WO2023010629A1 - 低温推进剂火箭发动机的流量计标定***及方法 - Google Patents

低温推进剂火箭发动机的流量计标定***及方法 Download PDF

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Publication number
WO2023010629A1
WO2023010629A1 PCT/CN2021/114962 CN2021114962W WO2023010629A1 WO 2023010629 A1 WO2023010629 A1 WO 2023010629A1 CN 2021114962 W CN2021114962 W CN 2021114962W WO 2023010629 A1 WO2023010629 A1 WO 2023010629A1
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Prior art keywords
container
low
filling
pipeline
weighing
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PCT/CN2021/114962
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English (en)
French (fr)
Inventor
唐斌运
陈雨
徐鸿鹏
沈继彬
高强
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西安航天动力试验技术研究所
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Application filed by 西安航天动力试验技术研究所 filed Critical 西安航天动力试验技术研究所
Priority to US18/002,405 priority Critical patent/US20230341254A1/en
Priority to EP21945369.3A priority patent/EP4155689A4/en
Publication of WO2023010629A1 publication Critical patent/WO2023010629A1/zh

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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
    • G01F25/00—Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume
    • G01F25/10—Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume of flowmeters
    • G01F25/14—Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume of flowmeters using a weighing apparatus
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
    • G01F25/00—Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume
    • G01F25/10—Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume of flowmeters
    • G01F25/17—Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume of flowmeters using calibrated reservoirs
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
    • F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
    • F17C13/00—Details of vessels or of the filling or discharging of vessels
    • F17C13/001—Thermal insulation specially adapted for cryogenic vessels

Definitions

  • the invention relates to a low-temperature propellant rocket engine, in particular to a flowmeter calibration system and method for a low-temperature propellant rocket engine.
  • the conventional flow calibration method is generally to calibrate the flow of the turbine flowmeter at the work site.
  • the amount of liquid flowing out of the container is used as the basis for flow meter calibration.
  • the flow meter is installed at the liquid outlet of the container, and then the flow output through the container Perform flow calibration of the flowmeter.
  • water calibration method or laser measuring instrument method is usually used.
  • the water calibration method is to fill the container with water, put the water into a weighable container, and obtain the height difference of the corresponding container by weighing. Through multiple calibrations, the actual volume of each height in the container can be completed.
  • the laser measuring instrument method is to measure the actual volume of the container by the laser measuring instrument, and subtract the volume of the redundant parts such as the ribs corresponding to each section in the container to obtain the actual and accurate volume of the container.
  • the low-temperature medium When measuring the volume of the container, if the low-temperature medium is directly used instead of water, the low-temperature medium will cause a large difference between the volume of the container and the actual working volume due to the low-temperature shrinkage, evaporation and uneven deformation of the related structure. It is very difficult to reweight, which leads to large errors in the flow calibration value of the flowmeter.
  • a segmented capacitor level gauge or other similar level gauges are generally used.
  • the liquid level gauge cannot be simultaneously Taking into account both water and the actual low-temperature medium, it is difficult to clean the water from the inside of the liquid level gauge after measuring the water. Therefore, it is generally necessary to remove the liquid level gauge during calibration, and use laser and other methods to realize liquid level measurement. After the liquid level calibration is completed, clean the container and reinstall the liquid level gauge. When measuring again, there is a relatively large error in the zero alignment of the same liquid level gauge, or there is a large error when using a different liquid level gauge.
  • the conventional calibration method When calibrating the reference flowmeter, in order to ensure that the outlet does not hold pressure, the conventional calibration method generally adopts the calibration method of open discharge of low-temperature media. For liquid hydrogen, methane and other explosive media, the danger is high and the safety is poor, so it can only be carried out. Calibration of the reference flowmeter for a short period of time reduces the accuracy of the method for calculating the average flow rate of the reference flowmeter.
  • the present invention aims to solve the problem that when low-temperature propellant rocket engines use flowmeters for flow measurement, if low-temperature medium is directly used instead of water, the volume of the container is quite different from the actual working volume, and it is very difficult to weigh the container, and it needs to be installed.
  • the calibration and measurement of the liquid level meter is cumbersome and has large errors, which further reduces the accuracy of the flow meter measurement.
  • the reference flow meter can only be used for a short period of time through the calibration method of open discharge of low-temperature medium.
  • the calibration reduces the calculation accuracy of the average flow rate of the reference flowmeter, and provides a flowmeter calibration system and method for a low-temperature propellant rocket engine.
  • the invention provides a flowmeter calibration system for a low-temperature propellant rocket engine, which is special in that:
  • the container filling unit is used to connect the tank car and the container;
  • the supply pipeline includes at least one temperature sensor and at least one pressure sensor set at any position, and a first isolation valve, a reference flow meter, a calibration flow regulating hand valve, a vertical main pipe and N circumferentially uniformly distributed horizontal pipe; wherein, 2 ⁇ N ⁇ 6; the inlet of the first isolation valve is connected to the outlet of the container, and the outlet of the vertical main pipe is respectively connected to the inlets of N horizontal pipes;
  • the weighing unit includes N vertical branch pipes, N collection containers and N weighing devices; the N vertical branch pipes are respectively communicated with corresponding horizontal pipes through force balance compensators; the N vertical branch pipes are respectively arranged in corresponding directly above the collection container; a weighing device is correspondingly provided below the N collection containers, and the weighing device is used for weighing the incremental liquid in the collection container;
  • the outlet of the collecting container is communicated with the inlet of the fast recovery container through the isolation pipeline and the second isolation valve;
  • the weighing filling recovery unit is used to connect the tank car and the collection container;
  • the recovery unit is used to connect the fast recovery container and the tanker;
  • the weighing device includes a weighing assembly and at least two balance assemblies uniformly distributed on the weighing assembly;
  • the weighing assembly includes a base, at least two load cells, a moving platform and a support frame arranged sequentially from bottom to top; at least two load cells are evenly arranged under the lower surface of the moving platform, and the sensitive surface of the load cell There is a gap or a contact setting between the lower table of the moving platform, and the support frame is installed in the middle of the moving platform to support the corresponding collection container;
  • the balance assembly includes a support rod arranged on the base, a lever hinged on the support rod, a hanging chain, and weights;
  • the inner end of the lever is connected with the moving platform through a hanging chain, and the outer end is hung with the weight.
  • balance assemblies there are two balance assemblies, and they are arranged symmetrically on both sides of the moving platform.
  • the low-temperature medium exhaust system includes at least two exhaust pipelines, the inlets of the exhaust pipelines are all connected to at least one collection container, and the outlets of the exhaust pipelines are all connected to the external The gas purification system is connected; one of the exhaust pipelines is equipped with an automatic exhaust valve, which is controlled by an external control unit to discharge the gas in the collection container, and the remaining exhaust pipelines are equipped with manual exhaust valves;
  • the calibrated flow regulating hand valve is connected in parallel with a calibrated pneumatic valve, and the calibrated pneumatic valve is controlled by an external control unit to discharge the low-temperature medium in the supply pipeline to the weighing, filling and recovery unit.
  • the container filling unit includes a filling interface, a filling pipeline connected to the filling interface, and a recovery pipeline connected to the filling pipeline, and the filling pipeline is along the low-temperature medium filling direction
  • a filling hand valve and a filling filter are set in sequence, and the recovery pipeline is sequentially set with a recovery valve and a bellows compensator along the low-temperature medium recovery direction, and the filling interface is connected to the tanker through a hose;
  • the weighing filling recovery unit has the same structure as the container filling unit, and the weighing filling recovery unit is used for filling and recovering the low-temperature medium into the collection container, and the recovery unit includes recovery valves connected in sequence through pipelines, Bellows compensator and filling port for recovery of cryogenic medium into the tanker.
  • the balance compensator adopts an angular force balance compensator, and a load cell is installed on the pull rod of the angular force balance compensator.
  • the supply pipeline is also provided with a corrugated compensator at the bottom of the container, a corrugated compensator at the horizontal section of the container, a filter and a corrugated compensator in the middle along the low-temperature medium conveying direction;
  • the collection container is a fully enclosed vacuum interlayer container.
  • the present invention also provides a method for calibrating a flowmeter of a cryogenic propellant rocket engine, which is special in that it comprises the following steps:
  • Step 1 In-situ Calibration of the Weighing Cell
  • Step 1.1 Weigh and fill the recovery unit to fill the collection container with low-temperature medium.
  • the filling level in each collection container reaches above 70%, and the temperature of the low-temperature medium in the collection container is ⁇ 5°C, the collection container The low-temperature medium in the medium is recovered to the fast recovery container;
  • Step 1.2 Record the zero position of the load cell and the total mass m of the weight on the weighing device
  • Step 1.4 Repeat step 1.3K times, K ⁇ 2, perform least squares fitting on the recorded ((K+1) ⁇ M) group of data, obtain the corresponding relationship between V and ( mtotal -m), and complete the weighing In situ calibration of the unit;
  • Step 2 Pre-cooling the cryogenic medium in-situ calibration system
  • Step 3 In situ calibration of the container
  • Step 3.1 close the second isolation valve, open the first isolation valve, and fill the container with the container filling unit;
  • Step 3.2 According to the drop height of the liquid level to be calibrated in the container, gradually open the calibrated flow adjustment hand valve, slowly discharge the low-temperature medium in the container to the collection container, use a weighing device to weigh each collection container, and calculate the volume of each collection container in the container. The volume corresponding to the drop height of the liquid level is repeated at least once to complete the calibration of the container;
  • the second isolation valve is opened to discharge the weighed low-temperature medium from the collection container;
  • Step 4 Calibrate the reference flow meter
  • Step 4.1 Close the second isolation valve, or remove the isolation pipeline and its downstream pipeline, so that the low-temperature medium in the collection container can only be discharged from the weighing filling recovery unit;
  • Step 4.2 Open the first isolation valve and the calibration pneumatic valve, so that the low-temperature medium passes through the supply pipeline, the collection container, and then discharged from the weighing, filling and recovery unit. Record the volume of the low-temperature medium in the container during the same period of time, and calculate The average flow out of the supply pipeline during this period is used to calibrate the flow rate of the reference flowmeter.
  • step 4.11 is also included: connect the low-temperature medium exhaust system to the collection container, open the automatic exhaust valve through the external control unit, and discharge the gas generated by the volatilization of the low-temperature medium in the system; When the pressure in the system is ⁇ 0.1MPa, close the automatic exhaust valve.
  • step 2 pre-cool the low-temperature medium in-situ calibration system, as follows:
  • Step 2.1 Weighing, filling, and recovery unit fills the collection container with low-temperature medium, and at the same time, the container filling unit fills the container with low-temperature medium, wherein the filling liquid level in the collection container reaches above 40%, and the filling of container 1 The liquid levels all reach more than 70%, realizing the precooling of the collection container 11 and the container 1;
  • Step 2.2 When the temperature of the low-temperature medium in the collection container and the container is both ⁇ 5°C, open the first isolation valve, close the calibrated flow adjustment hand valve, cool the first pipeline before the supply pipeline hand valve with low-temperature medium, and open at the same time The second isolation valve discharges the low-temperature medium in the collection container;
  • Step 2.3 When the difference between the measured temperature of the temperature sensor in the first pipeline and the temperature of the cryogenic medium under standard atmospheric pressure is less than 5°C, open the calibrated flow regulating hand valve to cool the second pipeline and the second pipeline after the hand valve of the supply pipeline.
  • vertical pipe
  • Step 2.4 When the difference between the temperature measured by the temperature sensor in the second pipeline and the temperature at the standard atmospheric pressure of the low-temperature medium is less than 5°C, and the pressure of the low-temperature medium in the supply pipeline is ⁇ 0.05Mpa, close the calibrated flow regulating hand valve and open The second isolation valve, when the low temperature medium is emptied from the collection container, isolation pipeline and fast recovery container, realizes the precooling of the low temperature medium in-situ calibration system.
  • the present invention has the following beneficial effects.
  • the flowmeter calibration system of a kind of cryogenic propellant rocket engine that the present invention adopts has adopted multi-container symmetrical structure force balance mode, a plurality of collecting containers adopts completely symmetrical structure, and the force balance compensator is set at the corner of pipeline, can The pipeline force at the turn is converted into the internal force in the force balance compensator rod, and a load cell is installed on the force balance compensator rod, which can compare and measure the symmetry of each force balance compensator.
  • In-situ correction when symmetrical; at the same time, multiple force-balanced bellows (corrugated compensators) are installed on the supply pipeline, which can effectively reduce the axial force generated by the pipeline due to the increase in the internal pressure of the supply pipeline.
  • the weighing of the container has an effect.
  • each collection container is all formed by the symmetrical structure of force balance compensator, solves the lateral force that produces in the horizontal direction of collection container, especially 4
  • the symmetrical structure of the collection container can well eliminate the influence caused by the internal pressure of the horizontal pipe, and then can effectively eliminate the additional stress caused by a small amount of gasification of the low-temperature medium in each container.
  • the flow meter calibration system of a low-temperature propellant rocket engine adopted by the present invention adopts a suspended load-bearing structure, and a high-precision weighing unit is arranged below each container, wherein the weighing device can first balance the self weight of the container, Furthermore, the load cell can be replaced with a small-range one to achieve high-precision weighing of the low-temperature medium entering the container, eliminate the basic zero position, and improve the weighing accuracy; at the same time, each container is fully enclosed, and a vacuum interlayer is used for insulation. Avoid the volatilization of low-temperature medium due to temperature rise.
  • the flowmeter calibration system of a low-temperature propellant rocket engine adopted by the present invention can discharge the gas produced by volatilization of the low-temperature medium in the system before calibrating the reference flowmeter by adopting the low-temperature medium exhaust system, so as to avoid the system outlet Therefore, the reference flowmeter can be safely calibrated for a long time, which increases the total amount of calculation data of the reference flowmeter, and can improve the accuracy of the average flow calculation method of the reference flowmeter.
  • the method for calibrating the flowmeter of a low-temperature propellant rocket engine adopted in the present invention by using the low-temperature medium to pre-cool the low-temperature medium in-situ calibration system in advance, and carrying out in-situ calibration on the container by the weighing device, avoiding the temperature difference
  • the influence of the quality change of the cryogenic medium improves the accuracy of the in-situ calibration of the container.
  • the in-situ calibration of the container and the calibration of the reference flowmeter do not require the installation of a liquid level gauge, which avoids the limitations of the use of the liquid level gauge.
  • the flowmeter calibration method of a kind of cryogenic propellant rocket engine that the present invention adopts can eliminate the effect of the additional force that container, pipeline precooling shrinkage causes, make load cell measure value It can more truly characterize the quality of the medium.
  • Fig. 1 is a structural schematic diagram of a flowmeter calibration system for a cryogenic propellant rocket engine of the present invention.
  • Fig. 2 is a structural schematic diagram of the weighing unit in the flow meter calibration system of the cryogenic propellant rocket engine of the present invention.
  • 2-container filling unit 21-recovery valve, 22-bellows compensator, 23-filling interface, 24-filling filter, 25-filling hand valve;
  • 3-container bottom corrugated compensator 4-first isolation valve, 5-container horizontal section corrugated compensator, 6-filter, 7-reference flow meter, 8-middle corrugated compensator, 9-calibration flow adjustment hand valve, 91-vertical main pipe, 92-horizontal pipe, 99-calibration pneumatic valve, 100-vertical branch pipe;
  • a flow meter calibration system for a low-temperature propellant rocket engine in this embodiment includes a container filling unit 2, a container 1, a supply pipeline, a weighing unit, and a quick recovery unit connected in sequence.
  • the container filling unit 2 is used to connect the tank car and the container 1;
  • the supply pipeline includes at least one temperature sensor and at least one pressure sensor arranged at any position, and the corrugated compensator 3 at the bottom of the container tank connected by pipelines in sequence, the second An isolation valve 4, a corrugated compensator 5 in the horizontal section of the container, a filter 6, a reference flow meter 7, a central corrugated compensator 8, a calibration flow regulating hand valve 9, a vertical main pipe 91 and 4 horizontal pipes 92 evenly distributed around the circumference;
  • the inlet of the first isolation valve 4 is connected to the outlet of the container 1, and the outlet of the vertical main pipe 91 is respectively connected to the inlets of the four horizontal pipes 92, and the corresponding four horizontal pipes 92 are distributed in a cross;
  • the weighing unit includes 4 vertical branch pipes 100, 4 collection containers 11 and 4 weighing devices; the 4 vertical branch pipes communicate with the corresponding horizontal pipes 92 through the force balance compensator 10 respectively ; 4 vertical branch pipes are respectively arranged directly above the corresponding collection containers 11; correspondingly, a weighing device is provided below the 4 collection containers 11, and the weighing device is used for weighing the incremental liquid in the collection container 11;
  • the outlet of the collection container 11 is communicated with the inlet of the fast recovery container 14 through the isolation pipeline 12 and the second isolation valve 13, and the outlet of the collection container 11 is provided with a drain valve 39, and the drain valve 39 is manually controlled. switch to discharge the low-temperature medium in the collection container 11 to the weighing filling recovery unit 15 or the recovery unit 16 .
  • the weighing filling recovery unit 15 is used to connect the tank car and the collection container 11;
  • the recovery unit is used to connect the fast recovery container 14 and the tanker.
  • the weighing device includes a weighing assembly and two balance assemblies evenly distributed on the weighing assembly;
  • the weighing assembly includes a base 31, two load cells 32, a moving platform 33, and a support frame 34 arranged sequentially from bottom to top; the two load cells 32 are evenly arranged under the lower surface of the moving platform 33, and The gap between the sensitive surface of the sensor 32 and the lower surface of the moving platform 33 is set or contacted, and the support frame 34 is installed in the middle of the moving platform 33 to support the corresponding collection container 11;
  • Two balance assemblies are symmetrically arranged on both sides of the moving platform 33, and the balance assemblies include a support rod 35 arranged on the base 31, a lever 36 hinged on the support rod 35, a hanging chain 37, and a weight 38;
  • the inner end of the lever 36 is connected with the moving platform 33 through a hanging chain 37 , and the weight 38 is hung on the outer end thereof.
  • the load cell 32 Due to the heavy weight of the container 1, if the load cell 32 is directly used to measure its weight, since the load cell 32 has a large measuring range, taking a 50m3 container as an example, about four 100kN or more are needed, and the relative error is relatively large . Therefore, 4 lever-type force balance devices are arranged around the platform. By setting suitable weights 38, the container can be lifted. With the increase of valves, the weight of the container on the load cell 32 will gradually decrease, which is an ideal state. The weight of the container on the lower load cell 32 can be 0, and it is generally controlled within 100kg in actual use. At this time, the load cell can be replaced with a small-range one, such as four 5kN-level ones. With this structure, high-precision weighing of the low-temperature medium entering the container can be realized.
  • the container filling unit 2 includes a filling interface 23, a filling pipeline connected to the filling interface and a recovery pipeline connected to the filling pipeline.
  • a filling hand valve 25 and a filling filter 24 are set, and the recovery pipeline is provided with a recovery valve 21 and a bellows compensator 22 in sequence along the low-temperature medium recovery direction, and the filling interface 23 is connected to the tanker through a hose , the tank car is set near the container filling unit 2.
  • the low-temperature medium outlet of the filling pipeline is connected with the bottom inlet of the container 1, the bottom outlet of the container 1 is connected with the inlet of the collection container 11 through the supply pipeline, and the outlet of the collection container 11 is connected with the fast recovery container 14 through the isolation pipeline 12
  • the isolation pipeline 12 adopts a force isolation hose, and the second isolation valve 13 is arranged on the force isolation hose.
  • the weighing filling recovery unit 15 has the same structure as the container filling unit 2, the weighing filling recovery unit 15 is used to fill and recover the low-temperature medium to the collection container 11, and the recovery unit 16 includes sequentially The connected recovery valve, bellows compensator and filling interface, the recovery unit 16 is used to recover the low-temperature medium into the tanker.
  • the balance compensator 10 adopts an angle-type force balance compensator, and a load cell is installed on the pull rod of the angle-type force balance compensator.
  • the collection container 11 is a fully enclosed vacuum interlayer container; the quick recovery container 14 is the The container is placed in a lower position and can be buried in the ground.
  • the present invention can also add a set of exhaust system to each collection container 11, including the first exhaust pipeline and the second exhaust pipeline , the inlets of the first exhaust pipeline and the second exhaust pipeline are all connected with one of the collection containers 11, and their outlets are all connected with the external gas purification system; the first exhaust pipeline includes an automatic exhaust valve 17, The second exhaust line includes a manual exhaust valve 18 .
  • the explosive and flammable gas at the outlet of the collection container 11 can be discharged by controlling the opening of the automatic exhaust valve 17 .
  • the manual exhaust valve 18 can be opened to discharge the excess explosive and combustible gas in the collection container 11 .
  • the present invention can also only install an exhaust system on one of the collection containers 11, since the four collection containers 11 communicate with each other through the vertical main pipe 91, and then the flammable gases in all the collection containers 11 can be discharged.
  • a calibration pneumatic valve 99 is connected in parallel on the calibration flow regulating hand valve 9.
  • the calibration pneumatic valve is controlled by an external control unit to quantitatively discharge the low-temperature medium in the supply pipeline to the weighing and filling recovery unit, and then The falling volume of the low temperature medium in the same time period can be recorded multiple times.
  • This implementation also provides a method for calibrating a flowmeter of a cryogenic propellant rocket engine, comprising the following steps:
  • Step 1 In-situ Calibration of the Weighing Cell
  • Step 1.1 Weighing and filling the recovery unit 15 to fill the collection container 11 with low-temperature medium, when the liquid level gauge 111 in each collection container 11 shows that the filling level reaches more than 70%, and the low-temperature medium in the collection container 11 When the temperature is ⁇ 5°C, recover the low-temperature medium in the collection container 11 to the fast recovery container 14;
  • Step 1.2 record the zero position of the load cell 32 and the total mass m of the weight 38 on the weighing device;
  • Step 1.3 According to the range of use of the load cell, unload the weight of the preset mass m0 on each lever 36, record the output value V of the load cell 32 and the mass m of the remaining weight, on this basis, Then unload the weight with preset mass m0 , record the output value V of load cell 32 and the mass m of the remaining weight, and unload the weight with mass m0 5 times in this way, and record 5 sets of data in total;
  • Step 1.4 Repeat step 1.3 twice to obtain a total of 15 sets of data, and perform least squares fitting on the recorded 15 sets of data to obtain the corresponding relationship between V and ( mtotal -m), and complete the in-situ calibration of the weighing unit;
  • Step 2 Pre-cooling the cryogenic medium in-situ calibration system
  • Step 2.1 Weighing and filling the recovery unit 15 to fill the collection container 11 with low-temperature medium, and the filling liquid level in the collection container 11 reaches above 40%.
  • the container filling unit 2 fills the container 1 with low-temperature medium, and the low-temperature medium tank truck enters the low-temperature medium from the filling filter 24 and the filling hand valve 25 into the container 1 sequentially through pressurization.
  • the top exhaust valve 101 of the container 1 is in an open state to ensure that the vaporized gas can be discharged in time after the low-temperature medium enters the container 1, and the internal pressure of the container 1 will not be too high, so that the filling level of the container 1 reaches 70 More than %, realize the precooling of collecting container 11 and container 1;
  • Step 2.2 When the temperature of the low-temperature medium in the collection container 11 and container 1 is both ⁇ 5°C, open the first isolation valve 4, close the calibration flow regulating hand valve 9, and cool the first pipe before the hand valve 9 of the supply line with the low-temperature medium and open the second isolation valve 13 at the same time to discharge the low-temperature medium in the collection container 11;
  • Step 2.3 When the difference between the measured temperature of the temperature sensor in the first pipeline and the temperature of the cryogenic medium under the standard atmospheric pressure is less than 5°C (take liquid oxygen as an example, its standard atmospheric pressure is -183°C, and the temperature of the relevant pipeline is required The measured temperature is lower than -178°C), at this time, after the first pipeline is completely cooled, there is no serious exhaust phenomenon in the container 1. Open the calibration flow regulating hand valve 9, cool the second pipeline and the vertical branch pipe behind the supply pipeline hand valve 9, and perform flow regulation according to the cold condition of the second pipeline of the supply pipeline and the vertical branch pipe 100;
  • Step 2.4 When the difference between the temperature measured by the temperature sensor in the second pipeline and the temperature at the standard atmospheric pressure of the low-temperature medium is less than 5°C, and the pressure of the low-temperature medium in the supply pipeline is ⁇ 0.05Mpa, close the calibrated flow regulating hand valve 9, Open the second isolation valve 13, and when the cryogenic medium is emptied from the collection container 11, the isolation pipeline 12 and the fast recovery container 14, the pre-cooling of the cryogenic medium in-situ calibration system is realized.
  • Step 3 In situ calibration of the container
  • Step 3.1 Close the calibration flow regulating hand valve 9 and the second isolation valve 13, and open the first isolation valve 4, and the container filling unit 2 fills the container 1 to the highest liquid level to be calibrated;
  • Step 3.2 Gradually open the calibrated flow regulating hand valve 9 according to the drop height of the liquid level to be calibrated in container 1, and slowly discharge the low-temperature medium in container 1 to the collection container 11 (slow discharge can ensure that the predetermined amount is discharged each time, generally at It is advisable to complete a discharge within 10 minutes), use a weighing device to weigh each collection container 11, calculate the volume corresponding to the drop height of each liquid level in the container 1, repeat at least once, and complete the calibration of the container 1; for example, when the container 1 The liquid oxygen drops to a certain height, such as 10cm, and the cryogenic medium entering the collection container 11 is weighed, for example, the weighed weight is 114kg.
  • the second isolation valve 13 is opened to discharge the weighed low-temperature medium from the collection container 11, and can be discharged to the quick recovery container 14. If the liquid level of the quick recovery container 14 is too high, the recovery unit can be used 16 to vent it out.
  • the system Since the system has undergone several previous pre-cooling steps, the system is already in the same temperature condition as the low-temperature medium, so its evaporation is very small, which is basically the same as the case of water calibration.
  • the weight of the medium according to the drop of the liquid level by 10 cm is 114 kg, so the volume of this section of the collection container 11 is 0.1 m 3 .
  • the second isolation valve 13 is used to discharge the weighed low-temperature medium to the fast recovery container 14 . If the liquid level in the quick recovery container 14 is too high, it can be drained using the recovery unit 16 .
  • the volume corresponding to each equal-height segment (for example, 10 cm as a unit height segment) in the container 1 can be obtained, and then the in-situ calibration of the container 1 is completed.
  • Step 4 Calibrate the reference flow meter
  • Step 4.1 Close the second isolation valve 13, or remove the isolation pipeline 12 and its downstream pipeline, so that the low-temperature medium in the collection container 11 can only be discharged from the weighing filling recovery unit 15;
  • Step 4.11 Connect the low-temperature medium exhaust system to the collection container 11, open the automatic exhaust valve 17 through the external control unit, and discharge the gas generated by the volatilization of the low-temperature medium in the system.
  • the pressure in the system is ⁇ 0.1MPa, close the automatic exhaust valve.
  • Step 4.2 Open the first isolation valve 4 and the calibration pneumatic valve 99, so that the low-temperature medium passes through the supply pipeline and the collection container 11 in sequence, and then is discharged from the weighing, filling and recovery unit 15, and records the drop of the low-temperature medium in the container 1 in the same time period several times and calculate the average flow of the supply pipeline during this period, and use the average flow to calibrate the flow of the reference flowmeter 7.
  • the calibration discharge the low-temperature medium for a period of time according to the expected time, and then use the measured data to calculate and complete the calibration.
  • the liquid level drops 20cm from 5-15S during the discharge process.
  • the number of rotations of the flow meter is 100 revolutions.
  • the 20cm calibrated containers are 0.1m 3 and 0.11m 3 respectively Therefore, the discharge container for 5-15s is 0.21m 3 , and the volume of each revolution of the flowmeter is 0.0021m 3 .
  • the gas generated by volatilization of the low-temperature medium in the system can be discharged before the reference flowmeter is calibrated, and the low-temperature medium containing gas is discharged in a small amount, which is safe and reliable. It can achieve long-term discharge calibration of low-temperature media, and the calibration algorithm for the average flow rate can greatly improve the calibration accuracy.

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  • Physics & Mathematics (AREA)
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  • General Physics & Mathematics (AREA)
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Abstract

本发明涉及低温推进剂火箭发动机，具体涉及一种低温推进剂火箭发动机的流量计标定***及方法，以解决现有低温推进剂火箭发动机使用流量计进行流量测量时，流量计测量的精确性低，且只能进行短时间段的参考流量计标定的问题。本发明所采用的技术方案为：一种低温推进剂火箭发动机的流量计标定***，包括依次连接的容器加注单元、容器、供应管路、称重单元、快速回收容器、称重加注回收单元和回收单元；容器加注单元用于连接槽车和容器；供应管路包括温度传感器和压力传感器，以及依次管路连接的第一隔离阀、参考流量计、标定流量调节手阀、竖直主管和N个圆周均布的水平管。本发明还提供一种低温推进剂火箭发动机的流量计标定方法。

Description

低温推进剂火箭发动机的流量计标定***及方法 技术领域
本发明涉及低温推进剂火箭发动机，具体涉及一种低温推进剂火箭发动机的流量计标定***及方法。
背景技术
对于使用液氧、液氢、甲烷等低温推进剂的火箭发动机，在地面热试车点火试验中发动机预冷排放的气液混合状态时，需进行准确的流量测量，一般使用涡轮型流量计进行流量测量。涡轮型流量计在使用前需要进行流量标定，由于涡轮流量计的流量标定一般在检定中心进行流量标定，并且只能进行水介质流动下的流量标定。因此当将涡轮流量计应用在低温介质的流量测量前，需进行低温介质流动下的流量标定。
常规的流量标定方法一般是在工作现场进行涡轮流量计的流量标定，一般采用容器内流出液体量作为流量计标定的基础，先将流量计安装在容器的液体出口，再通过该容器的流量输出进行流量计的流量标定。为了确保准确，首先需将标定容器的容积进行准确测量，目前通常采用水标定法或激光测量仪法。水标定法是通过把容器里放满水，通过将水放置至一个可称重的容器，通过称重得到对应容器的高差，通过多次的标定，可完成容器内各个高度的实际容积的测量。激光测量仪法是通过激光测量仪测量容器的实际容积，并将容器中每个截面对应的加强筋等多余物的体积减去，获取容器的实际准确容积。
然后给标定容器注水，并***一个可以准确测量低温介质液位的液位计， 进行液位的测量。通过液位计初始零液位值与容器标定零位的对齐，可以在累积时间内获取比较准确的标定容器实际液体流量。当容器通过低温介质对流量计流量标定时，建立低温介质流量供应管路，将容器和流量计安装在供应管路上，通过对比一段时间内流出的容器内的介质量和该段时间内流量计叶轮的实际转过的圈数，可以获取流量计叶轮每转过一圈的介质体积流量，实现流量计的流量标定。
但是现有技术方案在使用中存在如下几个问题：
1、当容器测量容积时，若直接采用低温介质代替水，低温介质由于低温的收缩、蒸发及相关结构的不均匀变形，导致容器的容积与实际工作时的容积差异较大，对容器进行称重十分困难，进而导致流量计的流量标定数值存在较大误差。
2、当通过容器的流量对流量计的流量进行标定时，为保证低温介质液位计的工作准确，一般采用分节式电容液位计及或其它类似液位计，液位计一般不能同时兼顾水及实际低温介质，当液位计测量过水以后很难将水从其内部清理掉。因此标定时一般需将液位计拆除，采用激光等方法实现液位测量。液位标定完毕后，清理容器，重新安装液位计。再次测量时，同一液位计的零位对齐存在比较大的误差，或者使用不同液位计也存在较大误差。
3、在标定参考流量计时，常规的标定方法为了确保出口不憋压，一般采用敞开式排放低温介质的标定方式，针对液氢，甲烷等易***介质危险性大、安全性差，进而只能进行短时间段的参考流量计标定，降低了参考流量计的平均流量计算方法的精度。
发明内容
本发明在于解决目前低温推进剂火箭发动机使用流量计进行流量测量时，若直接采用低温介质代替水，容器的容积与实际工作时的容积差异较大，对容器进行称重十分困难，并且需要安装液位计进行标定和测量，操作繁琐且误差较大，进而降低流量计测量的精确性，在标定参考流量计时，通过敞开式排放低温介质的标定方式，只能进行短时间段的参考流量计标定，降低了参考流量计的平均流量计算精度的问题，而提供一种低温推进剂火箭发动机的流量计标定***及方法。
本发明所采用的技术方案为：
本发明提供一种低温推进剂火箭发动机的流量计标定***，其特殊之处在于：
包括依次连接的容器加注单元、容器、供应管路、称重单元、快速回收容器、回收单元，以及称重加注回收单元；
所述容器加注单元用于连接槽车和容器；
所述供应管路包括任意位置设置的至少一个温度传感器和至少一个压力传感器，以及依次管路连接的第一隔离阀、参考流量计、标定流量调节手阀、竖直主管和N个圆周均布的水平管；其中，2≤N≤6；第一隔离阀的进口接容器的出口，所述竖直主管的出口与N个水平管的进口分别连接；
所述称重单元包括N个竖直分管、N个收集容器和N个称重装置；N个竖直分管分别通过力平衡补偿器与相应的水平管连通；N个竖直分管分别设置在相应收集容器的正上方；N个收集容器的下方对应设置有称重装置，所述称重装置用于收集容器中增量液体的称重；
所述收集容器的出口通过隔离管路和第二隔离阀与快速回收容器的进口 连通；
所述称重加注回收单元用于连接槽车和收集容器；
所述回收单元用于连接快速回收容器和槽车；
所述称重装置包括称重组件和均布在称重组件上的至少两个平衡组件；
所述称重组件包括从下至上依次设置的底座、至少两个测力传感器、动平台和支撑架；至少两个测力传感器均匀布设在动平台下台面的下方，且测力传感器的敏感面与动平台下台面之间间隙设置或接触设置，所述支撑架安装在动平台的正中部，用于支撑对应的收集容器；
所述平衡组件包括设置在底座上的支撑杆、铰接在支撑杆上的杠杆，以及挂链、砝码；
所述杠杆的内侧端通过挂链与动平台连接，其外侧端挂设有所述砝码。
进一步地，所述平衡组件设置有两个，且对称设置在动平台的两侧。
进一步地，所述收集容器设置有4个，对应的4个水平管呈十字分布。
进一步地，还包括低温介质排气***，所述低温介质排气***包括至少两条排气管路，所述排气管路的进口均与至少一个收集容器相连通，其出口均与外部的气体净化***相连；其中一条排气管路上设置有自动排气阀，通过外部控制单元控制自动排气阀将收集容器中的气体排出，其余排气管路上设置有手动排气阀；
所述标定流量调节手阀上并联有标定气动阀，通过外部控制单元控制标定气动阀将供应管路中的低温介质的排放至称重加注回收单元。
进一步地，所述容器加注单元包括加注接口、与加注接口连接的加注管路和并接在加注管路上的回收管路，所述加注管路沿低温介质加注方向上依 次设置加注手阀和加注过滤器，所述回收管路沿低温介质回收方向上依次设置回收阀门和波纹管补偿器，所述加注接口通过软管与槽车相连接；
所述称重加注回收单元与容器加注单元结构相同，所述称重加注回收单元用于向收集容器加注和回收低温介质，所述回收单元包括通过管路依次连接的回收阀门、波纹管补偿器和加注接口，用于将低温介质回收至槽车中。
进一步地，所述平衡补偿器采用角式力平衡补偿器，角式力平衡补偿器的拉杆上装有测力传感器。
进一步地，所述供应管路沿着低温介质输送方向还设置有容器箱底波纹补偿器、容器水平段波纹补偿器、过滤器和中部波纹补偿器；所述收集容器为全封闭真空夹层容器。
本发明还提供一种低温推进剂火箭发动机的流量计标定方法，其特殊之处在于，包括以下步骤：
步骤1：称重单元原位标定
步骤1.1：称重加注回收单元向收集容器加注低温介质，当每个收集容器中的加注液位均到达70％以上，且收集容器中的低温介质温度＜5℃时，将收集容器中的低温介质回收至快速回收容器；
步骤1.2：记录测力传感器的零位和称重装置上砝码总质量m 总；
步骤1.3：根据测力传感器的使用范围，在每个杠杆上均卸载预设质量m 0的砝码，记录测力传感器的输出值V和剩余砝码的质量m，在此基础上，再卸载预设质量m 0的砝码，记录测力传感器32的输出值V和剩余砝码的质量m，如此进行M次卸载质量为m 0的砝码，总共记录M组数据，M≥5，其中，m 0＝F/Mg，F为测力传感器最大量程，g为重力加速度；
步骤1.4：重复步骤1.3K次，K≥2，对记录的((K+1)×M)组数据进行最小二乘法拟合，得到V和(m 总-m)的对应关系，完成称重单元的原位标定；
步骤2：预冷低温介质原位标定***
用低温介质依次预冷收集容器和容器、供应管路手阀之前的第一管路、冷却供应管路手阀后的第二管路和竖直分管；要求前一个预冷区域的温度与低温介质标准大气压下的温度之差小于5℃时再进行下一个预冷区域的预冷；
当竖直分管冷却完成后，关闭标定流量调节手阀，将标定流量调节手阀下游的管路***进行排空，实现低温介质原位标定***的预冷；
步骤3：容器原位标定
步骤3.1：关闭第二隔离阀，并打开第一隔离阀，容器加注单元对容器加注；
步骤3.2：按照容器需要标定的液位下降高度，逐渐打开标定流量调节手阀，将容器中的低温介质缓慢排放至收集容器，使用称重装置对每个收集容器进行称重，计算容器中每个液位下降高度对应的容积，重复至少一次，完成容器的标定；
每次称重完成后，均打开第二隔离阀将称重后的低温介质从收集容器中排出；
步骤4：标定参考流量计
步骤4.1：关闭第二隔离阀，或拆除隔离管路及其下游管路，使收集容器中的低温介质只能从称重加注回收单元排出；
关闭第一隔离阀和标定流量调节手阀，容器加注单元对容器进行加注；
步骤4.2：打开第一隔离阀和标定气动阀，使低温介质依次通过供应管路、 收集容器后从称重加注回收单元排出，多次记录同一时间段容器中低温介质下降的体积，并计算出供应管路该段时间的平均流量，用平均流量来标定参考流量计的流量。
进一步地，在步骤4.1和步骤4.2之间，还包括步骤4.11：将低温介质排气***连接在收集容器上，通过外部控制单元打开自动排气阀，排放***中低温介质挥发产生的气体；当***中的压力≤0.1MPa时，关闭自动排气阀。
进一步地，步骤2中预冷低温介质原位标定***，具体如下：
步骤2.1：称重加注回收单元向收集容器加注低温介质，同时，容器加注单元向容器加注低温介质，其中收集容器中的加注液位均到达40％以上，容器1的加注液位均到达70％以上，实现收集容器11和容器1的预冷；
步骤2.2：当收集容器和容器中低温介质温度均＜5℃时，打开第一隔离阀，关闭标定流量调节手阀，用低温介质冷却供应管路手阀之前的第一管路，并同时打开第二隔离阀，将收集容器中的低温介质泄出；
步骤2.3：当第一管路中的温度传感器的测量温度与低温介质标准大气压下的温度之差小于5℃时，打开标定流量调节手阀，冷却供应管路手阀后的第二管路和竖直分管；
步骤2.4：当第二管路中温度传感器的测量温度与低温介质标准大气压下的温度之差小于5℃，且低温介质在供应管路中压力≤0.05Mpa时，关闭标定流量调节手阀，打开第二隔离阀，当低温介质从收集容器、隔离管路和快速回收容器排空后，实现低温介质原位标定***的预冷。
本发明与现有技术相比具有以下有益效果。
一、本发明采用的一种低温推进剂火箭发动机的流量计标定***，采用 了多容器对称结构力平衡方式，多个收集容器采用完全对称结构，在管道的拐弯处设置力平衡补偿器，可以将转弯处的管道力转化为力平衡补偿器拉杆内的内力，并且在力平衡补偿器拉杆上安装有测力传感器，可以对比测量各个力平衡补偿器的对称性，作为各个水平管出现力不对称时的原位修正；同时在供应管路上设置多个力平衡式波纹管(波纹补偿器)，该波纹管可以有效减少由于供应管路内部压力升高，管路产生的轴向力对收集容器的称重产生影响。
二、本发明采用的一种低温推进剂火箭发动机的流量计标定***，每个收集容器均通过力平衡补偿器形成的对称结构，解决在收集容器水平方向产生的侧向力，尤其是4个收集容器的对称结构，可以很好的消除水平管内压造成的影响，进而可以有效消除每个容器中低温介质少量气化造成的附加应力。
三、本发明采用的一种低温推进剂火箭发动机的流量计标定***，采用悬挂式承载结构，每个容器下方均设置有高精度称重单元，其中称重装置可先平衡容器的自身重量，进而可以将测力传感器更换为小量程的，实现进入容器的低温介质的高精度称重，消除基础零位，提高称重精度；同时每个容器实现全封闭设置，且采用真空夹层进行保温，避免出现由于温度升高造成低温介质挥发的现象。
四、本发明采用的一种低温推进剂火箭发动机的流量计标定***，通过采用低温介质排气***，可在标定参考流量计之前，将***中低温介质挥发产生的气体排放出去，避免***出口处的憋压，进而参考流量计可以长时间安全标定，增加了参考流量计计算数据的总量，可以提高参考流量计的平均 流量计算方法的精度。
五、本发明采用的一种低温推进剂火箭发动机的流量计标定方法，通过提前使用低温介质预冷低温介质原位标定***，并通过称重装置对容器进行原位标定，避免了温度差对低温介质的质量变化的影响，进而提高了容器原位标定的精度。容器原位标定和标定参考流量计阶段均不需要安装液位计，避免了液位计使用时的局限性。
六、本发明采用的一种低温推进剂火箭发动机的流量计标定方法，通过对称重传感器进行原位标定，可以消除容器、管路预冷收缩引起的附加力的作用，使称重传感器测量值更能真实表征介质质量。
附图说明
图1为本发明低温推进剂火箭发动机的流量计标定***的结构示意图。
图2为本发明低温推进剂火箭发动机的流量计标定***中称重单元的结构示意图。
图中：
1-容器；101-排气阀。
2-容器加注单元，21-回收阀门，22-波纹管补偿器，23-加注接口，24-加注过滤器，25-加注手阀；
3-容器箱底波纹补偿器，4-第一隔离阀，5-容器水平段波纹补偿器，6-过滤器，7-参考流量计，8-中部波纹补偿器，9-标定流量调节手阀，91-竖直主管，92-水平管，99-标定气动阀，100-竖直分管；
10-力平衡补偿器，11-收集容器，111-液位计，12-隔离管路，13-第二隔离阀，14-快速回收容器，15-称重加注回收单元，16-回收单元，17-自动排气 阀，18-手动排气阀；
31-底座，32-测力传感器，33-动平台，34-支撑架，35-支撑杆，36-杠杆，37-挂链，38-砝码，39-排液阀。
具体实施方式
下面将结合本发明的实施例和附图，对本发明的技术方案进行清楚、完整地描述，显然，所描述的实施例并非对本发明的限制。
如图1和图2所示，本实施例中的一种低温推进剂火箭发动机的流量计标定***，包括依次连接的容器加注单元2、容器1、供应管路、称重单元、快速回收容器14、回收单元16，以及称重加注回收单元15；
所述容器加注单元2用于连接槽车和容器1；所述供应管路包括任意位置设置的至少一个温度传感器和至少一个压力传感器，以及依次管路连接的容器箱底波纹补偿器3、第一隔离阀4、容器水平段波纹补偿器5、过滤器6、参考流量计7、中部波纹补偿器8、标定流量调节手阀9、竖直主管91和4个圆周均布的水平管92；第一隔离阀4的进口接容器1的出口，所述竖直主管91的出口与4个水平管92的进口分别连接，对应的4个水平管92呈十字分布；
如图2所示，所述称重单元包括4个竖直分管100、4个收集容器11和4个称重装置；4个竖直分管分别通过力平衡补偿器10与相应的水平管92连通；4个竖直分管分别设置在相应收集容器11的正上方；4个收集容器11的下方对应设置有称重装置，所述称重装置用于收集容器11中增量液体的称重；
所述收集容器11的出口通过隔离管路12和第二隔离阀13与快速回收容器14的进口连通，所述收集容器11的出口处设置有排液阀39，通过手动控 制排液阀39的开关，将收集容器11中的低温介质排放至称重加注回收单元15或回收单元16。
所述称重加注回收单元15用于连接槽车和收集容器11；
所述回收单元用于连接快速回收容器14和槽车。
所述称重装置包括称重组件和均布在称重组件上的两个平衡组件；
所述称重组件包括从下至上依次设置的底座31、两个测力传感器32、动平台33和支撑架34；两个测力传感器32均匀布设在动平台33下台面的下方，且测力传感器32的敏感面与动平台33下台面之间间隙设置或接触设置，所述支撑架34安装在动平台33的正中部，用于支撑对应的收集容器11；
两个平衡组件对称设置在动平台33的两侧，所述平衡组件包括设置在底座31上的支撑杆35、铰接在支撑杆35上的杠杆36，以及挂链37、砝码38；
所述杠杆36的内侧端通过挂链37与动平台33连接，其外侧端挂设有所述砝码38。
由于容器1的重量较重，如果直接使用测力传感器32对其重量进行测量，由于测力传感器32的量程较大，以50m 3容器为例，大约需要4个100kN以上，相对误差也比较大。因此在平台四周设置有4个杠杆式力平衡装置，通过设置合适的砝码38，可以将容器吊起，随着阀门的增多，容器在测力传感器32上的重量逐渐减少，比较理想的状态下测力传感器32上容器的重量可以为0，实际使用中一般控制在100kg以内，此时可以将测力传感器更换为小量程的，比如4个5kN级别的。通过该结构，可以实现进入容器的低温介质的高精度称重。
所述容器加注单元2包括加注接口23、与加注接口连接的加注管路和并 接在加注管路上的回收管路，所述加注管路沿低温介质加注方向上依次设置加注手阀25和加注过滤器24，所述回收管路沿低温介质回收方向上依次设置回收阀门21和波纹管补偿器22，所述加注接口23通过软管与槽车相连接，槽车设置在容器加注单元2附近。加注管路的低温介质出口与容器1的底部进口连通，容器1的底部出口通过供应管路与收集容器11的进口相连通，收集容器11的出口通过隔离管路12与快速回收容器14相连通，隔离管路12采用力隔离软管，所述力隔离软管上设置有第二隔离阀13。
所述称重加注回收单元15与容器加注单元2结构相同，所述称重加注回收单元15用于向收集容器11加注和回收低温介质，所述回收单元16包括通过管路依次连接的回收阀门、波纹管补偿器和加注接口，所述回收单元16用于将低温介质回收至槽车中。
本实施例中，平衡补偿器10采用角式力平衡补偿器，角式力平衡补偿器的拉杆上装有测力传感器，所述收集容器11为全封闭真空夹层容器；所述快速回收容器14该容器放置在较低的位置，可以采用地埋形式。
为了实现容器原位标定完毕后低温介质的长时间高安全性排放，本发明还可在每个收集容器11上增加一套排气***，包括第一排气管路和第二排气管路，第一排气管路和第二排气管路的进口均与其中一个收集容器11相连通，其出口均与外部的气体净化***相连；第一排气管路包括自动排气阀17，第二排气管路包括手动排气阀18。在标定参考流量计之前，可通过控制自动排气阀17打开，对收集容器11出口处***易燃气体进行排放。当标定参考流量计完成后，可打开手动排气阀18对收集容器11中的多余***易燃气体进行排放。
本发明还可只在其中一个收集容器11上安装排气***，由于4个收集容器11通过竖直主管91相互连通，进而可将所有收集容器11中的易燃气体进行排放。
同时在标定流量调节手阀9上并联有标定气动阀99，在标定参考流量计时，通过外部控制单元控制标定气动阀将供应管路中的低温介质的定量排放至称重加注回收单元，进而可多次记录同一时间段中低温介质下降的体积。
本实施还提供一种低温推进剂火箭发动机的流量计标定方法，包括以下步骤：
步骤1：称重单元原位标定
步骤1.1：称重加注回收单元15向收集容器11加注低温介质，当每个收集容器11中的液位计111显示加注液位均到达70％以上，且收集容器11中的低温介质温度＜5℃时，将收集容器11中的低温介质回收至快速回收容器14；
步骤1.2：记录测力传感器32的零位和称重装置上砝码38总质量m 总；
步骤1.3：根据测力传感器的使用范围，在每个杠杆36上均卸载预设质量m 0的砝码，记录测力传感器32的输出值V和剩余砝码的质量m，在此基础上，再卸载预设质量m 0的砝码，记录测力传感器32的输出值V和剩余砝码的质量m，如此进行5次卸载质量为m 0的砝码，总共记录5组数据；
上述预设质量m 0参考测力传感器的量程，一般存在下述对应关系m 0＝F/5g，其中F为测力传感器最大量程，g为重力加速度。
步骤1.4：重复步骤1.3两次，共获取15组数据，对记录的15组数据进行最小二乘法拟合，得到V和(m 总-m)的对应关系，完成称重单元的原位标 定；
步骤2：预冷低温介质原位标定***
步骤2.1：称重加注回收单元15向收集容器11加注低温介质，收集容器11中的加注液位均到达40％以上。同时，容器加注单元2向容器1加注低温介质，低温介质槽车通过增压将低温介质依次从加注过滤器24及加注手阀25进入到容器1，加注的过程中需确保容器1的顶部排气阀101处于打开状态，以保证当低温介质进入容器1后气化气体可及时排出，容器1内部不会产生过高的压力，使容器1的加注液位均到达70％以上，实现收集容器11和容器1的预冷；
步骤2.2：当收集容器11和容器1中低温介质温度均＜5℃时，打开第一隔离阀4，关闭标定流量调节手阀9，用低温介质冷却供应管路手阀9之前的第一管路，并同时打开第二隔离阀13，将收集容器11中的低温介质泄出；
步骤2.3：当第一管路中的温度传感器的测量温度与低温介质标准大气压下的温度之差小于5℃时，(以液氧为例，其标准大气压下为-183℃，要求相关管道的测量温度低于-178℃)，此时第一管路全部冷透后，容器1无比较严重的排气现象。打开标定流量调节手阀9，冷却供应管路手阀9后的第二管路和竖直分管，并依据供应管路的第二管路和竖直分管100的冷态情况进行流量调节；
步骤2.4：当第二管路中温度传感器的测量温度与低温介质标准大气压下的温度之差小于5℃，且低温介质在供应管路中压力≤0.05Mpa时，关闭标定流量调节手阀9，打开第二隔离阀13，当低温介质从收集容器11、隔离管路12和快速回收容器14排空后，实现低温介质原位标定***的预冷。
步骤3：容器原位标定
步骤3.1：关闭标定流量调节手阀9和第二隔离阀13，并打开第一隔离阀4，容器加注单元2对容器1加注到需标定的最高液位；
步骤3.2：按照容器1需要标定的液位下降高度，逐渐打开标定流量调节手阀9，将容器1中的低温介质缓慢排放至收集容器11(缓慢排放可确保每次按预定量排放，一般以10min完成一次排放为宜)，使用称重装置对每个收集容器11进行称重，计算容器1中每个液位下降高度对应的容积，重复至少一次，完成容器1的标定；例如当容器1液氧下降一定高度，比如10cm，对进入收集容器11的低温介质进行称重，比如称重后的重量为114kg。
每次称重完成后，均打开第二隔离阀13将称重后的低温介质从收集容器11中排出，可排放至快速回收容器14，若快速回收容器14液位过高，可使用回收单元16将其泄出。
由于***进行了前面的多个预冷步骤，***已经处在和低温介质基本一致的温度条件下，因此其蒸发量非常小，和水标定的情况下基本一致。依据液位下降10cm的介质重量为114kg，因此该收集容器11的此段截面的容积为0.1m 3。每次称重完毕后，都使用第二隔离阀13将称重后的低温介质排放至快速回收容器14。若快速回收容器14液位过高，可使用回收单元16将其泄出。
通过以上步骤，可以获取容器1中每个等高度段(例如以10cm作为单位高度段)对应的容积，进而完成了容器1的原位标定。
步骤4：标定参考流量计
步骤4.1：关闭第二隔离阀13，或拆除隔离管路12及其下游管路，使收集容器11中的低温介质只能从称重加注回收单元15排出；
关闭第一隔离阀4和标定流量调节手阀9，容器加注单元2对容器1加注到需标定的最高液位；
步骤4.11：将低温介质排气***连接在收集容器11上，通过外部控制单元打开自动排气阀17，排放***中低温介质挥发产生的气体，当***中的压力≤0.1MPa时，关闭自动排气阀17；
步骤4.2：打开第一隔离阀4和标定气动阀99，使低温介质依次通过供应管路、收集容器11后从称重加注回收单元15排出，多次记录同一时间段容器1中低温介质下降的体积，并计算出供应管路该段时间的平均流量，用平均流量来标定参考流量计7的流量。
标定时按预计时间进行一段时间的低温介质排放，然后利用测量到的数据进行计算完成标定。例如，在排放过程中在放液过程中从5-15S液位下降了20cm流量计的转动圈数为100转，依据前面的标定结果，这20cm标定的容器分别是0.1m 3及0.11m 3因此5-15s的排放容器为0.21m 3，流量计每转动一圈的容积是0.0021m 3。
本实施例中通过采用低温介质排气***，可在标定参考流量计之前，将***中低温介质挥发产生的气体排放出去，含气体的低温介质排放量小，安全可靠。可以实现低温介质长时间的排放标定，针对平均流量的标定算法可较大的提高标定精度。
以上所述仅为本发明的实施例，并非对本发明保护范围的限制，凡是利用本发明说明书及附图内容所作的等效结构变换，或直接或间接运用在其他相关的技术领域，均包括在本发明的专利保护范围内。

Claims (10)

  1. 一种低温推进剂火箭发动机的流量计标定***，其特征在于：
    包括依次连接的容器加注单元(2)、容器(1)、供应管路、称重单元、快速回收容器(14)、回收单元(16)，以及称重加注回收单元(15)；
    所述容器加注单元(2)用于连接槽车和容器(1)；
    所述供应管路包括任意位置设置的至少一个温度传感器和至少一个压力传感器，以及依次管路连接的第一隔离阀(4)、参考流量计(7)、标定流量调节手阀(9)、竖直主管(91)和N个圆周均布的水平管(92)；其中，2≤N≤6；第一隔离阀(4)的进口接容器(1)的出口，所述竖直主管(91)的出口与N个水平管(92)的进口分别连接；
    所述称重单元包括N个竖直分管(100)、N个收集容器(11)和N个称重装置；N个竖直分管分别通过力平衡补偿器(10)与相应的水平管(92)连通；N个竖直分管分别设置在相应收集容器(11)的正上方；N个收集容器(11)的下方对应设置有称重装置，所述称重装置用于收集容器(11)中增量液体的称重；
    所述收集容器(11)的出口通过隔离管路(12)和第二隔离阀(13)与快速回收容器(14)的进口连通；
    所述称重加注回收单元(15)用于连接槽车和收集容器(11)；
    所述回收单元用于连接快速回收容器(14)和槽车；
    所述称重装置包括称重组件和均布在称重组件上的至少两个平衡组件；
    所述称重组件包括从下至上依次设置的底座(31)、至少两个测力传感器(32)、动平台(33)和支撑架(34)；至少两个测力传感器(32)均匀布设 在动平台(33)下台面的下方，且测力传感器(32)的敏感面与动平台(33)下台面之间间隙设置或接触设置，所述支撑架(34)安装在动平台(33)的正中部，用于支撑对应的收集容器(11)；
    所述平衡组件包括设置在底座(31)上的支撑杆(35)、铰接在支撑杆(35)上的杠杆(36)，以及挂链(37)、砝码(38)；
    所述杠杆(36)的内侧端通过挂链(37)与动平台(33)连接，其外侧端挂设有所述砝码(38)。
  2. 根据权利要求1所述的低温推进剂火箭发动机的流量计标定***，其特征在于：
    所述平衡组件设置有两个，且对称设置在动平台(33)的两侧。
  3. 根据权利要求1或2所述的低温推进剂火箭发动机的流量计标定***，其特征在于：
    所述收集容器(11)设置有4个，对应的4个水平管(92)呈十字分布。
  4. 根据权利要求3所述的低温推进剂火箭发动机的流量计标定***，其特征在于：
    还包括低温介质排气***，所述低温介质排气***包括至少两条排气管路，所述排气管路的进口均与至少一个收集容器(11)相连通，其出口均与外部的气体净化***相连；其中一条排气管路上设置有自动排气阀(17)，通过外部控制单元控制自动排气阀(17)将收集容器(11)中的气体排出，其余排气管路上设置有手动排气阀(18)；
    所述标定流量调节手阀(9)上并联有标定气动阀(99)，通过外部控制单元控制标定气动阀(99)将供应管路中的低温介质的排放至称重加注回收 单元(15)。
  5. 根据权利要求4所述的低温推进剂火箭发动机的流量计标定***，其特征在于：
    所述容器加注单元(2)包括加注接口(23)、与加注接口连接的加注管路和并接在加注管路上的回收管路，所述加注管路沿低温介质加注方向上依次设置加注手阀(25)和加注过滤器(24)，所述回收管路沿低温介质回收方向上依次设置回收阀门(21)和波纹管补偿器(22)，所述加注接口(23)通过软管与槽车相连接；
    所述称重加注回收单元(15)与容器加注单元(2)结构相同，所述称重加注回收单元(15)用于向收集容器(11)加注和回收低温介质，所述回收单元(16)包括通过管路依次连接的回收阀门、波纹管补偿器和加注接口，用于将低温介质回收至槽车中。
  6. 根据权利要求5所述的低温推进剂火箭发动机的流量计标定***，其特征在于：
    所述平衡补偿器(10)采用角式力平衡补偿器，角式力平衡补偿器的拉杆上装有测力传感器。
  7. 根据权利要求6所述的一种低温推进剂火箭发动机的流量计标定***，其特征在于：
    所述供应管路沿着低温介质输送方向还设置有容器箱底波纹补偿器(3)、容器水平段波纹补偿器(5)、过滤器(6)和中部波纹补偿器(8)；
    所述收集容器(11)为全封闭真空夹层容器。
  8. 一种低温推进剂火箭发动机的流量计标定方法，其特征在于，包括以 下步骤：
    步骤1：称重单元原位标定
    步骤1.1：称重加注回收单元(15)向收集容器(11)加注低温介质，当每个收集容器(11)中的加注液位均到达70％以上，且收集容器(11)中的低温介质温度＜5℃时，将收集容器(11)中的低温介质回收至快速回收容器(14)；
    步骤1.2：记录测力传感器(32)的零位和称重装置上砝码(38)总质量m 总；
    步骤1.3：根据测力传感器(32)的使用范围，在每个杠杆(36)上均卸载预设质量m 0的砝码，记录测力传感器(32)的输出值V和剩余砝码的质量m，在此基础上，再卸载预设质量m 0的砝码，记录测力传感器32的输出值V和剩余砝码的质量m，如此进行M次卸载质量为m 0的砝码，总共记录M组数据，M≥5，其中，m 0＝F/Mg，F为测力传感器最大量程，g为重力加速度；
    步骤1.4：重复步骤1.3 K次，K≥2，对记录的((K+1)×M)组数据进行最小二乘法拟合，得到V和(m 总-m)的对应关系，完成称重单元的原位标定；
    步骤2：预冷低温介质原位标定***
    用低温介质依次预冷收集容器(11)和容器(1)、供应管路手阀(9)之前的第一管路、冷却供应管路手阀(9)后的第二管路和竖直分管(100)；要求前一个预冷区域的温度与低温介质标准大气压下的温度之差小于5℃时再进行下一个预冷区域的预冷；
    当第二管路和竖直分管(100)冷却完成后，关闭标定流量调节手阀(9)， 将标定流量调节手阀(9)下游的管路***进行排空，实现低温介质原位标定***的预冷；
    步骤3：容器原位标定
    步骤3.1：关闭第二隔离阀(13)，并打开第一隔离阀(4)，容器加注单元(2)对容器(1)加注；
    步骤3.2：按照容器(1)需要标定的液位下降高度，逐渐打开标定流量调节手阀(9)，将容器(1)中的低温介质缓慢排放至收集容器(11)，使用称重装置对每个收集容器(11)进行称重，计算容器(1)中每个液位下降高度对应的容积，重复至少一次，完成容器(1)的标定；
    每次称重完成后，均打开第二隔离阀(13)将称重后的低温介质从收集容器(11)中排出；
    步骤4：标定参考流量计
    步骤4.1：关闭第二隔离阀(13)，或拆除隔离管路(12)及其下游管路；
    关闭第一隔离阀(4)和标定流量调节手阀(9)，容器加注单元(2)对容器(1)进行加注；
    步骤4.2：打开第一隔离阀(4)和标定气动阀(99)，使低温介质依次通过供应管路、收集容器(11)后从称重加注回收单元(15)排出，多次记录同一时间段容器(1)中低温介质下降的体积，并计算出供应管路该段时间的平均流量，用平均流量来标定参考流量计(7)的流量。
  9. 根据权利要求8所述的一种低温推进剂火箭发动机的流量计标定方法，其特征在于：
    在步骤4.1和步骤4.2之间，还包括步骤4.11：将低温介质排气***连接 在收集容器(11)上，通过外部控制单元打开自动排气阀(17)，排放***中低温介质挥发产生的气体；当***中的压力≤0.1MPa时，关闭自动排气阀(17)。
  10. 根据权利要求8或9所述的低温推进剂火箭发动机的流量计标定方法，其特征在于：
    步骤2中预冷低温介质原位标定***，具体如下：
    步骤2.1：称重加注回收单元(15)向收集容器(11)加注低温介质，同时，容器加注单元(2)向容器(1)加注低温介质，其中收集容器(11)中的加注液位均到达40％以上，容器(1)的加注液位到达70％以上，实现收集容器(11)和容器(1)的预冷；
    步骤2.2：当收集容器(11)和容器(1)中低温介质温度均＜5℃时，打开第一隔离阀(4)，关闭标定流量调节手阀(9)，用低温介质冷却供应管路手阀(9)之前的第一管路，并同时打开第二隔离阀(13)，将收集容器(11)中的低温介质泄出；
    步骤2.3：当第一管路中的温度传感器的测量温度与低温介质标准大气压下的温度之差小于5℃时，打开标定流量调节手阀(9)，冷却供应管路手阀(9)后的第二管路和竖直分管(100)；
    步骤2.4：当第二管路中温度传感器的测量温度与低温介质标准大气压下的温度之差小于5℃，且低温介质在供应管路中压力≤0.05Mpa时，关闭标定流量调节手阀(9)，打开第二隔离阀(13)，当低温介质从收集容器(11)、隔离管路(12)和快速回收容器(14)排空后，实现低温介质原位标定***的预冷。
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Families Citing this family (4)

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Publication number Priority date Publication date Assignee Title
CN114088169B (zh) * 2021-11-09 2023-08-04 浙江浙能富兴燃料有限公司 一种气压驱动的双向质量法液氢流量标准装置
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CN114087539B (zh) * 2021-11-09 2023-08-25 浙江浙能技术研究院有限公司 一种基于动静态称重法的液氢流量标准装置
CN114440133A (zh) * 2021-12-17 2022-05-06 河南平高电气股份有限公司 用于sf6充气、放气回收装置的监测模块及流量计纠偏方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2001215145A (ja) * 2000-01-31 2001-08-10 Tokiko Techno Kk 流量計校正システム
CN202974416U (zh) * 2012-11-28 2013-06-05 丹东贝特自动化工程仪表有限公司 质量法液体流量标准装置的电子称标准器装置
CN107131931A (zh) * 2017-06-06 2017-09-05 西安航天动力试验技术研究所 姿控发动机高温推进剂稳态流量原位校准装置及校准方法
CN107941307A (zh) * 2017-11-10 2018-04-20 西安航天动力试验技术研究所 一种常规大型液体发动机推进剂流量现场校准***及方法
CN110231173A (zh) * 2019-05-31 2019-09-13 西安航天动力试验技术研究所 一种微小流量供应测量装置
CN111397699A (zh) * 2020-02-16 2020-07-10 西安航天动力试验技术研究所 一种称重测量装置、流量计校验***及方法

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3212318A (en) * 1962-04-30 1965-10-19 United Aircraft Corp Calibration device
US7055366B2 (en) * 2004-05-21 2006-06-06 Upchurch Scientific, Inc. Flow sensor calibration methods and apparatus
CN104634409B (zh) * 2015-02-06 2019-03-26 中国运载火箭技术研究院 一种5m级贮箱容积标定装备及方法
CN106124006B (zh) * 2016-06-16 2019-02-19 日照海达尔加气设备有限公司 一种高精度低温流量计检测***及其方法
CN107631786A (zh) * 2017-09-04 2018-01-26 中国人民解放军63729部队 一种火箭加注量称重计量装置
CN110057614A (zh) * 2019-05-14 2019-07-26 山东华盛天同标准技术服务有限公司 一种净水机净水量自动称量装置及其使用方法
CN111256787A (zh) * 2020-03-05 2020-06-09 中国人民解放军63729部队 一种发射场地面加注***流量计在线高精度标定方法

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2001215145A (ja) * 2000-01-31 2001-08-10 Tokiko Techno Kk 流量計校正システム
CN202974416U (zh) * 2012-11-28 2013-06-05 丹东贝特自动化工程仪表有限公司 质量法液体流量标准装置的电子称标准器装置
CN107131931A (zh) * 2017-06-06 2017-09-05 西安航天动力试验技术研究所 姿控发动机高温推进剂稳态流量原位校准装置及校准方法
CN107941307A (zh) * 2017-11-10 2018-04-20 西安航天动力试验技术研究所 一种常规大型液体发动机推进剂流量现场校准***及方法
CN110231173A (zh) * 2019-05-31 2019-09-13 西安航天动力试验技术研究所 一种微小流量供应测量装置
CN111397699A (zh) * 2020-02-16 2020-07-10 西安航天动力试验技术研究所 一种称重测量装置、流量计校验***及方法

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP4155689A4 *

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