CN109307598B - Fault identification pulse working condition engine propellant flow dual-mode measuring method and device - Google Patents

Fault identification pulse working condition engine propellant flow dual-mode measuring method and device Download PDF

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CN109307598B
CN109307598B CN201811335749.6A CN201811335749A CN109307598B CN 109307598 B CN109307598 B CN 109307598B CN 201811335749 A CN201811335749 A CN 201811335749A CN 109307598 B CN109307598 B CN 109307598B
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propellant
flow
engine
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sensor
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CN109307598A (en
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王开厅
王明迪
朱晓骅
庄杰
谢龙
沈锡江
梁健
俞春生
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Shanghai Institute of Space Propulsion
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Abstract

The invention provides a dual-mode measuring device for propellant flow of an engine under fault identification pulse working conditions, wherein a function realization auxiliary unit is used for matching propellant flow measurement and controlling a circulation pipeline of a propellant; the parameter detection module is used for measuring characteristic parameters in the propellant flowing process and calculating the propellant flow value through the characteristic parameters; the cylinder supporting member comprises an outer cylinder and an inner cylinder, the outer cylinder is used for sealing a pressurized gas space, and the inner cylinder is used for storing propellant; the peripheral component is used for guaranteeing the flow measurement stability of the propellant; the barrel supporting member is connected with the function realization auxiliary unit through a propellant liquid outlet pipe, and the propellant flows between the inner barrel and the function realization auxiliary unit through the propellant liquid outlet pipe. The flow measurement under the propellant pulse working condition is realized, the characteristics of dual-mode measurement, good reliability, high stability, fault identification and the like are realized, and the high-precision measurement requirement of the engine on the flow can be met.

Description

Fault identification pulse working condition engine propellant flow dual-mode measuring method and device
Technical Field
The invention relates to the technical field of fault identification, sensor technology, measurement control and high-precision flow measurement of a liquid rocket engine, in particular to a fault identification pulse working condition engine propellant flow dual-mode measurement method and device.
Background
The propellant flow directly reflects the performance parameters of the engine, so the propellant flow 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.
Patent document CN101737199A discloses a pressure drop type rocket engine liquid propellant conveying system, belonging to the field of rocket engine conveying systems. The conveying system comprises a storage tank (1), an electric explosion valve (2), a throttling hole (3), a flow control valve (4), a pressure increasing valve (5), a filling valve (6), a connecting pipeline and an electric explosion valve control circuit. The operation gas of the flow control valve (4) is the gas in the storage tank (1); the flow control valve is in a closed state before being started; the flow control valve (4) is started through the electric explosion valve (2), the flow can be controlled after the flow control valve (4) is started, when the pressure of the storage tank (2) is reduced, the valve core (8) is controlled to move through the pressure of the storage tank (2), the opening degree of the valve is increased, the throttling area of the valve is adjusted, the purpose of stabilizing the flow is achieved, the throttling hole can prevent the valve from being opened accidentally, and the reliability of a system is improved. The above system does not solve the problem of instability of the flow rate of the propellant when influenced by external factors such as temperature, pressure, etc.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a dual-mode measurement method and device for the propellant flow of the engine under the fault identification pulse working condition.
The invention provides a dual-mode measuring device for the propellant flow of a fault recognition pulse working condition engine, which comprises a function realization auxiliary unit, a parameter detection module, a cylinder body supporting member and a peripheral component, wherein the function realization auxiliary unit is connected with the parameter detection module; the function realization auxiliary unit is used for controlling a circulation pipeline of the propellant in cooperation with propellant flow measurement; the parameter detection module is used for measuring characteristic parameters in the propellant flowing process and calculating the propellant flow value through the characteristic parameters; the cylinder supporting member comprises an outer cylinder and an inner cylinder, the outer cylinder is used for sealing a pressurized gas space, and the inner cylinder is used for storing propellant; the peripheral component is used for guaranteeing the flow measurement stability of the propellant; the barrel supporting member is connected with the function realization auxiliary unit through a propellant liquid outlet pipe, and the propellant flows between the inner barrel and the function realization auxiliary unit through the propellant liquid outlet pipe.
Preferably, the characteristic parameters comprise the internal scene, pressure, flow, liquid level, temperature and propellant concentration of the device, and the dual-mode flow measurement of a volume method and a weighing method is realized.
Preferably, the parameter detection module mainly comprises a pressure sensor, a force sensor, a temperature sensor, a liquid level sensor and a propellant concentration sensor; the first pressure sensor, the force sensor, the temperature sensor and the propellant concentration sensor are arranged on the outer cylinder body, and the liquid level sensor is arranged in the inner cylinder body; the temperature sensor is used for detecting a temperature value and obtaining the density of the propellant according to the corresponding relation between the temperature value and the density; the propellant concentration sensor can detect the propellant concentration of the pressurized gas in the outer cylinder, and the evaporation capacity of the propellant can be calculated by combining the measurement parameters of the first pressure sensor and the liquid level sensor; the force sensor can detect the reduction amount of the propellant in the barrel in unit time, and can obtain high-precision propellant flow parameters through correction of evaporation amount.
Preferably, the function realization auxiliary unit mainly comprises a test run storage container and a container pressurization control valve; the test run storage container is used for storing the propellant, the container pressurization control valve is used for pressurizing the test run storage container, and the pressurized propellant flows into the inner cylinder body from the test run storage container.
Preferably, the peripheral component mainly comprises a gas reverse spray head, a pressurization electromagnetic valve, a liquid path electromagnetic valve, a filter, a manual liquid outlet valve, a first transverse damper and a second transverse damper; the gas reverse sprayer and the pressurization electromagnetic valve are used for controlling the pressure of the outer barrel, and the pressurization electromagnetic valve can pressurize or release the pressure of the outer barrel; the liquid path electromagnetic valve, the filter and the manual liquid outlet valve are used for controlling the circulation of the propellant; the first transverse damper and the second transverse damper are arranged between the inner wall of the outer cylinder and the outer wall of the inner cylinder, and vibration of the inner cylinder caused by outflow of propellant under the pulse working condition of the engine can be restrained.
Preferably, the upper part of the gas reverse spray head is of a hemispherical dense-hole structure, pressurized gas flows out of the upper hemispherical dense-hole structure, and the pressurized gas flow does not disturb the weight change measurement of the propellant in the inner cylinder body.
Preferably, the inner surface of the inner cylinder body is subjected to high-precision machining, so that high surface smoothness can be achieved, and cylindricity shape deviation is reduced.
The invention provides a dual-mode measurement method for engine propellant flow under fault identification pulse working conditions, which comprises the following steps:
calculating the mass flow rate of the propellant per unit time: mass flow rate Q per unit time of propellantmYCalculated using the following formula:
QmY＝ρT×QVY
Figure GDA0002387357910000031
where ρ isTRecording the density of the propellant at the temperature corresponding to the detection temperature value of the temperature sensor; qVYIs expressed as the volume flow per unit time, LVYAnd (3) recording the parameter change value of the liquid level sensor (17) in unit time, and recording the D as the inner circle diameter of the inner cylinder body (22), calculating the evaporation amount of the propellant in unit time, namely calculating the evaporation amount ξ of the propellant in unit time by using the following formula:
ξ＝δ×QVY
wherein δ is the content of propellant in a unit volume of propellant vapor; the weighing method comprises the following calculation steps: first mass flow Q of propellant obtained by weighingBalanceComprises the following steps:
Qbalance＝QL-ξ
Wherein Q isLRecording the parameter change value as the parameter change value of the force sensor in unit time;
calculating by a volume method: second mass flow rate Q of propellant obtained by volumetric methodBodyComprises the following steps:
Qbody＝QmY-ξ
Weighing method and volume method mean value meterCalculating: taking the mean value Q of parameters obtained by two flow measurement methods, namely weighing method and volume method, of propellant mass flowQuality of food：
Figure GDA0002387357910000032
Preferably, the fault identification pulse working condition engine propellant flow dual-mode measuring method further comprises a flow alarming step;
setting the error of the engine flow measured by a weighing method and a volume method to be η, and performing flow alarm when the absolute value of Q isBalance-QBodyWhen the flow measurement parameter is greater than η, alarm feedback is carried out.
Compared with the prior art, the invention has the following beneficial effects:
1. the propellant flow measurement in the engine test process is carried out by adopting a dual-mode measurement method in the same device, so that the stability and the reliability of the propellant flow measurement are improved, and the high-precision measurement requirement of the engine on the flow can be met;
2. the pulse working state real-time feedback and fault recognition are carried out, the automation level of flow measurement is improved, the generation of invalid and wrong flow data in the engine test process is effectively prevented, the test cost is saved, and the quality of test data is improved;
3. the method can realize high-precision measurement of the pulse flow, feed back and identify faults of the flow measurement state of the device, adopts a mass method and a volume method to perform pulse flow dual-mode measurement, 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 diagram of the apparatus;
fig. 2 is a propellant flow measurement supply schematic.
The figures show that:
Figure GDA0002387357910000041
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 relates to a dual-mode measuring device for engine propellant flow under fault identification pulse working conditions. The device comprises a function realization auxiliary unit, a parameter detection module, a cylinder body supporting member and a peripheral assembly. The function realization auxiliary unit is matched with the device to realize the flow measurement function of the propellant. The high-precision measurement of the propellant flow, the flow measurement working state feedback and the fault identification are completed through the organic combination of the parameter detection module and other units. The test run storage container 28, the container pressurization control valve 29, the pressure sensor 30, the second pressure gauge 31, the container bottom valve 32, the test run main valve 33, the test run control valve 34, the device filling control valve 35 and the engine 36 form a function realization auxiliary unit; the explosion-proof camera 2, the pressure sensor 5, the force sensor 6, the first pressure gauge 11, the temperature sensor 13, the liquid level sensor 17 and the propellant concentration sensor 27 form a parameter detection module; the outer cylinder 1, the outer cylinder flange 10, the outer cylinder base 24 and the inner cylinder 22 form a cylinder supporting member; the gas reverse spray head 3, the pressurization electromagnetic valve 4, the liquid path electromagnetic valve 7, the filter 8, the manual liquid outlet valve 9, the explosion-proof illuminating lamp 12, the first cleaning liquid inlet 14, the first manual cleaning valve 15, the first transverse damper 16, the propellant liquid outlet pipe 18, the blow-off valve 19, the blow-off pipe 20, the second transverse damper 23, the second manual cleaning valve 25 and the second cleaning liquid inlet 26 form a peripheral component. The invention aims to realize stable, accurate and continuous measurement of the flow under the propellant pulse working condition.
The invention provides a dual-mode measuring device for the propellant flow of a fault recognition pulse working condition engine, which comprises a function realization auxiliary unit, a parameter detection module, a cylinder body supporting member and a peripheral component, wherein the function realization auxiliary unit is connected with the parameter detection module; the function realization auxiliary unit is used for controlling a circulation pipeline of the propellant 21 in cooperation with propellant flow measurement; the parameter detection module is used for measuring characteristic parameters in the propellant flowing process and calculating the propellant flow value through the characteristic parameters; the cylinder supporting member comprises an outer cylinder 1 and an inner cylinder 22, wherein the outer cylinder 1 is used for sealing a pressurized gas space, and the inner cylinder 22 is used for storing a propellant 21; the peripheral component is used for guaranteeing the flow measurement stability of the propellant; the cartridge support member is connected to the function enabling auxiliary unit via a propellant outlet 18, and propellant 21 flows between the inner cartridge 22 and the function enabling auxiliary unit via the propellant outlet 18.
Specifically, the characteristic parameters comprise the internal scene, pressure, flow, liquid level, temperature and propellant concentration of the device, and the dual-mode flow measurement of a volume method and a weighing method is realized.
Specifically, the parameter detection module mainly comprises a pressure sensor 5, a force sensor 6, a temperature sensor 13, a liquid level sensor 17 and a propellant concentration sensor 27; the first pressure sensor 5, the force sensor 6, the temperature sensor 13 and the propellant concentration sensor 27 are arranged on the outer cylinder body 1, and the liquid level sensor 17 is arranged in the inner cylinder body 22; the temperature sensor 13 is used for detecting a temperature value, the density of the propellant is obtained through the corresponding relation between the temperature value and the density, preferably, the temperature sensor 13 can obtain the density of the propellant at the corresponding temperature through detecting the temperature in the outer cylinder 1 in real time, the volume change of the propellant can be obtained through the related parameters of the liquid level sensor 17 and the inner cylinder 22, so that the flow parameter of the propellant is obtained, and the flow parameter is compared with the flow parameter obtained by a weighing method to feed back the working state. When the deviation is larger than a critical value, a fault alarm is carried out; the propellant concentration sensor 27 can detect the propellant concentration of the pressurized gas in the outer cylinder 1, and can calculate the evaporation capacity of the propellant 21 by combining the measurement parameters of the first pressure sensor 5 and the liquid level sensor 17 and the relevant parameters of the inner cylinder 22; the force sensor 6 can detect the reduction of the propellant in the cylinder 22 in unit time, and can obtain a propellant flow parameter with high precision through the correction of the evaporation amount.
Specifically, the function realization auxiliary unit mainly includes a trial run storage container 28, a container pressurization control valve 29;
the test run storage tank 28 stores the propellant 21, and the tank pressurization control valve 29 pressurizes the test run storage tank 28, so that the pressurized propellant 21 flows from the test run storage tank 28 into the inner cylinder 22.
Specifically, the peripheral components mainly comprise a gas reverse spray head 3, a pressurization electromagnetic valve 4, a liquid path electromagnetic valve 7, a filter 8, a manual liquid outlet valve 9, a first transverse damper 16 and a second transverse damper 23; the gas reverse spray head 3 and the pressurization electromagnetic valve 4 are used for controlling the pressure of the outer barrel 1, and the pressurization electromagnetic valve 4 can pressurize or release the pressure of the outer barrel 1; the liquid path electromagnetic valve 7, the filter 8 and the manual liquid outlet valve 9 are used for controlling the circulation of the propellant 21; the first transverse damper 16 and the second transverse damper 23 are arranged between the inner wall of the outer cylinder 1 and the outer wall of the inner cylinder 22, so that vibration of the inner cylinder 22 caused by outflow of the propellant 21 under the pulse working condition of the engine can be inhibited, and the measured parameters are more stable and reliable.
Specifically, the upper part of the gas reverse nozzle 3 is of a hemispherical dense-hole structure, pressurized gas flows out of the upper hemispherical dense-hole structure, and the pressurized gas flow does not disturb the weight change measurement of the propellant 21 in the inner cylinder 22.
Specifically, the inner surface of the inner cylinder 22 is highly precisely machined, so that the inner cylinder can achieve high surface smoothness and small cylindricity shape deviation, has a function similar to a measuring cylinder, and is used for measuring the volume of the propellant. Preferably, the device also has an explosion-proof camera 2, said explosion-proof camera 2 being able to observe the operating conditions of the internal components.
The invention discloses a dual-mode measurement method for engine propellant flow under fault identification pulse working conditions, which comprises the following steps: calculating the mass flow rate of the propellant per unit time: mass flow rate Q per unit time of propellantmYCalculated using the following formula:
QmY＝ρT×QVY
Figure GDA0002387357910000061
where ρ isTRecording as the density of the propellant at the temperature corresponding to the detection temperature value of the temperature sensor 13; qVYIs expressed as the volume flow per unit time, LVYThe parameter change value of the liquid level sensor 17 in unit time is recorded, and D is the diameter of the inner circle of the inner cylinder body (22).
The evaporation amount per unit time of the propellant ξ is calculated by the following formula:
ξ＝δ×QVY
wherein δ is the content of propellant in a unit volume of propellant vapor; the weighing method comprises the following calculation steps: first mass flow Q of propellant obtained by weighingBalanceComprises the following steps:
Qbalance＝QL-ξ
Wherein Q isLRecording as the parameter change value of the force sensor 6 in unit time;
calculating by a volume method: second mass flow rate Q of propellant obtained by volumetric methodBodyComprises the following steps:
Qbody＝QmY-ξ
Calculating the mean value of a weighing method and a volume method: taking the mean value Q of parameters obtained by two flow measurement methods, namely weighing method and volume method, of propellant mass flowQuality of food：
Figure GDA0002387357910000071
Specifically, the dual-mode measurement method for the engine propellant flow under the fault identification pulse working condition further comprises a flow alarming step, wherein the flow alarming step comprises the step of setting the engine flow error measured by a weighing method and a volume method to be η, and when the absolute value of Q is greater than or equal toBalance-QBodyWhen the flow measurement parameter is greater than η, alarm feedback is carried out.
As shown in fig. 1 and 2, the function realization auxiliary unit is composed of a test run storage container 28, a container pressurization control valve 29, a pressure sensor 30, a pressure gauge 31, a container bottom valve 32, a test run main valve 33, a test run control valve 34, a device filling control valve 35, and an engine 36. The container pressurization control valve 29, the pressure sensor 30 and the pressure gauge 31 are all installed on the test run storage container 28, and the test run main valve 33, the test run control valve 34 and the device filling control valve 35 are installed on the propellant supply pipeline. The function realization auxiliary unit is mainly used for assisting in realizing the extrusion of the propellant in the flow dual-mode measuring body 22, and the propellant enters and exits along the propellant liquid outlet pipe 18. The cartridge support member comprises an outer cartridge 1, an outer cartridge flange 10, an outer cartridge base 24 and an inner cartridge 22. The cylinder supporting member is mainly used for mounting other components, and the outer cylinder 1 has a sealing effect on pressurized gas and discharges the inner cylinder. The peripheral components comprise a gas reverse spray head 3, a pressurizing electromagnetic valve 4, a liquid path electromagnetic 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 spray head 3 and the pressurizing electromagnetic valve 4 are arranged on a pressurizing pipeline, the liquid path electromagnetic valve 7, the filter 8 and the manual liquid outlet valve 9 are arranged on a liquid path pipeline, and the explosion-proof illuminating lamp 12, the first cleaning liquid inlet 14, the first manual cleaning valve 15, the first transverse damper 16, the blow-down valve 19, the blow-off pipe 20, the second transverse damper 23, the second manual cleaning valve 25 and the second cleaning liquid inlet 26 are arranged on the outer barrel body 1.
In the function realization auxiliary unit, the flow rate measuring device and the main propellant supply line are connected and disconnected by opening and closing the trial run control valve 34. The device fill control valve 35 allows propellant in the test run storage container 28 to be filled into the flow measurement device. The parameter detection module can realize the detection of the scene, pressure, flow, liquid level, temperature and propellant concentration inside the device. The cylinder supporting member is mainly used for mounting other components, the outer cylinder 1 has a sealing effect on pressurized gas, and the inner cylinder 22 stores propellant and is used for realizing the volume flow measurement of the propellant in a volume flow measurement method. The peripheral components play a role in ensuring the stability and reliability of the flow measurement function of the device, and the first transverse damper 16 and the second transverse damper 23 can restrain vibration of the inner cylinder 22 caused by propellant flow under the pulse working condition.
In a specific implementation process, in an initial state of the device, all valves are in a closed state, no propellant 21 is in the inner cylinder 22, the propellant 21 is filled in the test run storage container 28, the container pressurization control valve 29 is opened, the test run storage container 28 is pressurized, the container bottom valve 32, the device filling control valve 35, the test run control valve 34, the liquid path electromagnetic valve 7 and the manual liquid outlet valve 9 are opened, the propellant 21 is filled in the inner cylinder 22, and the pressurization electromagnetic valve 4 is opened to release the pressure of the outer cylinder 1. The filling amount of the propellant 21 is determined based on the display values of the force sensor 6 and the liquid level sensor 17. And when the filling amount meets the requirement, closing the device filling control valve 35, opening the pressurizing 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 performing an ignition test on the engine 36. The propellant 21 is discharged from the inner cylinder 22 to cause the force sensor 6 to detect a parameter change, the parameter change per unit time of the force sensor 6 being QL. The propellant 21 is discharged from the inner cylinder 22, the detection parameter of 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 can be obtained according to the detected temperature of the temperature sensor 13TFrom the dimensional parameters of the inner diameter of the inner cylinder 22, the mass flow per unit time is:
QmY＝ρT×QVY
Figure GDA0002387357910000081
the propellant concentration sensor 27 can detect the concentration of the propellant vapor in the outer cylinder 1, the pressure sensor 5 can obtain the pressure of the gas in the outer cylinder 1, and therefore, the content delta of the propellant in the unit volume of the propellant vapor, the evaporation amount of the propellant per unit time in the test process:
ξ＝δ×QVY
the mass flow rate of the engine test obtained by the weighing method was:
Qbalance＝QL-ξ
The mass flow rate of the engine test obtained by the volumetric method was:
Qbody＝QmY-ξ
In the test process, the mass flow of the propellant of the engine is measured and the mean value of parameters obtained by two flow measurement methods, namely a weighing method and a volume method:
Figure GDA0002387357910000082
the error of the engine flow measured by the weighing method and the volume method is set to be η when the absolute value of Q isBalance-QBodyWhen the flow measurement parameter is greater than η, the device gives an alarm and feeds back.
The invention realizes 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 identification of the measurement fault in the engine test process through the flow.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
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 dual-mode measurement device for engine propellant flow under fault identification pulse working conditions is characterized by comprising a function realization auxiliary unit, a parameter detection module, a cylinder body supporting member and a peripheral component;
the function realization auxiliary unit is used for controlling a circulation pipeline of the propellant (21) in cooperation with propellant flow measurement;
the parameter detection module is used for measuring characteristic parameters in the propellant flowing process and calculating the propellant flow value through the characteristic parameters;
the cylinder supporting member comprises an outer cylinder (1) and an inner cylinder (22), the outer cylinder (1) is used for sealing a pressurized gas space, and the inner cylinder is used for storing propellant;
the peripheral component is used for guaranteeing the flow measurement stability of the propellant;
the parameter detection module mainly comprises a pressure sensor (5), a force sensor (6), a temperature sensor (13), a liquid level sensor (17) and a propellant concentration sensor (27);
the first pressure sensor (5), the force sensor (6), the temperature sensor (13) and the propellant concentration sensor (27) are arranged on the outer cylinder body (1), and the liquid level sensor (17) is arranged in the inner cylinder body (22);
the temperature sensor (13) is used for detecting a temperature value and obtaining the density of the propellant according to the corresponding relation between the temperature value and the density;
the propellant concentration sensor (27) can detect the propellant concentration of the pressurized gas in the outer cylinder body (1), and the evaporation amount of the propellant (21) can be obtained by combining the measurement parameters of the first pressure sensor (5) and the liquid level sensor (17);
the force sensor (6) can detect the reduction amount of the propellant in the cylinder (22) in unit time, and can obtain a high-precision propellant flow parameter through the correction of the evaporation amount.
2. The dual-mode engine propellant flow measurement device with fault identification and pulse working conditions as claimed in claim 1, is characterized in that the characteristic parameters comprise internal scene, pressure, flow, liquid level, temperature and propellant concentration of the device, and dual-mode flow measurement of a volume method and a weighing method is realized.
3. The dual-mode measurement device for the propellant flow of the fault-recognition pulse operating condition engine according to claim 1, characterized in that the function-realization auxiliary unit mainly comprises a test run storage container (28), a container pressurization control valve (29);
the test run storage container (28) is used for storing the propellant (21), the container pressurization control valve (29) is used for pressurizing the test run storage container (28), and the pressurized propellant (21) flows into the inner cylinder body (22) from the test run storage container (28).
4. The dual-mode measurement device for the propellant flow of the engine under the fault recognition pulse working condition according to claim 1, wherein the peripheral components mainly comprise a gas reverse spray head (3), a pressurization electromagnetic valve (4), a liquid path electromagnetic valve (7), a filter (8), a manual liquid outlet valve (9), a first transverse damper (16) and a second transverse damper (23);
the gas reverse spray head (3) and the pressurization electromagnetic valve (4) are used for controlling the pressure of the outer barrel (1), and the pressurization electromagnetic valve (4) can pressurize or release the pressure of the outer barrel (1);
the liquid path electromagnetic valve (7), the filter (8) and the manual liquid outlet valve (9) are used for controlling the circulation of the propellant (21);
the first transverse damper (16) and the second transverse damper (23) are arranged between the inner wall of the outer cylinder body (1) and the outer wall of the inner cylinder body (22), and can inhibit vibration of the inner cylinder body (22) caused by outflow of the propellant (21) under the pulse working condition of the engine.
5. The dual-mode measurement device for the propellant flow of the fault-recognition pulse operating condition engine as claimed in claim 4, wherein the upper part of the gas reverse nozzle (3) is of a hemispherical dense-hole structure, pressurized gas flows out of the upper hemispherical dense-hole structure, and the pressurized gas flow does not disturb the measurement of the weight change of the propellant (21) in the inner cylinder (22).
6. The dual-mode measurement device for the propellant flow of the fault-identification pulse working condition engine as claimed in claim 1, wherein the inner surface of the inner cylinder (22) is subjected to high precision machining, so that high surface smoothness can be achieved, and cylindricity shape deviation is reduced.
7. A dual-mode measurement method for engine propellant flow under fault identification pulse working conditions is characterized by comprising the following steps:
calculating the mass flow rate of the propellant per unit time: mass flow rate Q per unit time of propellantmYCalculated using the following formula:
QmY＝ρT×QVY
Figure FDA0002387357900000021
where ρ isTRecording the density of the propellant at the temperature corresponding to the detection temperature value of the temperature sensor (13); qVYIs expressed as the volume flow per unit time, LVYRecording the parameter change value of the liquid level sensor (17) in unit time, and recording the D as the diameter of the inner circle of the inner cylinder body (22);
the evaporation amount per unit time of the propellant ξ is calculated by the following formula:
ξ＝δ×QVY
wherein δ is the content of propellant in a unit volume of propellant vapor; the weighing method comprises the following calculation steps: first mass flow Q of propellant obtained by weighingBalanceComprises the following steps:
Qbalance＝QL-ξ
Wherein Q isLRecording the parameter change value as the parameter change value of the force sensor (6) in unit time;
calculating by a volume method: second mass flow rate Q of propellant obtained by volumetric methodBodyComprises the following steps:
Qbody＝QmY-ξ
Calculating the mean value of a weighing method and a volume method: taking the mean value Q of parameters obtained by two flow measurement methods, namely weighing method and volume method, of propellant mass flowQuality of food：
Figure FDA0002387357900000031
8. The dual-mode measurement method for the propellant flow of the fault-identified pulse operating condition engine as claimed in claim 7, characterized by further comprising a flow alarm step;
setting the error of the engine flow measured by a weighing method and a volume method to be η, and performing flow alarm when the absolute value of Q isBalance-QBodyWhen the flow measurement parameter is greater than η, alarm feedback is carried out.
CN201811335749.6A 2018-11-11 2018-11-11 Fault identification pulse working condition engine propellant flow dual-mode measuring method and device Active CN109307598B (en)

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