CN109443781B - Self-feedback fault recognition engine pulse working condition flow measuring device and method - Google Patents

Self-feedback fault recognition engine pulse working condition flow measuring device and method Download PDF

Info

Publication number
CN109443781B
CN109443781B CN201811096482.XA CN201811096482A CN109443781B CN 109443781 B CN109443781 B CN 109443781B CN 201811096482 A CN201811096482 A CN 201811096482A CN 109443781 B CN109443781 B CN 109443781B
Authority
CN
China
Prior art keywords
propellant
outer cylinder
sensor
flow
valve
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201811096482.XA
Other languages
Chinese (zh)
Other versions
CN109443781A (en
Inventor
王开厅
王明迪
朱晓骅
庄杰
谢龙
沈锡江
梁健
俞春生
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shanghai Institute of Space Propulsion
Original Assignee
Shanghai Institute of Space Propulsion
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Shanghai Institute of Space Propulsion filed Critical Shanghai Institute of Space Propulsion
Priority to CN201811096482.XA priority Critical patent/CN109443781B/en
Publication of CN109443781A publication Critical patent/CN109443781A/en
Application granted granted Critical
Publication of CN109443781B publication Critical patent/CN109443781B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
    • G01F1/00—Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through a meter in a continuous flow
    • G01F1/76—Devices for measuring mass flow of a fluid or a fluent solid material
    • G01F1/86—Indirect mass flowmeters, e.g. measuring volume flow and density, temperature or pressure
    • 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

Landscapes

  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Measuring Volume Flow (AREA)
  • Testing Of Engines (AREA)

Abstract

The invention provides a flow measurement device and a flow measurement method for identifying pulse working conditions of an engine through self-feedback faults, wherein the flow measurement device comprises a detection unit and a function realization auxiliary unit, wherein the detection unit comprises a parameter detection module, a cylinder supporting member and a peripheral assembly; the detection unit connection function implements an auxiliary unit. The core of the invention is a parameter detection module, which is organically combined with other units to complete high-precision measurement of propellant flow, feedback of flow measurement working state and intelligent fault identification, and comprises an explosion-proof camera (2), a first pressure sensor (5), a force sensor (6), a first pressure gauge (11), a temperature sensor (13), a liquid level sensor (17) and a propellant concentration sensor (27). The invention adopts a mass method and a volume method to carry out dual-mode measurement, mutual correction and fault detection of the propellant flow, thereby improving the stability and reliability of the propellant flow detection.

Description

Self-feedback fault recognition engine pulse working condition flow measuring device and method
Technical Field
The invention relates to the field of fault identification, sensor technology and measurement control, in particular to a pulse working condition flow measuring device and method for an engine with self-feedback fault identification.
Background
In the technical field of high-precision measurement of the flow of the liquid rocket engine, the flow of the propellant directly reflects performance parameters of the engine, so that the flow of the propellant is an important detection index in the test process of the liquid rocket engine. The propellant pulse flow of the liquid rocket engine at the present stage is widely measured by a volume tube method, the measurement precision is influenced by the processing precision of the inner diameter of the volume tube, the volume tube is of a slender cylindrical structure, and the high-precision processing of the inner diameter is difficult. The density of the propellant is influenced by external factors such as temperature, pressure and the like, so that the flow measurement has large uncertainty. Therefore, there is a need to develop an engine propellant flow measurement device that addresses the above-mentioned problems.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a flow measuring device and a flow measuring method for identifying the pulse working condition of an engine through self-feedback faults.
According to one aspect of the invention, a self-feedback fault recognition engine pulse condition flow measurement device is provided and comprises a detection unit, wherein the detection unit comprises a parameter detection module, a cylinder supporting member and peripheral components.
Preferably, the cylinder support member comprises an outer cylinder, an outer cylinder flange, an inner cylinder, and a base; wherein, an accommodation space has been injectd jointly to outer barrel, outer barrel flange, interior barrel is located the accommodation space that outer barrel, outer barrel flange were injectd jointly, and interior barrel top has injectd first installation space jointly with outer barrel flange is inside, and interior barrel circumference has injectd second installation space jointly with outer barrel circumference, and pedestal mounting installs the pressure boost pipeline in the bottom of outer barrel on the outer barrel flange, and the pressure boost pipeline end is located first installation space.
Preferably, the peripheral component comprises a gas reverse sprayer, a pressurizing electromagnetic valve, a liquid path electromagnetic valve, a filter, a manual liquid outlet valve, an explosion-proof illuminating lamp, a first cleaning liquid inlet, a first manual cleaning valve, a first transverse damper, a propellant liquid outlet pipe, a blow-off valve, a blow-off pipe, a second transverse damper, a second manual cleaning valve and a second cleaning liquid inlet;
the gas reverse nozzle is arranged at the tail end of the pressurization pipeline and is positioned in the first installation space, and the pressurization electromagnetic valve is arranged on the pressurization pipeline and is positioned outside the flange of the outer cylinder body; the propellant liquid outlet pipe is arranged on the flange of the outer barrel in a penetrating way, one end of the propellant liquid outlet pipe is positioned in the inner barrel, and the other end of the propellant liquid outlet pipe is positioned outside the flange of the outer barrel; the manual liquid outlet valve, the liquid path electromagnetic valve and the filter are sequentially arranged on the propellant liquid outlet pipe positioned outside the outer cylinder flange; the explosion-proof illuminating lamp is arranged on the outer cylinder and is positioned in the first installation space; the first cleaning liquid inlet is connected with the outer cylinder through a first manual cleaning valve, and the second cleaning liquid inlet is communicated with a second manual cleaning valve and connected with the outer cylinder; the first transverse damper and the second transverse damper are both positioned in the second mounting space and are connected with the outer cylinder and the inner cylinder; the blow-off pipe is arranged at the bottom of the outer barrel body and is positioned in the base, and the blow-off valve is arranged on the blow-off pipe.
Preferably, the parameter detection module comprises an explosion-proof camera, a first pressure sensor, a force sensor, a first pressure gauge, a temperature sensor, a liquid level sensor and a propellant concentration sensor;
the anti-explosion camera is arranged on the outer barrel and is positioned in the first installation space; the first pressure sensor is arranged on the flange of the outer cylinder body, and the detection end of the first pressure sensor is positioned in the first installation space; the force sensor is arranged in the first installation space and connected with the outer cylinder flange and the inner cylinder; the first pressure gauge is arranged on the flange of the outer cylinder, and the detection end of the first pressure gauge is positioned in the first installation space; the temperature sensor and the propellant concentration sensor are both arranged on the outer cylinder body; the liquid level sensor is arranged on the inner cylinder body, and the detection end of the liquid level sensor is positioned in the inner cylinder body.
Preferably, the device comprises a function realization auxiliary unit, wherein the function realization auxiliary unit is connected with the detection unit; the function realization auxiliary unit comprises a test run storage container, a container pressurization control valve, a second pressure sensor, a second pressure gauge, a container bottom valve, a test run main valve, a test run control valve and a device filling control valve;
the device comprises a container pressurization control valve, a second pressure sensor, a pressure sensor and a pressure sensor, wherein the container pressurization control valve is installed on a pressurization pipeline at the top of a test run storage container; the second pressure gauge is arranged at the top of the test run storage container, one end of the second pressure gauge is positioned inside the test run storage container, and the other end of the second pressure gauge is positioned outside the test run storage container; the bottom of the test run storage container is connected with a propellant supply pipeline, a container bottom valve, a device filling control valve, a test run control valve and a test run main valve are sequentially arranged on the propellant supply pipeline, the test run main valve is connected with an engine, and the test run control valve is connected with a filter of a peripheral component.
Preferably, the hemispherical dense-hole structure of the gas reverse nozzle faces one side of the flange of the outer barrel, so that pressurized gas flows out from one side of the flange of the outer barrel, and the pressurized gas flow cannot disturb the measurement of the weight change of the propellant in the inner barrel; the first transverse damper and the second transverse damper can restrain vibration of the inner cylinder body caused by outflow of the propellant under the pulse working condition of the engine.
Preferably, the inner cylinder has a measuring cylinder function; the liquid level sensor is used for detecting the liquid level height of the propellant; the temperature sensor detects the temperature in the outer cylinder in real time to obtain the density of the propellant at the corresponding temperature, and then the volume variation of the propellant measured by the liquid level sensor and the inner cylinder is combined, so that the flow parameter of the propellant is obtained by a volume method and is corrected by the volatilization parameter of the propellant;
the volatilization amount of the propellant is calculated by the propellant concentration detected by the propellant concentration sensor and the combination of the first pressure sensor, the liquid level sensor and the related parameters of the inner cylinder body.
Preferably, the force sensor is used for detecting the mass change of the propellant in the barrel in unit time; and (4) obtaining a propellant flow parameter by a mass method through parameter correction of propellant volatilization.
Preferably, the propellant flow parameter obtained by the force sensor is dynamically compared with the flow parameter obtained by the liquid level sensor, the working state feedback is carried out, when the deviation is greater than a critical value, the fault alarm is carried out, and the automatic feedback of the flow state and the intelligent identification of the fault are realized.
According to another aspect of the invention, a self-feedback fault recognition engine pulse condition flow measurement method is providedRecording the parameter change value of the liquid level sensor in unit time as LVYRecording the mass parameter change value converted by the force sensor in unit time as QLThe temperature sensor detects the real-time temperature in the working process, and the density rho of the propellant at the corresponding temperature is obtained according to the detected temperature of the temperature sensorTThen, according to the size parameter D of the inner diameter of the inner cylinder body, the mass flow Q of the unit time is obtainedMYComprises the following steps:
QMY＝ρT×LVY×πD2/4
obtaining the content of the propellant in the saturated vapor of the propellant in unit volume according to the concentration of the saturated vapor of the propellant in the outer cylinder detected by the propellant concentration sensor and the pressure of the gas in the outer cylinder detected by the first pressure sensor, wherein the evaporation amount ξ of the propellant in unit time is as follows:
ξ＝×LVY×πD2/4
mass-derived engine-test mass flow QQuality of foodComprises the following steps:
Qquality of food＝QL-ξ
The mass flow Q for the engine test obtained by the volumetric method was:
Qbody＝QMY-ξ
Measuring mass flow of propellant of an engine by a mass method and a volume method, and measuring the mean value Q of parameters obtained by two flow measurement methods:
Q＝(Qquality of food+QBody)/2
The error of the engine flow measured by the mass method and the volume method is set to be η when the absolute value of Q isQuality of food-QBodyWhen the flow measurement parameter is greater than η, the device gives an alarm and feeds back.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention adopts a mass method and a volume method to carry out dual-mode measurement, mutual correction and fault detection of the propellant flow in the engine test process, can realize high-precision measurement of the pulse flow, improves the stability and reliability of propellant flow detection, and can realize continuous measurement.
2. The invention can perform real-time feedback and fault identification of the working state, improves the intelligent level of flow measurement, effectively prevents the generation of invalid and wrong flow data in the engine test process, saves the test cost, improves the quality of test data and has good engineering application value.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic structural diagram of a detecting unit according to the present invention.
Fig. 2 is a schematic structural diagram of the present invention.
The figures show that:
Figure GDA0002533674540000041
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The invention provides a self-feedback fault recognition engine pulse working condition flow measuring device which comprises a detection unit, wherein the detection unit comprises a parameter detection module, a cylinder supporting member and peripheral components. The core of the invention is a parameter detection module, and the high-precision measurement of the propellant flow, the feedback of the flow measurement working state and the intelligent fault identification are completed through the organic combination of the module and other units.
As shown in fig. 1, the cylinder support member includes an outer cylinder 1, an outer cylinder flange 10, an inner cylinder 22, a base 24; wherein, an accommodation space has been injectd jointly to outer barrel 1, outer barrel flange 10, interior barrel 22 is located outer barrel 1, the accommodation space that outer barrel flange 10 is injectd jointly, and interior barrel 22 top has injectd first installation space jointly with outer barrel flange 10 is inside, and interior barrel 22 circumference has injectd second installation space jointly with outer barrel 1 circumference, and base 24 installs in the bottom of outer barrel 1, installs the pressure boost pipeline on the outer barrel flange 10, and the pressure boost pipeline end is located first installation space. The cylinder supporting member is mainly used for mounting other components, the inner cylinder 22 stores the propellant 21, the outer cylinder 1 has a sealing effect on the pressurized gas, the propellant in the inner cylinder 22 is squeezed, and the volume flow measurement of the propellant is realized through a volume flow measurement method.
As shown in fig. 1, the peripheral components comprise a gas reverse spray nozzle 3, a pressurization solenoid valve 4, a liquid path solenoid valve 7, a filter 8, a manual liquid outlet valve 9, an explosion-proof illuminating lamp 12, a first cleaning liquid inlet 14, a first manual cleaning valve 15, a first transverse damper 16, a propellant liquid outlet pipe 18, a blow-down valve 19, a blow-down pipe 20, a second transverse damper 23, a second manual cleaning valve 25 and a second cleaning liquid inlet 26; the gas reverse nozzle 3 is arranged at the tail end of the pressurization pipeline and is positioned in the first installation space, and the pressurization electromagnetic valve 4 is arranged on the pressurization pipeline and is positioned outside the outer cylinder flange 10; the propellant liquid outlet pipe 18 is arranged on the outer cylinder flange 10 in a penetrating way, one end of the propellant liquid outlet pipe 18 is positioned inside the inner cylinder 22, and the other end of the propellant liquid outlet pipe 18 is positioned outside the outer cylinder flange 10; the manual liquid outlet valve 9, the liquid path electromagnetic valve 7 and the filter 8 are sequentially arranged on a propellant liquid outlet pipe 18 positioned outside the outer cylinder flange 10; the explosion-proof illuminating lamp 12 is arranged on the outer cylinder body 1 and is positioned in the first installation space; the first cleaning liquid inlet 14 is connected with the outer cylinder 1 through a first manual cleaning valve 15, and the second cleaning liquid inlet 26 is connected with the outer cylinder 1 through a second manual cleaning valve 25; the first transverse damper 16 and the second transverse damper 23 are both positioned in the second installation space and are connected with the outer cylinder body 1 and the inner cylinder body 22; the blow-off pipe 20 is arranged at the bottom of the outer cylinder body 1 and is positioned in the base 24, and the blow-off valve 19 is arranged on the blow-off pipe 20. The peripheral components play a role in ensuring the stability and reliability of the flow measurement function of the device. Preferably, the hemispherical dense-hole structure of the gas reverse nozzle 3 faces one side of the outer cylinder flange 10, so that the pressurized gas flows out from the side facing the outer cylinder flange 10, and the pressurized gas flow does not disturb the measurement of the weight change of the propellant in the inner cylinder 22; the first transverse damper 16 and the second transverse damper 23 can suppress vibration of the inner cylinder 22 caused by outflow of propellant under the pulse working condition of the engine, so that the measured parameters are more stable and reliable.
As shown in fig. 1, the parameter detection module includes an explosion-proof camera 2, a first pressure sensor 5, a force sensor 6, a first pressure gauge 11, a temperature sensor 13, a liquid level sensor 17, and a propellant concentration sensor 27; the anti-explosion camera 2 is arranged on the outer barrel 1 and is positioned in the first installation space; the first pressure sensor 5 is arranged on the outer cylinder flange 10, and the detection end of the first pressure sensor 5 is positioned in the first installation space; the force sensor 6 is arranged in the first installation space and is connected with the outer cylinder flange 10 and the inner cylinder 22; a first pressure gauge 11 is arranged on the outer cylinder flange 10, and a detection end of the first pressure gauge 11 is positioned in a first installation space; the temperature sensor 13 and the propellant concentration sensor 27 are both arranged on the outer cylinder body 1; the liquid level sensor 17 is installed on the inner cylinder 22, and the detection end of the liquid level sensor 17 is positioned in the inner cylinder 22. The parameter detection module can realize the detection of the scene, pressure, flow, liquid level, temperature and propellant concentration inside the device, and the explosion-proof camera 2 can observe the working state of the internal components.
As shown in fig. 2, the measuring apparatus further includes a function-implementing auxiliary unit, which is connected to the detecting unit; the function realization auxiliary unit comprises a test run storage container 28, a container pressurization control valve 29, a second pressure sensor 30, a second pressure gauge 31, a container bottom valve 32, a test run main valve 33, a test run control valve 34 and a device filling control valve 35; wherein, the container pressure-increasing control valve 29 is installed on the pressure-increasing pipeline at the top of the test run storage container 28, the second pressure sensor 30 is installed at the top of the test run storage container 28, one end of the second pressure sensor 30 is located inside the test run storage container 28, and the other end of the second pressure sensor 30 is located outside the test run storage container 28; the second pressure gauge 31 is arranged at the top of the test run storage container 28, one end of the second pressure gauge 31 is positioned inside the test run storage container 28, and the other end of the second pressure gauge 31 is positioned outside the test run storage container 28; the bottom of the test run storage container 28 is connected with a propellant supply pipeline, a container bottom valve 32, a device filling control valve 35, a test run control valve 34 and a test run main valve 33 are sequentially arranged on the propellant supply pipeline, the test run main valve 33 is connected with an engine 36, and the test run control valve 34 is connected with a filter 8 of a peripheral component. The function realization auxiliary unit is matched with the device to realize the propellant flow measurement function, the test run storage container 28 is filled with the propellant 21, the flow measurement device is connected with the main propellant supply pipeline in a switching mode through the opening and closing of the test run control valve 34, and the propellant in the test run storage container 28 can be filled into the flow measurement device through the device filling control valve 35.
Preferably, the inner cylinder 22 has a graduated cylinder function; the liquid level sensor 17 is used for detecting the liquid level height of the propellant; the temperature sensor 13 detects the temperature in the outer cylinder 1 in real time to obtain the density of the propellant at the corresponding temperature, and then the volume variation of the propellant measured by the liquid level sensor 17 and the inner cylinder 22 is combined to obtain the flow parameter of the propellant by a volume method and is corrected by the volatilization parameter of the propellant; the volatilization amount of the propellant is calculated by the concentration of the propellant detected by the propellant concentration sensor 27 and the relevant parameters of the first pressure sensor 5, the liquid level sensor 17 and the inner cylinder 22. Preferably, the force sensor 6 is arranged to detect the amount of change in mass of propellant in the barrel 22 per unit of time; and (4) obtaining a propellant flow parameter by a mass method through parameter correction of propellant volatilization. Preferably, the propellant flow parameter obtained by the force sensor 6 is dynamically compared with the flow parameter obtained by the liquid level sensor 17, the working state feedback is carried out, when the deviation is greater than a critical value, the fault alarm is carried out, and the automatic feedback of the flow state and the intelligent identification of the fault are realized.
The specific measurement method is as follows:
in the initial state all valves are closed, the inner cylinder 22 is empty of propellant 21 and the test run storage container 28 is filled with propellant 21. Opening a container pressurization control valve 29, pressurizing the test run storage container 28, and sequentially opening a container bottom valve 32, a device filling control valve 35, a test run control valve 34, a liquid path electromagnetic valve 7 and a manual liquid outlet valve 9 to fill the propellant 21 into the inner cylinder 22; opening the pressurizing electromagnetic valve 4 to perform pressure relief and air release on the outer cylinder 1; determining the filling amount of the propellant 21 according to the display values of the force sensor 6 and the liquid level sensor 17, closing the device filling control valve 35 when the filling amount meets the requirement, opening the pressurization electromagnetic valve 4 to pressurize the outer cylinder 1, opening the test run main valve 33, enabling the propellant 21 to flow out of the propellant liquid outlet pipe 18, and flowing into the engine 36 through the test run control valve 34 and the test run main valve 33 to carry out the ignition test of the engine 36; the opening of the booster solenoid valve 4 can be either boosted or deflated, mainly determined by the gas pressure of the external pipe.
The propellant 21 is discharged from the inner cylinder 22 to cause the change of the detection parameter of the force sensor 6, and the change value of the mass parameter converted by the force sensor 6 in unit time is QLThe propellant 21 is discharged from the inner cylinder 22, the parameter detected by the liquid level sensor 17 is changed, and the parameter change value of the liquid level sensor 17 in unit time is LVYThe temperature sensor 13 detects the real-time temperature in the working process, and the density rho of the propellant 21 at the corresponding temperature is obtained according to the detected temperature of the temperature sensor 13TThen, the mass flow rate Q per unit time is obtained according to the size parameter D of the inner diameter of the inner cylinder 22MYComprises the following steps:
QMY＝ρT×LVY×πD2/4
obtaining the content of the propellant in the saturated vapor of the propellant per unit volume according to the concentration of the saturated vapor of the propellant in the outer cylinder 1 detected by the propellant concentration sensor 27 and the pressure of the gas in the outer cylinder 1 detected by the first pressure sensor 5, wherein the evaporation amount ξ of the propellant per unit time is as follows:
ξ＝×LVY×πD2/4
mass-derived engine-test mass flow QQuality of foodComprises the following steps:
Qquality of food＝QL-ξ
Mass flow Q of an engine test obtained by volumetric methodBodyComprises the following steps:
Qbody＝QMY-ξ
Measuring mass flow of propellant of an engine by a mass method and a volume method, and measuring the mean value Q of parameters obtained by two flow measurement methods:
Q＝(Qquality of food+QBody)/2
The error of the engine flow measured by the mass method and the volume method is set to be η when the absolute value of Q isQuality of food-QBodyWhen the flow measurement parameter is greater than η, the device gives an alarm and feeds back.
According to the invention, in the engine test process, the high-precision measurement of the flow of the propellant under the pulse working condition, the real-time automatic feedback of the working state and the intelligent identification of the measurement fault are realized through the process.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.

Claims (8)

1. A self-feedback fault recognition engine pulse working condition flow measurement device is characterized by comprising a detection unit, wherein the detection unit comprises a parameter detection module, a cylinder supporting member and a peripheral assembly;
the cylinder supporting component comprises an outer cylinder (1), an outer cylinder flange (10), an inner cylinder (22) and a base (24); the outer cylinder body (1) and the outer cylinder body flange (10) jointly define an accommodating space, the inner cylinder body (22) is located in the accommodating space defined by the outer cylinder body (1) and the outer cylinder body flange (10), the top of the inner cylinder body (22) and the inside of the outer cylinder body flange (10) jointly define a first mounting space, the circumferential direction of the inner cylinder body (22) and the circumferential direction of the outer cylinder body (1) jointly define a second mounting space, the base (24) is mounted at the bottom of the outer cylinder body (1), the outer cylinder body flange (10) is provided with a pressurizing pipeline, and the tail end of the pressurizing pipeline is located in the first mounting space;
the parameter detection module comprises an explosion-proof camera (2), a first pressure sensor (5), a force sensor (6), a first pressure gauge (11), a temperature sensor (13), a liquid level sensor (17) and a propellant concentration sensor (27);
the anti-explosion camera (2) is arranged on the outer cylinder body (1) and is positioned in the first installation space; the first pressure sensor (5) is arranged on the outer cylinder flange (10), and the detection end of the first pressure sensor (5) is positioned in the first installation space; the force sensor (6) is arranged in the first installation space and is connected with the outer cylinder flange (10) and the inner cylinder (22); a first pressure gauge (11) is arranged on the outer cylinder flange (10), and a detection end of the first pressure gauge (11) is positioned in a first installation space; the temperature sensor (13) and the propellant concentration sensor (27) are both arranged on the outer cylinder body (1); the liquid level sensor (17) is arranged on the inner cylinder body (22), and the detection end of the liquid level sensor (17) is positioned in the inner cylinder body (22).
2. The self-feedback fault recognition engine pulse condition flow measuring device according to claim 1, wherein the peripheral components comprise a gas reverse spray head (3), a pressurization solenoid valve (4), a liquid path solenoid valve (7), a filter (8), a manual liquid outlet valve (9), an explosion-proof illuminating lamp (12), a first cleaning liquid inlet (14), a first manual cleaning valve (15), a first transverse damper (16), a propellant liquid outlet pipe (18), a blow-off valve (19), a blow-off pipe (20), a second transverse damper (23), a second manual cleaning valve (25) and a second cleaning liquid inlet (26);
the gas reverse nozzle (3) is arranged at the tail end of the pressurization pipeline and is positioned in the first installation space, and the pressurization electromagnetic valve (4) is arranged on the pressurization pipeline and is positioned outside the outer cylinder flange (10); the propellant liquid outlet pipe (18) is arranged on the outer cylinder flange (10) in a penetrating mode, one end of the propellant liquid outlet pipe (18) is located inside the inner cylinder (22), and the other end of the propellant liquid outlet pipe (18) is located outside the outer cylinder flange (10); the manual liquid outlet valve (9), the liquid path electromagnetic valve (7) and the filter (8) are sequentially arranged on a propellant liquid outlet pipe (18) positioned outside the outer cylinder flange (10); the explosion-proof illuminating lamp (12) is arranged on the outer cylinder body (1) and is positioned in the first installation space; the first cleaning liquid inlet (14) is connected with the outer cylinder body (1) through a first manual cleaning valve (15), and the second cleaning liquid inlet (26) is communicated with a second manual cleaning valve (25) and connected with the outer cylinder body (1); the first transverse damper (16) and the second transverse damper (23) are both positioned in the second mounting space and are connected with the outer cylinder body (1) and the inner cylinder body (22); the blow-off pipe (20) is arranged at the bottom of the outer barrel (1) and is positioned in the base (24), and the blow-off valve (19) is arranged on the blow-off pipe (20).
3. The pulse condition flow measuring device of the self-feedback fault recognition engine according to claim 1, comprising a function realization auxiliary unit, wherein the function realization auxiliary unit is connected with the detection unit; the function realization auxiliary unit comprises a test run storage container (28), a container pressurization control valve (29), a second pressure sensor (30), a second pressure gauge (31), a container bottom valve (32), a test run main valve (33), a test run control valve (34) and a device filling control valve (35);
the device comprises a container pressurization control valve (29), a second pressure sensor (30), a first pressure sensor and a second pressure sensor, wherein the container pressurization control valve (29) is installed on a pressurization pipeline at the top of a test run storage container (28), the second pressure sensor (30) is installed at the top of the test run storage container (28), one end of the second pressure sensor (30) is located inside the test run storage container (28), and the other end of the second pressure sensor (30) is located outside the test run storage container (28); the second pressure gauge (31) is arranged at the top of the test run storage container (28), one end of the second pressure gauge (31) is positioned inside the test run storage container (28), and the other end of the second pressure gauge (31) is positioned outside the test run storage container (28); the bottom of the test run storage container (28) is connected with a propellant supply pipeline, a container bottom valve (32), a device filling control valve (35), a test run control valve (34) and a test run main valve (33) are sequentially arranged on the propellant supply pipeline, the test run main valve (33) is connected with an engine (36), and the test run control valve (34) is connected with a filter (8) of a peripheral component.
4. The self-feedback failure recognition engine pulse condition flow measuring device according to claim 2, wherein the hemispherical dense-hole structure of the gas reverse nozzle (3) faces the outer cylinder flange (10) side, so that the pressurized gas flows out from the outer cylinder flange (10) side, and the pressurized gas flow does not disturb the measurement of the propellant weight change in the inner cylinder (22); the first transverse damper (16) and the second transverse damper (23) can restrain vibration of the inner cylinder (22) caused by outflow of propellant under the pulse working condition of the engine.
5. The self-feedback fault identification engine pulse regime flow measurement device of claim 1, wherein the inner cylinder (22) has a graduated cylinder function; the liquid level sensor (17) is used for detecting the liquid level height of the propellant; the temperature sensor (13) detects the temperature in the outer cylinder (1) in real time to obtain the density of the propellant at the corresponding temperature, and then the volume variation of the propellant measured by the liquid level sensor (17) and the inner cylinder (22) is combined to obtain the flow parameter of the propellant by a volume method and is corrected by the volatilization parameter of the propellant;
the volatilization amount of the propellant is calculated by the propellant concentration detected by the propellant concentration sensor (27) and the relevant parameters of the first pressure sensor (5), the liquid level sensor (17) and the inner cylinder body (22).
6. A self-feedback fault identifying engine pulse regime flow measurement apparatus according to claim 1 or 5, wherein the force sensor (6) is arranged to detect the amount of change in mass of propellant in the barrel (22) per unit time; and (4) obtaining a propellant flow parameter by a mass method through parameter correction of propellant volatilization.
7. The pulse condition flow measuring device of the self-feedback fault recognition engine according to claim 1, wherein a propellant flow parameter obtained by the force sensor (6) and a flow parameter obtained by the liquid level sensor (17) are dynamically compared, the working state feedback is carried out, and when the deviation is larger than a critical value, the fault alarm is carried out, so that the automatic feedback of the flow state and the intelligent recognition of the fault are realized.
8. A self-feedback fault recognition engine pulse condition flow measuring method is characterized in that the parameter change value of a liquid level sensor (17) in unit time is recorded as L by adopting the self-feedback fault recognition engine pulse condition flow measuring device of any one of claims 1 to 7VYRecording the mass parameter change value converted by the force sensor (6) in unit time as QLTemperature sensor (13) detectsThe real-time temperature in the working process is obtained according to the detection temperature of the temperature sensor (13) to obtain the density rho of the propellant (21) at the corresponding temperatureTThen, according to the size parameter D of the inner diameter of the inner cylinder (22), the mass flow rate Q of the unit time is obtainedMYComprises the following steps:
QMY＝ρT×LVY×πD2/4
and obtaining the content of the propellant in the saturated vapor per unit volume of the propellant according to the concentration of the saturated vapor of the propellant in the outer cylinder (1) detected by the propellant concentration sensor (27) and the pressure of the gas in the outer cylinder (1) detected by the first pressure sensor (5), wherein the evaporation amount ξ of the propellant per unit time is as follows:
ξ＝×LVY×πD2/4
mass-derived engine-test mass flow QQuality of foodComprises the following steps:
Qquality of food＝QL-ξ
Mass flow Q of an engine test obtained by volumetric methodBodyComprises the following steps:
Qbody＝QMY-ξ
Measuring mass flow of propellant of an engine by a mass method and a volume method, and measuring the mean value Q of parameters obtained by two flow measurement methods:
Q＝(Qquality of food+QBody)/2
The error of the engine flow measured by the mass method and the volume method is set to be η when the absolute value of Q isQuality of food-QBodyWhen the flow measurement parameter is greater than η, the device gives an alarm and feeds back.
CN201811096482.XA 2018-09-19 2018-09-19 Self-feedback fault recognition engine pulse working condition flow measuring device and method Active CN109443781B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201811096482.XA CN109443781B (en) 2018-09-19 2018-09-19 Self-feedback fault recognition engine pulse working condition flow measuring device and method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201811096482.XA CN109443781B (en) 2018-09-19 2018-09-19 Self-feedback fault recognition engine pulse working condition flow measuring device and method

Publications (2)

Publication Number Publication Date
CN109443781A CN109443781A (en) 2019-03-08
CN109443781B true CN109443781B (en) 2020-07-28

Family

ID=65532774

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201811096482.XA Active CN109443781B (en) 2018-09-19 2018-09-19 Self-feedback fault recognition engine pulse working condition flow measuring device and method

Country Status (1)

Country Link
CN (1) CN109443781B (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN203610384U (en) * 2013-05-28 2014-05-28 北京航天试验技术研究所 Liquid rocket engine testing pipeline cleaning device
JP6273487B2 (en) * 2013-07-12 2018-02-07 国立研究開発法人宇宙航空研究開発機構 Method and apparatus for measuring pulsating flow rate
CN104191176B (en) * 2014-08-25 2016-11-16 沈阳航天新光集团有限公司 The preparation method of cryogenic flow weighing container
CN107131931B (en) * 2017-06-06 2020-02-21 西安航天动力试验技术研究所 Attitude control engine high-temperature propellant steady-state flow in-situ calibration device and calibration method
CN107843330B (en) * 2017-12-08 2024-04-16 上海悟道机电设备有限公司 Flow weighing measurement device

Also Published As

Publication number Publication date
CN109443781A (en) 2019-03-08

Similar Documents

Publication Publication Date Title
JPS62223640A (en) System for detecting leakage in liquid storage tank
CN203643142U (en) A safety valve checking platform
CN109307598B (en) Fault identification pulse working condition engine propellant flow dual-mode measuring method and device
CN109083790A (en) A kind of injection rate measuring system and method based on Zeuch pressure magnetic method
CN108627222B (en) A kind of oil meter nucleus correcting system
CN110207976A (en) A kind of automobile-used breather valve intelligent type comprehensive test device of oil tank
JPH0121450B2 (en)
CN109443781B (en) Self-feedback fault recognition engine pulse working condition flow measuring device and method
CN111964851A (en) Aerostat valve airtightness detection system and detection method
JPH0510845A (en) Device for inspecting mobile storage tank for leakage
CN208831128U (en) A kind of distributive value electrical signal collection system based on Zeuch pressure magnetic method
CN109520849B (en) Container pressure tester and testing method thereof
CN209979168U (en) Engine gasket sealing performance test equipment
CN220136583U (en) Filter leakproofness micro-leakage detection device
RU1789865C (en) Device for measuring fuel consumption of internal combustion engine
CN209671185U (en) A kind of booster measurement device of oil tempera
JPH0132454B2 (en)
CN210690061U (en) 1N single-component thruster test system
CN112484940B (en) High-precision valve sealing performance detection device and detection method
CN107782484A (en) Flow resistance experimental provision
CN114483301B (en) Simple gas engine jet rule measuring method
CN210375568U (en) Gas flow detection device
RU2771653C1 (en) Device for measuring fuel consumption by an internal combustion engine
RU2098787C1 (en) Method for determination of integral leakage from closed space
JPS56150322A (en) Method and device for leakage inspection of storage tank

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant