simple and reliable rocket oxygen safety valve opening and closing performance test method and high accuracy.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a rocket oxygen relief valve opening and closing performance test system according to one embodiment of the present invention;
FIG. 2 is a schematic diagram of a rocket oxygen relief valve opening and closing performance test system according to another embodiment of the present invention;
FIG. 3 is a flow control logic diagram of a rocket oxygen relief valve opening and closing performance test method according to an embodiment of the present invention;
FIG. 4 is a temperature control logic diagram of a rocket oxygen relief valve opening and closing performance test method according to an embodiment of the present invention;
FIG. 5A is a flow control logic diagram of a rocket oxygen relief valve height Wen Qibi performance test method according to an embodiment of the present invention;
FIG. 5B is a flow control logic diagram of a rocket oxygen relief valve low temperature opening and closing performance test method according to an embodiment of the present invention;
FIG. 5C is a flow control logic diagram of a rocket oxygen relief valve normal temperature opening and closing performance test method according to an embodiment of the invention;
FIG. 6 is an AMESIM simulation diagram of a rocket oxygen relief valve opening and closing performance test system according to an embodiment of the present invention;
FIG. 7 is a graph of rocket oxygen relief valve opening pressure, closing pressure, and test tank relief valve pressure profiles in accordance with an embodiment of the present invention;
FIG. 8 is a schematic diagram of a rocket oxygen safety valve opening and closing performance test result when a small flow of pressurizing gas is adopted for pressurizing in the rocket oxygen safety valve opening and closing performance test method according to the embodiment of the invention;
FIG. 9 is a schematic diagram of a rocket oxygen relief valve opening and closing performance test result when a large flow of pressurized gas is used for pressurization in the rocket oxygen relief valve opening and closing performance test method according to the embodiment of the invention.
Reference numerals illustrate:
1. a test tank; 2. an oxygen safety valve; 3. a filling tank; 4. a flow rate adjusting device; 5. a test controller; 6. a liquid filling pump controller; 7. a temperature adjusting unit; 8. a filter; 10. a pressure reducer; 11. air pillow of test tank; 12. a liquid reservoir; 13. a test tank safety valve; 14. an inflation switch of the test tank; 15. a test tank pressurizing port; 16. a fourth temperature sensor; 17. a test canister bleed valve; 18. a test tank filling valve; 31. filling a tank air pillow; 32. filling the storage tank; 33. a charging port of the charging tank; 34. a filling tank safety valve; 35. a filling tank inflation switch; 36. extraction means; 361. a pump motor; 362. a liquid pump; 37. an orifice plate; 38. an electromagnetic valve; 41. a second electromagnetic regulating valve; 42. a first electromagnetic regulating valve; 43. a first pressurizing aperture plate; 44. a second pressurizing aperture plate; 45. a first boost solenoid valve; 46. a second boost solenoid valve; 51. a flow meter; 52. a first temperature sensor; 53. a third temperature sensor; 54. a second temperature sensor; 61. a second pressure sensor; 62. a first pressure sensor; 71. a first boost switch; 72. a first warmer; 73. a second warmer; 74. a second boost switch; 75. a third boost switch; 76. a first desuperheater; 77. a fourth boost switch; 78. a second desuperheater; 79. a liquid nitrogen tank; 710. a fifth boost switch; 91. a first test tank inflation solenoid valve; 92. a second test tank inflation solenoid valve; 100. a helium source; 200. a nitrogen source.
Detailed Description
Features and exemplary embodiments of various aspects of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by showing examples of the invention. In the drawings and the following description, at least some well-known structures and techniques have not been shown in detail in order not to unnecessarily obscure the present invention; also, the dimensions of some of the structures may be exaggerated for clarity. Furthermore, the described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.
As shown in fig. 1 and fig. 2, the rocket oxygen safety valve 2 opening and closing performance test system according to the embodiment of the invention includes: a test tank 1, an oxygen relief valve 2 and a pressurization system.
The test tank 1 comprises a test tank air pillow 11 at the upper part and a liquid storage tank 12 at the lower part.
The oxygen safety valve 2 is the oxygen safety valve 2 to be tested and is communicated with the test tank air pillow 11.
The outlet end of the pressurizing system is communicated with the test tank air pillow 11, the inlet end of the pressurizing system is communicated with the air supply device, and the pressurizing system comprises a temperature regulating unit 7 and a flow regulating device 4 which are sequentially arranged between the inlet end and the outlet end of the pressurizing system; the temperature adjusting unit 7 includes a warming unit, a cooling unit, and a conventional unit arranged in parallel.
The test tank air pillow 11 is used for filling pressurized gas, and the liquid storage tank 12 is used for filling test liquid. The test tank air pillow 11 is provided with a test tank pressurizing port 15, and is also respectively communicated with a test tank inflation switch 14 and a test tank safety valve 13 through pipelines. The bottom of the liquid storage tank 12 is respectively communicated with a test tank filling valve 18 and a test tank discharging valve 17 through pipelines, liquid is filled into the liquid storage tank 12 through the test tank filling valve 18, and the liquid is discharged out of the liquid storage tank 12 through the test tank discharging valve 17.
The flow regulating device 4 comprises a first regulating device, a second regulating device and a third regulating device which are arranged in parallel; the first regulating device comprises a first electromagnetic regulating valve 42 and a second electromagnetic regulating valve 41 which are connected in series; the second regulating device comprises a first pressurizing electromagnetic valve 45 and a first pressurizing pore plate 43 which are connected in series; the third regulating means comprises a second pressurizing solenoid valve 46 and a second pressurizing aperture plate 44 in series.
A filter 8 is also provided in this embodiment before the inlet of the flow regulating device 4. The first booster solenoid valve 45 and the second booster solenoid valve 46 include only two states of opening and closing, and the first solenoid valve 42 and the second solenoid valve 41 can adjust the flow rate by changing the opening degree in addition to the two states of opening and closing. The second adjusting device and the third adjusting device are used for adjusting the flow of the pressurized gas by replacing the first pressurizing orifice plate 43 or the second pressurizing orifice plate 44 with different specifications, or by opening or closing the first pressurizing electromagnetic valve 45 or the second pressurizing electromagnetic valve 46 to adjust the flow of the pressurized gas, so as to study the influence of different flows of the pressurized gas on the opening pressure and the closing pressure of the oxygen safety valve 2.
The supercharging system further comprises a flow meter 51, a first temperature sensor 52 and a test controller 5, wherein the flow meter 51 and the first temperature sensor 52 are respectively arranged on a pipeline between the temperature regulating unit 7 and the flow regulating device 4, and the test controller 5 is respectively electrically connected with the flow meter 51, the first temperature sensor 52, the first electromagnetic regulating valve 42 and the second electromagnetic regulating valve 41.
The first temperature sensor 52 is used to measure the temperature of the pressurized gas in the system. The test controller 5 is configured to control the opening of the first electromagnetic regulating valve 42 and the second electromagnetic regulating valve 41 according to different preset flow ranges when performing the opening and closing performance test of the rocket oxygen safety valve 2, so that the gas flow of the pressurization system reaches the preset flow range, and the influence of different pressurization flows on the opening pressure and the closing pressure of the oxygen safety valve 2 is studied.
The heating unit comprises a first supercharging switch 71, a first heater 72, a second heater 73 and a second supercharging switch 74 which are sequentially arranged from the inlet end of the supercharging system to the outlet end of the supercharging system; the cooling unit comprises a third supercharging switch 75, a first cooler 76, a second cooler 78 and a fourth supercharging switch 77 which are sequentially arranged from the inlet end of the supercharging system to the outlet end of the supercharging system; the conventional unit includes a fifth boost switch 710.
Specifically, in the present embodiment, the warming unit is further provided with a second temperature sensor 54 between the first warmer 72 and the second warmer 73. The cooling unit is also provided with a second temperature sensor 54 between the first cooler 76 and the second cooler 78, and the first cooler 76 and the second cooler 78 are respectively arranged in the corresponding liquid nitrogen tanks 79. The pressurizing system is further provided with a third temperature sensor 53 in front of the inlet of the temperature adjusting unit 7, and the arrangement of a plurality of temperature sensors is beneficial to accurately controlling the temperature of the pressurizing gas in the pressurizing system. A filter 8 and a pressure reducer 10 are also provided in this order at the inlet end of the pressurization system, and the inlet end is in communication with a helium source 100. The pressurizing gas in the embodiment is helium, and the helium is inflated into the test tank air pillow 11 after being heated by the heating unit so as to perform a high-temperature opening and closing performance test of the rocket oxygen safety valve 2; the helium is cooled by the cooling unit and then is inflated into the test tank air pillow 11 so as to perform a low-temperature start-stop performance test of the rocket oxygen safety valve 2; helium is directly inflated into the test tank air pillow 11 through a conventional unit so as to perform a normal-temperature start-stop performance test of the rocket oxygen safety valve 2. The three temperature regulating units 7 are arranged in parallel, so that the rocket oxygen safety valve has few types of parts and simple structure, is convenient for the start-stop performance test of each state of the rocket oxygen safety valve 2, and reduces the production input cost of the whole equipment.
In this embodiment, a first test tank charging solenoid valve 91 is also provided between the flow regulator 4 and the test tank pressurizing port 15, and a second test tank charging solenoid valve 92 is also provided after the outlet of the flow regulator 4. After the first test tank charging electromagnetic valve 91 is opened and the second test tank charging electromagnetic valve 92 is closed, the pressurized gas in the pressurizing system can be charged into the test tank air pillow 11; after the second test tank charging electromagnetic valve 92 is opened and the first test tank charging electromagnetic valve 91 is closed, the pressurized gas in the pressurizing system is directly discharged into the surrounding environment for debugging before the start-stop performance test of the rocket oxygen safety valve 2, such as debugging the flow and the temperature of the pressurized gas, and after the preset requirement is met, the inflating operation is performed in the test tank air pillow 11.
The rocket oxygen safety valve 2 opening and closing performance test system further comprises a liquid filling pump controller 6, a first pressure sensor 62 and a second pressure sensor 61 which are electrically connected with the liquid filling pump controller 6, wherein the first pressure sensor 62 is used for detecting the pressure in the test tank air pillow 11, and the second pressure sensor 61 is used for detecting the pressure in the liquid storage tank 12 of the test tank 1.
The first pressure sensor 62 detects the liquid pressure in the liquid storage tank 12 of the test tank 1 in real time, and the second pressure sensor 61 detects the gas pressure in the test tank air pillow 11 in real time, and the liquid level of the liquid storage tank 12 of the test tank 1 is obtained through calculation according to the ratio of the pressure difference of the two pressure sensors to the liquid density and the gravity acceleration. The input cost of the liquid level sensor is saved, the problem of measurement error caused by the liquid level sensor when liquid shakes is avoided, and the stability of the whole system is improved.
The rocket oxygen safety valve 2 opening and closing performance test system further comprises a filling device, the filling device comprises a filling tank 3 and an extraction device 36, an inlet of the extraction device 36 is communicated with an outlet of the filling tank 3, an outlet of the extraction device 36 is communicated with an inlet of the liquid storage tank 12 of the test tank 1, and the extraction device 36 is electrically connected with the liquid filling pump controller 6.
The filling tank 3 comprises an upper filling tank air pillow 31 and a lower filling tank 32, and an outlet is arranged at the bottom of the filling tank 32 and is communicated with an inlet of the extracting device 36 for filling the test tank 1 with liquid. The filling tank air pillow 31 is provided with a filling tank pressurizing opening 33, and the nitrogen source 200 is filled into the filling tank air pillow 31 after passing through a filter 8, a pressure reducer 10, the filter 8, an electromagnetic valve 38 and an orifice plate 37 which are sequentially arranged. The filling tank air pillow 31 is also provided with a filling tank safety valve 34 and a filling tank inflation switch 35.
In this embodiment, the pumping device 36 includes a liquid pump 362 and a pump motor 361, the pump motor 361 is electrically connected to a liquid filling pump controller 6, and the liquid filling pump controller 6 is used for calculating the liquid level of the liquid in the liquid storage tank 12 of the test tank 1, and controlling the pumping device 36 to be turned on or off according to the liquid level calculation result; the calculation formula of the liquid level height is as follows:
Wherein P1 is the pressure in the test tank air pillow 11 detected by the first pressure sensor 62; p2 is the pressure in the liquid tank 12 of the test tank 1 detected by the second pressure sensor 61; ρ is the liquid density in the liquid reservoir 12 of the test tank 1; g is gravitational acceleration.
The liquid level height calculating method of the embodiment is simple and accurate, and meanwhile, the omitted liquid level meter saves certain production and manufacturing cost.
The test controller 5 is configured to receive temperature detection results of the first temperature sensor 52, the second temperature sensor 54, and the third temperature sensor 53 and compare the temperature detection results with a preset temperature range when the rocket oxygen safety valve 2 is subjected to a high-temperature start-stop performance test, and when the temperature detection results are within the preset temperature range, no operation is required, and when the temperature detection results are outside the preset temperature range, the system temperature is coarsely adjusted by adjusting the first heater 72 and is finely adjusted by adjusting the second heater 73, so that the system temperature is within the preset temperature range;
the test controller 5 is further configured to receive the temperature detection results of the first temperature sensor 52, the second temperature sensor 54, and the third temperature sensor 53 and compare the temperature detection results with a preset temperature range when the rocket oxygen safety valve 2 is subjected to a low-temperature start-stop performance test, and when the temperature detection results are within the preset temperature range, no operation is required, and when the temperature detection results are outside the preset temperature range, the system temperature is coarsely adjusted by adjusting the first cooler 76, and then finely adjusted by adjusting the second cooler 78, so that the system temperature is within the preset temperature range.
In order to make the temperature control of the whole system more accurate, a fourth temperature sensor 16 can be further arranged on the test tank air pillow 11 and used for detecting the temperature in the test tank air pillow 11 in real time.
As shown in FIG. 6, the rocket oxygen safety valve 2 opening and closing performance test system of the embodiment of the invention is simulated by an AMESIM simulation method to obtain a simulation model and a simulation method of the rocket oxygen safety valve 2 opening and closing performance test system.
As shown in fig. 3 to 5, a further embodiment of the present invention provides a method for testing the opening and closing performance of a rocket oxygen safety valve 2, which is used in the above system for testing the opening and closing performance of a rocket oxygen safety valve 2, wherein the method for testing the opening and closing performance of a rocket oxygen safety valve 2 includes a method for testing the high-temperature opening and closing performance of a rocket oxygen safety valve 2, a method for testing the low-temperature opening and closing performance of a rocket oxygen safety valve 2, and a method for testing the normal-temperature opening and closing performance of a rocket oxygen safety valve 2.
As shown in FIG. 5A, the high-temperature opening and closing performance test method of the rocket oxygen safety valve 2 comprises the following steps: filling deionized water into the liquid storage tank 12 of the test tank 1 to a preset liquid level; respectively setting preset ranges of gas temperature and gas flow, and adjusting the gas temperature and the gas flow in the heating unit to reach the preset ranges, and then pressurizing the test tank air pillow 11; performing a high-temperature start-stop performance test; and after changing the preset range value according to actual requirements, re-pressurizing the test tank air pillow 11, and then performing a high-temperature start-stop performance test again until the high-temperature start-stop performance test of the rocket oxygen safety valve 2 is finished. The specific operation is as follows:
S11, starting a test;
s12, initializing test equipment;
s13, opening an electromagnetic valve in front of a pressurizing opening 33 of the filling tank, and pressurizing a gas pillow 31 of the filling tank by using nitrogen;
s14, opening a test tank filling valve 18, filling deionized water into the test tank 1 by starting a liquid pump 362, and filling the deionized water to a preset liquid level;
s15, opening a second test tank inflation electromagnetic valve 92, closing a first test tank inflation electromagnetic valve 91, realizing coarse adjustment of helium temperature by adjusting a first heater 72, and realizing fine adjustment of helium temperature by adjusting a second heater 73;
s16, the rough adjustment of helium flow is realized by replacing the first pressurizing orifice plate 43 and the second pressurizing orifice plate 44 with different sizes, and the precise control of the helium flow is realized by controlling the opening of the first electromagnetic regulating valve 42 and the second electromagnetic regulating valve 41 through the test controller 5;
s17, closing a second test tank inflation electromagnetic valve 92, opening a first test tank inflation electromagnetic valve 91, pressurizing the test tank air pillow 11, and performing an oxygen safety valve high-temperature performance test;
s18, researching the influence of the flow and the high temperature of the helium gas on the opening and closing performance test of the oxygen safety valve by changing the flow and the temperature of the pressurized helium gas, and repeating the steps S15 to S17 until the high temperature performance test of the oxygen safety valve is finished.
As shown in fig. 5B, the method for testing the low-temperature opening and closing performance of the rocket oxygen safety valve 2 comprises the following steps: filling liquid nitrogen into the liquid storage tank 12 of the test tank 1 to a preset liquid level; respectively setting preset ranges of gas temperature and gas flow, and adjusting the gas temperature and the gas flow in the cooling unit to reach the preset ranges, and then pressurizing the test tank air pillow 11; performing a low-temperature start-stop performance test; and after changing the preset range value according to actual needs, re-pressurizing the test tank air pillow 11, and then performing the low-temperature start-stop performance test again until the low-temperature start-stop performance test of the rocket oxygen safety valve 2 is finished. The specific operation is as follows:
s21, starting a test;
s22, initializing test equipment;
s23, opening an electromagnetic valve in front of a pressurizing opening 33 of the filling tank, and pressurizing a gas pillow 31 of the filling tank by using nitrogen;
s24, opening the test tank filling valve 18, and filling liquid nitrogen into the test tank 1 by opening the liquid pump 362 to a preset liquid level;
s25, opening a second test tank inflation electromagnetic valve 92, closing a first test tank inflation electromagnetic valve 91, realizing coarse adjustment of helium temperature by adjusting the first cooler 76, and realizing fine adjustment of helium temperature by adjusting the second cooler 78;
S26, the rough adjustment of helium flow is realized by replacing the first pressurizing orifice plate 43 and the second pressurizing orifice plate 44 with different sizes, and the precise control of the helium flow is realized by controlling the opening of the first electromagnetic regulating valve 42 and the second electromagnetic regulating valve 41 through the test controller 5;
s27, closing a second test tank inflation electromagnetic valve 92, opening a first test tank inflation electromagnetic valve 91, pressurizing the test tank air pillow 11, and performing an oxygen safety valve low-temperature performance test;
s28, researching the influence of the flow and the low-temperature of the helium gas on the opening and closing performance test of the oxygen safety valve by changing the flow and the temperature of the pressurized helium gas, and repeating the steps S25 to S27 until the oxygen safety valve low-temperature performance test is finished.
As shown in fig. 5C, the normal temperature opening and closing performance test method of the rocket oxygen relief valve 2 comprises the following steps: filling deionized water into the liquid storage tank 12 of the test tank 1 to a preset liquid level; setting a preset range of gas flow, and adjusting the gas flow in the conventional unit to reach the preset range, and then pressurizing the test tank gas pillow 11; performing a normal temperature start-stop performance test; and after changing the preset range value according to actual requirements, re-pressurizing the test tank air pillow 11, and then performing the normal-temperature start-stop performance test again until the normal-temperature start-stop performance test of the rocket oxygen safety valve 2 is finished. The specific operation is as follows:
S31, starting a test;
s32, initializing test equipment;
s33, opening an electromagnetic valve in front of a pressurizing opening 33 of the filling tank, and pressurizing a gas pillow 31 of the filling tank by using nitrogen;
s34, opening the test tank filling valve 18, filling deionized water into the test tank 1 by starting the liquid pump 362, and filling the deionized water to a preset liquid level;
s35, opening a second test tank inflation electromagnetic valve 92, closing a first test tank inflation electromagnetic valve 91, closing a first booster switch 71, a second booster switch 74, a third booster switch 75 and a fourth booster switch 77, and opening a fifth booster switch 710;
s36, the rough adjustment of the helium flow is realized by replacing the first pressurizing orifice plate 43 and the second pressurizing orifice plate 44 with different sizes, and the precise control of the helium flow is realized by controlling the opening of the first electromagnetic regulating valve 42 and the second electromagnetic regulating valve 41 through the test controller 5;
s37, closing a second test tank inflation electromagnetic valve 92, opening a first test tank inflation electromagnetic valve 91, pressurizing the test tank air pillow 11, and performing an oxygen safety valve normal temperature performance test;
s28, researching the influence of helium flow on the oxygen safety valve opening and closing performance test by changing the flow of the pressurized helium, and repeating the steps S35 to S37 until the oxygen safety valve normal-temperature performance test is finished.
As shown in fig. 3, specifically, the flow control logic of the rocket oxygen safety valve 2 opening and closing performance test of the present embodiment is as follows:
after the flow control system starts to operate, the first electromagnetic regulating valve 42, the second electromagnetic regulating valve 41, the flowmeter 51 and the test controller 5 are initialized;
s1, opening a second test tank inflation electromagnetic valve 92, and detecting the flow Q of pressurized gas (helium) in a pressurizing system by a flowmeter 51 0 And sent to the test controller 5;
s2, the test controller 5 is used for controlling the flow Q of the pressurized gas 0 An operation of selecting one of the following;
s2.1, when the test controller 5 judges the flow Q of the pressurized gas 0 When the flow rate is within the preset flow rate range, calibrating the opening of the first electromagnetic regulating valve 42 and the second electromagnetic regulating valve 41, closing the second test tank inflation electromagnetic valve 92, opening the first test tank inflation electromagnetic valve 91, and performing a rocket oxygen safety valve 2 opening and closing performance test; repeating the steps S1 and S2 after changing the preset flow range value until the whole test is finished;
s2.2, when the test controller 5 judges the flow Q of the pressurized gas 0 If the flow rate is not within the preset flow rate range, further judging whether the first supercharging orifice plate 43 and the second supercharging orifice plate 44 need to be replaced, if the first supercharging orifice plate 43 and the second supercharging orifice plate 44 need to be replaced, after the first supercharging orifice plate 43 and the second supercharging orifice plate 44 are replaced, adjusting the opening and closing of the first supercharging electromagnetic valve 45 and the second supercharging electromagnetic valve 46, controlling the opening of the first electromagnetic regulating valve 42 and the second electromagnetic regulating valve 41 by using the test controller 5, and repeating the steps S1 and S2;
S2.3, when the test controller 5 judges the flow Q of the pressurized gas 0 If the flow rate is not within the preset flow rate range, it is further determined that if the first pressurization orifice plate 43 and the second pressurization orifice plate 44 do not need to be replaced, the opening and closing of the first pressurization solenoid valve 45 and the second pressurization solenoid valve 46 are adjusted, and after the opening degrees of the first electromagnetic regulating valve 42 and the second electromagnetic regulating valve 41 are controlled by the test controller 5, the steps S1 and S2 are repeated.
Wherein, the liquid crystal display device comprises a liquid crystal display device,
q m is the gas mass flow rate, kg/s; c (C) q The flow coefficient (dimensionless) of the gas through the orifice; a is that 39 Is the effective cross-sectional area of the orifice of the first pressurizing orifice plate, mm 2 ；A 41 Is the effective cross section area of the throttling mouth of the second pressurizing orifice plate, mm 2 ；p up Absolute pressure in front of the throttle openings of the first pressurizing orifice plate and the second pressurizing orifice plate is MPa, (namely, gas pressure at the first pressurizing electromagnetic valve and the second pressurizing electromagnetic valve); t (T) up The absolute temperature of the gas before the orifice of the first pressurizing orifice plate and the orifice of the second pressurizing orifice plate is K, (namely, the gas temperature at the first pressurizing electromagnetic valve and the second pressurizing electromagnetic valve); gamma is the specific heat ratio (dimensionless) of the gas; r is a gas constant J/(kg.K); a is that 42 Effective cross section of throttle mouth of first electromagnetic regulating valveArea of mm 2 ；A 43 Is the effective cross section area of the throttle orifice of the second electromagnetic regulating valve, mm 2 。
Wherein formula (1) is the case when both the first booster solenoid valve 45 and the second booster solenoid valve 46 are open; equation (2) is the case when the first booster solenoid valve 45 is open and the second booster solenoid valve 46 is closed; equation (3) is the case when the first booster solenoid valve 45 is closed and the second booster solenoid valve 46 is open; equation (4) is the case when both the first booster solenoid valve 45 and the second booster solenoid valve 46 are closed.
As shown in fig. 4, specifically, the temperature control logic of the rocket oxygen safety valve 2 opening and closing performance test of the present embodiment is as follows:
after the temperature control system starts to operate, first, the first electromagnetic control valve 42, the second electromagnetic control valve 41, the flowmeter 51, and the test controller 5 are initialized.
When the high-temperature opening and closing performance test is performed on the rocket oxygen safety valve 2, the following steps are executed:
s10, opening the second test tank charging electromagnetic valve 92, and detecting the temperature T of the pressurized gas by the first temperature sensor 52, the second temperature sensor 54 and the third temperature sensor 53 0 And sent to the test controller 5, when T 0 When the temperature is within the preset temperature range, the step S40 is continued, when T 0 When the temperature is not within the preset temperature range, the temperature of the pressurized gas is coarsely adjusted by adjusting the first heater 72, and then the temperature of the pressurized gas is finely adjusted by adjusting the second heater 73, and then the step S10 is repeated;
S40, closing the second test tank inflation electromagnetic valve 92, opening the first test tank inflation electromagnetic valve 91, and performing a start-stop performance test on the rocket oxygen safety valve 2.
When the rocket oxygen safety valve 2 is subjected to a low-temperature opening and closing performance test, the following steps are executed:
s20, opening a second test tank inflation electromagnetic valve 92, and receiving the temperature T of the pressurized gas detected by the first temperature sensor 52, the second temperature sensor 54 and the third temperature sensor 53 by the test controller 5 0 When T 0 When the temperature is within the preset temperature range, the step S40 is continued, when T 0 Not at a preset temperatureWhen the temperature is within the range, the temperature of the pressurized gas is roughly adjusted by adjusting the first cooler 76, and then the temperature of the pressurized gas is finely adjusted by adjusting the second cooler 78, and then the step S1 is repeated;
s40, closing the second test tank inflation electromagnetic valve 92, opening the first test tank inflation electromagnetic valve 91, and performing a start-stop performance test on the rocket oxygen safety valve 2.
When the rocket oxygen safety valve 2 is subjected to a normal-temperature opening and closing performance test, the following steps are executed:
s30, turning off the first boost switch 71, the second boost switch 74, the third boost switch 75 and the fourth boost switch 77, and turning on the fifth boost switch 710;
s40, closing the second test tank inflation electromagnetic valve 92, opening the first test tank inflation electromagnetic valve 91, and performing a start-stop performance test on the rocket oxygen safety valve 2.
FIG. 7 is a graph of rocket oxygen relief valve opening pressure, closing pressure, and test tank relief valve pressure profiles, wherein P max Is the opening pressure of a safety valve of the test tank, P 2 Is the opening pressure of the rocket oxygen relief valve, P 1 Is the rocket oxygen relief valve closing pressure.
FIG. 8 is a schematic diagram showing the results of the rocket oxygen safety valve opening and closing performance test when the rocket oxygen safety valve opening and closing performance test method is carried out by using a small flow of pressurizing gas according to the embodiment of the invention, wherein P 0 For testing the pressure of the air pillow of the tank, P 1 For rocket oxygen relief valve closing pressure, P 2 For rocket oxygen relief valve opening pressure, P max The pressure was opened for the test tank relief valve.
FIG. 9 is a schematic diagram showing the results of the rocket oxygen safety valve opening and closing performance test when the rocket oxygen safety valve opening and closing performance test method is carried out by using a large flow of pressurized gas according to the embodiment of the invention, wherein P 0 For testing the pressure of the air pillow of the tank, P 1 For rocket oxygen relief valve closing pressure, P 2 For rocket oxygen relief valve opening pressure, P max The pressure was opened for the test tank relief valve.
According to the rocket oxygen safety valve 2 opening and closing performance test system, coarse adjustment of the flow of the pressurized helium is achieved by replacing the first pressurizing orifice plate 43 and the second pressurizing orifice plate 44 with different sizes, fine adjustment of the flow of the pressurized helium is achieved by controlling the opening of the two first electromagnetic regulating valves 42 and the second electromagnetic regulating valves 41 which are connected in series through the test controller 5, and precise control of the flow of the pressurized gas can be achieved through the mode.
As shown in FIG. 6, the embodiment of the invention provides an AMESIM oxygen safety valve 2 experimental simulation method of a rocket oxygen safety valve 2 opening and closing performance test system, and provides a logic theory about the flow control of pressurized gas.
According to the rocket oxygen safety valve 2 opening and closing performance test system, the accurate control of the high-temperature of the pressurized gas can be realized through the two first heaters 72 and the second heaters 73 which are connected in series; accurate control of the low temperature of the pressurized gas can be achieved by two serially connected coolers 78.
The rocket oxygen safety valve 2 opening and closing performance test system provided by the embodiment of the invention can be used for carrying out opening and closing performance tests of the oxygen safety valve 2 in three different states of high temperature, normal temperature and low temperature, can realize flow customization, provides a flow control method, a calculation method and a temperature control method, and provides effective test means and methods for the opening and closing performance test of the oxygen safety valve 2.
The embodiment of the invention provides a flow logic diagram of a rocket oxygen safety valve 2 opening and closing performance test method, and provides a high-efficiency method for smooth test. According to the rocket oxygen safety valve 2 start-stop performance test system, in the process of filling liquid into the liquid storage tank 12 of the test tank 1, the filling liquid level in the liquid storage tank 12 is obtained by adopting a calculation method that the pressure difference measured by the two pressure sensors is divided by the density and the gravity acceleration, instead of adopting a traditional liquid level sensor, so that the input cost of the liquid level sensor is saved, the problem that the liquid level sensor is easy to produce measurement errors when the liquid shakes is avoided, and the accuracy of measurement data is improved. The accurate control of the filling liquid level of the liquid storage tank 12 is realized through the liquid level calculation method, so that the size of the initial air pillow space is ensured, and the actual oxygen tank initial air pillow space is simulated.
The rocket oxygen safety valve 2 opening and closing performance test system provided by the embodiment of the invention can realize the accurate control of the flow and the temperature of the pressurized gas only through the simple combination of the parts with the same structure, ensures the initial filling liquid level, meets the test requirements, and simultaneously reduces the production cost of the whole system with the same and simple part structure.
In the description of the present invention, it should be noted that the orientation or positional relationship indicated by "upper, lower, inner and outer", etc. in terms are based on the orientation or positional relationship shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or element in question must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first, second, or third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The terms "mounted, connected, and coupled" should be construed broadly in this disclosure unless otherwise specifically indicated and defined, such as: can be fixed connection, detachable connection or integral connection; it may also be a mechanical connection, an electrical connection, or a direct connection, or may be indirectly connected through an intermediate medium, or may be a communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
While the invention has been described with reference to a preferred embodiment, various modifications may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In particular, the technical features mentioned in the respective embodiments may be combined in any manner as long as there is no structural conflict. The present invention is not limited to the specific embodiments disclosed herein, but encompasses all technical solutions falling within the scope of the claims.
Claims (10)
1. The rocket oxygen relief valve opening and closing performance test system is characterized by comprising:
a test tank (1) comprising an upper test tank air pillow (11) and a lower liquid storage tank (12);
an oxygen safety valve (2) communicated with the test tank air pillow (11);
the outlet end of the pressurizing system is communicated with the test tank air pillow (11), and the inlet end of the pressurizing system is communicated with the air supply device and comprises a temperature regulating unit (7) and a flow regulating device (4) which are sequentially arranged between the inlet end and the outlet end of the pressurizing system; the temperature adjusting unit (7) comprises a heating unit, a cooling unit and a conventional unit which are arranged in parallel, and the three temperature adjusting units (7) can respectively perform opening and closing performance tests of the rocket oxygen safety valve (2) in three different states of high temperature, low temperature and normal temperature.
2. Rocket oxygen safety valve opening and closing performance test system according to claim 1, characterized in that the flow regulating device (4) comprises a first regulating device, a second regulating device and a third regulating device which are arranged in parallel; the first regulating device comprises a first electromagnetic regulating valve (42) and a second electromagnetic regulating valve (41) which are connected in series; the second regulating device comprises a first pressurizing electromagnetic valve (45) and a first pressurizing pore plate (43) which are connected in series; the third regulating device comprises a second pressurizing electromagnetic valve (46) and a second pressurizing pore plate (44) which are connected in series.
3. Rocket oxygen safety valve opening and closing performance test system according to claim 2, characterized in that the pressurization system further comprises a flowmeter (51), a first temperature sensor (52) and a test controller (5), wherein the flowmeter (51) and the first temperature sensor (52) are respectively arranged on a pipeline between the temperature regulating unit (7) and the flow regulating device (4), and the test controller (5) is respectively electrically connected with the flowmeter (51), the first temperature sensor (52), the first electromagnetic regulating valve (42) and the second electromagnetic regulating valve (41).
4. A rocket oxygen safety valve opening and closing performance test system according to claim 3, wherein the heating unit comprises a first pressurizing switch (71), a first warmer (72), a second warmer (73) and a second pressurizing switch (74) which are sequentially arranged from an inlet end of the pressurizing system to an outlet end of the pressurizing system;
The cooling unit comprises a third supercharging switch (75), a first cooler (76), a second cooler (78) and a fourth supercharging switch (77) which are sequentially arranged from the inlet end of the supercharging system to the outlet end of the supercharging system;
the conventional unit includes a fifth boost switch (710).
5. Rocket oxygen safety valve opening and closing performance test system according to claim 1, further comprising a liquid filling pump controller (6) and a first pressure sensor (62) and a second pressure sensor (61) electrically connected with the liquid filling pump controller (6), wherein the first pressure sensor (62) is used for detecting the pressure in the test tank air pillow (11), and the second pressure sensor (61) is used for detecting the pressure in the liquid storage tank (12) of the test tank (1).
6. Rocket oxygen safety valve opening and closing performance test system according to claim 5, further comprising a filling device, the filling device comprising a filling tank (3) and an extraction device (36), an inlet of the extraction device (36) being in communication with an outlet of the filling tank (3), an outlet of the extraction device (36) being in communication with an inlet of a liquid tank (12) of the test tank (1), the extraction device (36) being electrically connected with the liquid filling pump controller (6).
7. Rocket oxygen safety valve opening and closing performance test system according to claim 6, wherein the liquid filling pump controller (6) is used for calculating the liquid level height of the liquid in the liquid storage tank (12) of the test tank (1) and controlling the opening and closing of the extraction device (36) according to the liquid level height calculation result; the calculation formula of the liquid level height is as follows:
wherein P1 is the pressure in the test tank air pillow (11) detected by a first pressure sensor (62); p2 is the pressure in the liquid storage tank (12) of the test tank (1) detected by a second pressure sensor (61); ρ is the liquid density in the liquid reservoir (12) of the test tank (1); g is gravitational acceleration.
8. A rocket oxygen safety valve opening and closing performance test system according to claim 4, wherein the test controller (5) is used for controlling the opening degree of the first electromagnetic regulating valve (42) and the opening degree of the second electromagnetic regulating valve (41) according to different preset flow ranges when the rocket oxygen safety valve opening and closing performance test is carried out, so that the gas flow of the pressurizing system reaches the preset flow range.
9. A rocket oxygen safety valve opening and closing performance test system according to claim 4, wherein the test controller (5) is configured to receive a temperature detection result of the first temperature sensor (52) and compare the temperature detection result with a preset temperature range when the rocket oxygen safety valve opening and closing performance test is performed, and perform coarse adjustment on a system temperature by adjusting the first warmer (72) and fine adjustment on the system temperature by adjusting the second warmer (73) when the temperature detection result is within the preset temperature range without operation when the temperature detection result is outside the preset temperature range;
The test controller (5) is further used for receiving a temperature detection result of the first temperature sensor (52) and comparing the temperature detection result with a preset temperature range when a rocket oxygen safety valve low-temperature start-stop performance test is carried out, operation is not needed when the temperature detection result is in the preset temperature range, when the temperature detection result is out of the preset temperature range, the system temperature is coarsely regulated by regulating the first cooler (76), and the system temperature is finely regulated by regulating the second cooler (78), so that the system temperature is in the preset temperature range.
10. A rocket oxygen safety valve opening and closing performance test method, which is characterized by being used for the rocket oxygen safety valve opening and closing performance test system according to any one of claims 1 to 9, wherein the rocket oxygen safety valve opening and closing performance test method comprises a rocket oxygen safety valve high Wen Qibi performance test method, a rocket oxygen safety valve low-temperature opening and closing performance test method and a rocket oxygen safety valve normal-temperature opening and closing performance test method;
the rocket oxygen safety valve high Wen Qibi performance test method comprises the following steps: filling deionized water into a liquid storage tank (12) of the test tank (1) to a preset liquid level; respectively setting preset ranges of gas temperature and gas flow, and adjusting the gas temperature and the gas flow in the heating unit to enable the gas temperature and the gas flow to reach the preset ranges, and then pressurizing the test tank air pillow (11); performing a high-temperature start-stop performance test; after changing the preset range value according to actual requirements, re-pressurizing the test tank air pillow (11), and then performing a high-temperature start-stop performance test again until the rocket oxygen safety valve high Wen Qibi performance test is finished;
The rocket oxygen safety valve low-temperature opening and closing performance test method comprises the following steps: filling liquid nitrogen into a liquid storage tank (12) of the test tank (1) to a preset liquid level; respectively setting preset ranges of gas temperature and gas flow, and adjusting the gas temperature and the gas flow in the cooling unit to enable the gas temperature and the gas flow to reach the preset ranges, and then pressurizing the test tank air pillow (11); performing a low-temperature start-stop performance test; the air pillow (11) of the test tank is pressurized again after the preset range value is changed according to actual requirements, and then the low-temperature start-stop performance test is carried out again until the low-temperature start-stop performance test of the rocket oxygen safety valve is finished;
the rocket oxygen safety valve normal temperature opening and closing performance test method comprises the following steps: filling deionized water into a liquid storage tank (12) of the test tank (1) to a preset liquid level; setting a preset range of gas flow, and adjusting the gas flow in the conventional unit to reach the preset range, so as to pressurize the test tank air pillow (11); performing a normal temperature start-stop performance test; and (3) after changing the preset range value according to actual needs, re-pressurizing the test tank air pillow (11), and then performing a normal-temperature start-stop performance test again until the normal-temperature start-stop performance test of the rocket oxygen safety valve is finished.
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