CN109307598A - Fault identification pulse operation engine propellant flow rate bimodulus measurement method and device - Google Patents
Fault identification pulse operation engine propellant flow rate bimodulus measurement method and device Download PDFInfo
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- CN109307598A CN109307598A CN201811335749.6A CN201811335749A CN109307598A CN 109307598 A CN109307598 A CN 109307598A CN 201811335749 A CN201811335749 A CN 201811335749A CN 109307598 A CN109307598 A CN 109307598A
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
Abstract
The present invention provides a kind of self feed back intelligent troubles to identify that pulse operation engine propellant flow rate bimodulus measuring device, function realize that auxiliary unit for cooperating propellant flow rate to measure, controls the flow pipe of propellant；Parameter detection module is used to measure the characteristic parameter in propellant flow process, and obtains propellant flow rate value by calculation of characteristic parameters；Barrel support component includes outer barrel, inner cylinder, and the outer barrel is for closing pressurization gas space, and inner cylinder is for storing propellant；Peripheral assembly is for ensureing that propellant flow rate measures stability；Barrel support component realizes that auxiliary unit is connected with function by propellant outlet tube, and propellant is realized by propellant outlet tube in inner cylinder and function to be flowed between auxiliary unit.The measurement for realizing propellant pulse operation down-off has the characteristics that bimodulus measurement, good reliability, stability height, intelligent trouble identification, can satisfy high-acruracy survey requirement of the engine to flow.
Description
Technical field
The present invention relates to the flow high-precisions of fault identification, sensor technology, measurement control and liquid-propellant rocket engine
A kind of field of measuring technique, and in particular, to self feed back intelligent trouble pulse operation engine propellant flow rate bimodulus measurement dress
It sets.
Background technique
Propellant flow rate directly reacts the performance parameter of engine, and therefore, propellant flow rate is liquid-propellant rocket engine examination
Important Testing index during testing.The method that volume pipe is widely used in liquid-propellant rocket engine propellant pulse flow at this stage
Measure, measurement accuracy is influenced by volume bore machining accuracy, volume pipe be elongate cylinder structure, internal diameter it is high-precision
It is close to be machined with bigger difficulty.The density of propellant is influenced by external factor such as temperature, pressure, and flow measurement is caused to deposit
In biggish uncertainty.Therefore, it is necessary to develop a kind of engine propellant flow rate measuring device for being able to solve the above problem.
Patent document CN101737199A discloses a kind of liquid propellant conveying system of blow-down rocket engine, belongs to
Rocket engine transportation system field.The transportation system includes tank (1), electric blasting valve (2), throttle orifice (3), flow control valve
(4), pressure charging valve (5), fill valve (6), connecting line and electric detonation valve controling circuit.The manipulation gas of flow control valve (4) is tank
(1) interior gas；Flow control valve is in close state before activation；Start flow control valve (4) by electric blasting valve (2), flow
It can control flow after control valve (4) starting, when the decline of tank (2) pressure, transported by tank (2) pressure-control valve core (8)
It is dynamic, increase valve opening, control valve orifice size achievees the purpose that stability of flow, throttle orifice can prevent valve from surprisingly opening,
Increase system reliability.Above system does not simultaneously solve propellant when being influenced by external factor such as temperature, pressure, and flow is not
Stability problem.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of down pulse operating condition engine propellant streams
Measure bimodulus measurement method and device.
A kind of fault identification pulse operation engine propellant flow rate bimodulus measuring device provided according to the present invention, including
Function realizes auxiliary unit, parameter detection module, barrel support component and peripheral assembly；Function realizes auxiliary unit for cooperating
Propellant flow rate measurement, controls the flow pipe of propellant；Parameter detection module is used to measure the spy in propellant flow process
Parameter is levied, and propellant flow rate value is obtained by calculation of characteristic parameters；Barrel support component includes outer barrel, inner cylinder, described
Outer barrel is for closing pressurization gas space, and inner cylinder is for storing propellant；Peripheral assembly is for ensureing that propellant flow rate is surveyed
Measure stability；Barrel support component realizes that auxiliary unit is connected with function by propellant outlet tube, and propellant passes through propulsion
Agent outlet tube is realized in inner cylinder and function to be flowed between auxiliary unit.
Preferably, the characteristic parameter includes scene inside device, pressure, flow, liquid level, temperature and propellant concentration,
Realize the bimodulus flow measurement of volumetric method and weight method.
Preferably, parameter detection module mainly includes pressure sensor, force snesor, temperature sensor, liquid level sensor
With propellant concentration sensor；First pressure sensor, force snesor, temperature sensor and the setting of propellant concentration sensor exist
On outer barrel, liquid level sensor is arranged in inner cylinder；The temperature sensor for detecting temperature value, by temperature value with it is close
The corresponding relationship of degree obtains propellant density；The propellant concentration sensor is able to detect the propulsion of pressurization gas in outer barrel
The evaporation capacity of propellant can be calculated in conjunction with first pressure sensor, the measurement parameter of liquid level sensor in agent concentration；Institute
The reduction amount that force snesor is able to detect that propellant in unit time inner cylinder is stated, by the amendment of evaporation capacity, can be obtained
High-precision propellant flow rate parameter.
Preferably, the function realizes that auxiliary unit mainly includes test run hold-up vessel, vessel pressurization control valve；Test run storage
Container is deposited for storing propellant, vessel pressurization control valve for being pressurized to test run hold-up vessel, after pressurization propellant by
Test run hold-up vessel flows into inner cylinder.
Preferably, the peripheral assembly mainly include the reversed spray head of gas, boost electromagnetic valve, fluid path solenoid valve, filter,
Manual liquid outlet valve, the first lateral damper, the second lateral damper；The reversed spray head of gas, boost electromagnetic valve are for controlling outer cylinder
The pressure of body, boost electromagnetic valve can carry out pressurization or pressure release to outer barrel；Fluid path solenoid valve, filter and manual liquid outlet valve are used
In the circulation of control propellant；The inner wall and inner cylinder of outer barrel is arranged in first lateral damper, the second lateral damper
Between outer wall, it is able to suppress the vibration of inner cylinder caused by propellant flows out under engine impulse operating condition.
Preferably, the top of the reversed spray head of the gas is the close pore structure of hemispherical, and pressurization gas is close from upper hemispherical shape
Pore structure outflow, pressurized air stream will not measure the weight change of the propellant in inner cylinder and generate disturbance.
Preferably, the inner surface of the inner cylinder passes through high-accuracy processing, can reach surface best bright finish, reduces cylinder
Spend form variations.
A kind of fault identification pulse operation engine propellant flow rate bimodulus measurement method provided according to the present invention, including
Following steps:
The mass flow calculation step of the unit time of propellant: the mass flow Q of the unit time of corresponding propellantmYWith
Following formula calculates:
QmY=ρT×QVY
Wherein, ρTThe propellant density being denoted as at temperature corresponding to the detection temperature value of temperature sensor；QVYIt is denoted as unit
The parameter variation value of liquid level sensor in time；
The evaporation capacity of the unit time of propellant calculates step: the evaporation capacity ξ of the unit time of corresponding propellant is with following
Formula calculates:
ξ=δ × QVY
Wherein, δ is denoted as the content of propellant in unit volume propellant saturated vapor；
Weight method calculates step: by the first mass flow Q of the propellant that weight method obtainsClaimAre as follows:
QClaim=QL-ξ
Wherein, QLIt is denoted as the parameter variation value of unit time inner force sense device；
Volumetric method calculates step: by the second mass flow Q of the propellant that volumetric method obtainsBodyAre as follows:
QBody=QmY-ξ
Weight method and volumetric method mean value computation step: mass-flow rate of propellant takes the two kinds of flow measurements of weight method and volumetric method
The mean value Q of method parameters obtainedMatter:
QMatter=(QClaim+QBody)/2。
Preferably, fault identification pulse operation engine propellant flow rate bimodulus measurement method further includes flow alarm function step
Suddenly；
Flow alarm function step: the engine flow error of weight method and volumetric method measurement is set as η, as | QClaim+QBody| > η
When, flow measurement parameter is overproof, carries out alarm feedback.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, the propellant flow rate measurement during engine test is carried out using double mode measurement method in the same apparatus,
The stability and reliability for improving propellant flow rate detection can satisfy high-acruracy survey requirement of the engine to flow；
2, working condition Real-time Feedback and intelligent trouble identification are carried out, improves the intelligent level of flow measurement, effectively
Invalid, mistake data on flows generation during engine test is prevented, experimentation cost has been saved, has improved test data matter
Amount；
3, it can be realized the high-acruracy survey of pulse flow, and feedback and failure knowledge carried out to the flow measurement state of device
Not, the measurement of pulse flow bimodulus is carried out using mass method and volumetric method, there is good engineering application value.
Detailed description of the invention
Upon reading the detailed description of non-limiting embodiments with reference to the following drawings, other feature of the invention,
Objects and advantages will become more apparent upon:
Fig. 1 is schematic diagram of device；
Fig. 2 is propellant flow rate measuring principle figure.
It is shown in figure:
Specific embodiment
The present invention is described in detail combined with specific embodiments below.Following embodiment will be helpful to the technology of this field
Personnel further understand the present invention, but the invention is not limited in any way.It should be pointed out that the ordinary skill of this field
For personnel, without departing from the inventive concept of the premise, several changes and improvements can also be made.These belong to the present invention
Protection scope.
The present invention relates to a kind of self feed back intelligent troubles to identify pulse operation engine propellant flow rate bimodulus measuring device.
The device includes that function realizes auxiliary unit, parameter detection module, barrel support component and peripheral assembly.Function realizes that auxiliary is single
The member cooperation present apparatus realizes that propellant flow rate measures function.It is pushed away by parameter detection module and the organic assembling completion of other units
Into the high-acruracy survey of agent flux, flow measurement working condition feedback and intelligent fault identification.Wherein test run hold-up vessel 28, appearance
Device supercharger control valve 29, pressure sensor 30, second pressure gauge 31, container bottom valve 32, test run main valve 33, test run control valve 34,
Device filling control valve 35 and engine 36 constitute function and realize auxiliary unit；Explosion-proof video camera 2, pressure sensor 5, power pass
Sensor 6, first pressure gauge 11, temperature sensor 13, liquid level sensor 17 and propellant concentration sensor 27 constitute parameter inspection
Survey module；Outer barrel 1, outer barrel flange 10, outer cylinder pedestal 24 and inner cylinder 22 constitute barrel support component；Gas reversely sprays
First 3, boost electromagnetic valve 4, fluid path solenoid valve 7, filter 8, manual liquid outlet valve 9, explosion-proof illuminating lamp 12, the first filter washing water inlet
14, first manual purge valve 15, the first lateral damper 16, propellant outlet tube 18, blowdown valve 19, sewage pipe 20, second are horizontal
Peripheral assembly is constituted to damper 23, the second manual purge valve 25 and the second filter washing water inlet 26.The present invention is directed to realize to push away
Stabilization, accurate, test constantly into agent pulse operation down-off.
A kind of fault identification pulse operation engine propellant flow rate bimodulus measuring device provided according to the present invention, including
Function realizes auxiliary unit, parameter detection module, barrel support component and peripheral assembly；Function realizes auxiliary unit for cooperating
Propellant flow rate measurement, controls the flow pipe of propellant 21；Parameter detection module is for measuring in propellant flow process
Characteristic parameter, and propellant flow rate value is obtained by calculation of characteristic parameters；Barrel support component includes outer barrel 1, inner cylinder 22,
The outer barrel 1 is for closing pressurization gas space, and inner cylinder 22 is for storing propellant 21；Peripheral assembly is promoted for ensureing
Agent flux measures stability；Barrel support component realizes that auxiliary unit is connected with function by propellant outlet tube 18, promotes
Agent 21 is realized by propellant outlet tube 18 in inner cylinder 22 and function to be flowed between auxiliary unit.
Specifically, the characteristic parameter includes scene inside device, pressure, flow, liquid level, temperature and propellant concentration,
Realize the bimodulus flow measurement of volumetric method and weight method.
Specifically, parameter detection module mainly includes pressure sensor 5, force snesor 6, temperature sensor 13, liquid level biography
Sensor 17 and propellant concentration sensor 27；First pressure sensor 5, force snesor 6, temperature sensor 13 and propellant concentration
Sensor 27 is arranged on outer barrel 1, and liquid level sensor 17 is arranged in inner cylinder 22；The temperature sensor 13 is for detecting
Temperature value obtains propellant density by temperature value and the corresponding relationship of density, it is preferable that the temperature sensor 13 passes through reality
When detection outer barrel 1 in temperature, the propellant density under corresponding temperature can be obtained, by the phase of liquid level sensor 17 and inner cylinder 22
Propellant volume change can be obtained by closing parameter, to obtain the flow parameter of propellant, be compared with the flow parameter that weight method obtains,
Carry out working condition feedback.When deviation is greater than critical value, that is, carry out fault alarm；The propellant concentration sensor 27 can
The propellant concentration for detecting pressurization gas in outer barrel 1, in conjunction with first pressure sensor 5, the measurement parameter of liquid level sensor 17,
And the relevant parameter of inner cylinder 22 is combined, the evaporation capacity of propellant 21 can be calculated；The force snesor 6 is able to detect that
The reduction amount of propellant in unit time inner cylinder 22 can obtain high-precision propellant flow rate by the amendment of evaporation capacity
Parameter.
Specifically, the function realizes that auxiliary unit mainly includes test run hold-up vessel 28, vessel pressurization control valve 29；
Test run hold-up vessel 28 for storing propellant 21, vessel pressurization control valve 29 be used for test run hold-up vessel 28 into
Row pressurization, propellant 21 flows into inner cylinder 22 by test run hold-up vessel 28 after pressurization.
Specifically, the peripheral assembly mainly includes the reversed spray head 3 of gas, boost electromagnetic valve 4, fluid path solenoid valve 7, filtering
Device 8, manual liquid outlet valve 9, the first lateral damper 16, the second lateral damper 23；The reversed spray head 3 of gas, boost electromagnetic valve 4 are used
In the pressure of control outer barrel 1, boost electromagnetic valve 4 can carry out pressurization or pressure release to outer barrel 1；Fluid path solenoid valve 7, filter
8 and manual liquid outlet valve 9 be used to control the circulation of propellant 21；First lateral damper 16, the setting of the second lateral damper 23 exist
Between the inner wall of outer barrel 1 and the outer wall of inner cylinder 22, it is able to suppress caused by propellant 21 under engine impulse operating condition flows out
The vibration of inner cylinder 22, so that measurement parameter is more reliable and more stable.
Specifically, the top of the reversed spray head 3 of the gas is the close pore structure of hemispherical, and pressurization gas is close from upper hemispherical shape
Pore structure outflow, pressurized air stream will not measure the weight change of the propellant 21 in inner cylinder 22 and generate disturbance.
Specifically, the inner surface of the inner cylinder 22 pass through high-accuracy processing, can reach very high surface finish and compared with
Small column degree form variations, have the function of class graduated cylinder, carry out the cubing of propellant.Preferably, described device is also explosion-proof
Video camera 2, the explosion-proof video camera 2 can observe the working condition of internal component.
Disclosed a kind of fault identification pulse operation engine propellant flow rate bimodulus measurement method according to the present invention, including
Following steps: the mass flow calculation step of the unit time of propellant: the mass flow Q of the unit time of corresponding propellantmY
It is calculated with following formula:
QmY=ρT×QVY
Wherein, ρTThe propellant density being denoted as at temperature corresponding to the detection temperature value of temperature sensor 13；QVYIt is denoted as list
The parameter variation value of liquid level sensor 17 in the time of position；
The evaporation capacity of the unit time of propellant calculates step: the evaporation capacity ξ of the unit time of corresponding propellant is with following
Formula calculates:
ξ=δ × QVY
Wherein, δ is denoted as the content of propellant in unit volume propellant saturated vapor；
Weight method calculates step: by the first mass flow Q of the propellant that weight method obtainsClaimAre as follows:
QClaim=QL-ξ
Wherein, QLIt is denoted as the parameter variation value of unit time inner force sense device 6；
Volumetric method calculates step: by the second mass flow Q of the propellant that volumetric method obtainsBodyAre as follows:
QBody=QmY-ξ
Weight method and volumetric method mean value computation step: mass-flow rate of propellant takes the two kinds of flow measurements of weight method and volumetric method
The mean value Q of method parameters obtainedMatter:
QMatter=(QClaim+QBody)/2
Specifically, the fault identification pulse operation engine propellant flow rate bimodulus measurement method further includes flow alarm function
Step；Flow alarm function step: the engine flow error of weight method and volumetric method measurement is set as η, as | QClaim+QBody| when > η, stream
Measurement parameter is overproof, carries out alarm feedback.
As shown in Figure 1 and Figure 2, function realizes auxiliary unit by test run hold-up vessel 28, vessel pressurization control valve 29, pressure
Sensor 30, pressure gauge 31, container bottom valve 32, test run main valve 33, test run control valve 34, device filling control valve 35 and engine
36 compositions.Vessel pressurization control valve 29, pressure sensor 30, pressure gauge 31 are installed on test run hold-up vessel 28, test run master
Valve 33, test run control valve 34, device filling control valve 35 are mounted on propellant feed pipes.Function realizes that auxiliary unit is main
Effect is that the propellant that auxiliary realizes that flow bimodulus is surveyed in body 22 is squeezed, and propellant is passed in and out along propellant outlet tube 18 is gone out.
Barrel support component includes outer barrel 1, outer barrel flange 10, outer cylinder pedestal 24 and inner cylinder 22.Barrel support component is mainly used
It is installed in other components, outer barrel 1 plays sealing process to pressurization gas, and inner cylinder is discharged.Peripheral assembly includes that gas is reversed
Spray head 3, boost electromagnetic valve 4, fluid path solenoid valve 7, filter 8, manual liquid outlet valve 9, explosion-proof illuminating lamp 12, the first filter washing water inlet
14, first manual purge valve 15, the first lateral damper 16, propellant outlet tube 18, blowdown valve 19, sewage pipe 20, second are horizontal
To damper 23, the second manual purge valve 25 and the second filter washing water inlet 26.The reversed spray head 3 of gas, boost electromagnetic valve 4 are mounted on
On pressure piping, fluid path solenoid valve 7, filter 8 and manual liquid outlet valve 9 are mounted on influidic pipe road, explosion-proof illuminating lamp 12, first
The laterally damping of filter washing water inlet 14, first manual purge valve 15, the first lateral damper 16, blowdown valve 19, sewage pipe 20, second
Device 23, the second manual purge valve 25 and the second filter washing water inlet 26 are mounted on outer barrel 1.
Function realize auxiliary unit in, by the unlatching of test run control valve 34, close realize flow measurement device with
The on-off of main propellant supply line.Device fills control valve 35 can be by the repropellenting in test run hold-up vessel 28 to stream
In measuring device.Parameter detection module can realize scene inside device, pressure, flow, liquid level, temperature and propellant concentration
Detection.Barrel support component is mainly used for other component installations, and outer barrel 1 plays sealing process, inner cylinder 22 to pressurization gas
Propellant is stored, and for realizing the propellant volume flow measurement of volume flow measurement method.Peripheral assembly, which plays, ensures device
Flow measurement function-stable reliably acts on, and the first lateral damper 16, the second lateral damper 23 are able to suppress pulse operation
The vibration of inner cylinder 22 caused by lower propellant flows.
In the specific implementation process, under device original state, all valves are in closed state, in inner cylinder 22
Without propellant 21, it is filled with propellant 21 in test run hold-up vessel 28, vessel pressurization control valve 29 is opened, to test run hold-up vessel
28 are pressurized, and are opened container bottom valve 32, device filling control valve 35, test run control valve 34, fluid path solenoid valve 7 and are gone out liquid manually
Valve 9 fills propellant 21 into inner cylinder 22, opens boost electromagnetic valve 4 and carries out pressure release deflation to outer barrel 1.According to force snesor
6, the show value of liquid level sensor 17 determines the adding amount of propellant 21.After adding amount is met the requirements, device filling control is closed
Valve 35 processed is opened boost electromagnetic valve 4 and is pressurized to outer barrel 1, opens test run main valve 33, and propellant 21 is from propellant outlet tube
18 outflows, carry out 36 fire trial of engine.Propellant 21 is discharged from inner cylinder 22, can cause 6 detection parameters of force snesor
Variation, the parameter variation value of unit time inner force sense device 6 is QL.Propellant 21 is discharged from inner cylinder 22, level sensing
17 detection parameters of device can also change, and the parameter variation value of liquid level sensor 17 is Q in the unit timeVY, temperature sensor 13
Real-time temperature in the course of work is detected, according to the propellant under the available corresponding temperature of detection temperature of temperature sensor 13
21 density pT, it can be obtained further according to the dimensional parameters of 22 internal diameter of inner cylinder, the mass flow of unit time:
QmY=ρT×QVY
Propellant concentration sensor 27 can detecte the concentration of propellant saturated vapor in outer barrel 1, and pressure sensor 5 can
The pressure for obtaining gas in outer barrel 1 can obtain the content δ of propellant in unit volume propellant saturated vapor as a result, test process
In, the evaporation capacity of propellant unit time:
ξ=δ × QVY
By the mass flow for the engine test that weight method obtains are as follows:
QClaim=QL-ξ
By the mass flow for the engine test that volumetric method obtains are as follows:
QBody=QmY-ξ
The mass-flow rate of propellant of engine takes obtained by two kinds of flow-measuring methods of weight method and volumetric method during test
The mean value of parameter:
QMatter=(QClaim+QBody)/2
The engine flow error of weight method and volumetric method measurement is set as η, as | QClaim+QBody| when > η, flow measurement parameter
Overproof, device carries out alarm feedback.
During the present invention realizes engine test by above-mentioned process, the high-precision of the flow of propellant under pulse operation
The real time automatic feedback of measurement and working condition, measures the intelligent recognition of failure.
In the description of the present application, it is to be understood that term " on ", "front", "rear", "left", "right", " is erected at "lower"
Directly ", the orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is orientation based on the figure or position
Relationship is set, description the application is merely for convenience of and simplifies description, rather than the device or element of indication or suggestion meaning are necessary
It with specific orientation, is constructed and operated in a specific orientation, therefore should not be understood as the limitation to the application.
Specific embodiments of the present invention are described above.It is to be appreciated that the invention is not limited to above-mentioned
Particular implementation, those skilled in the art can make a variety of changes or modify within the scope of the claims, this not shadow
Ring substantive content of the invention.In the absence of conflict, the feature in embodiments herein and embodiment can any phase
Mutually combination.
Claims (9)
1. a kind of fault identification pulse operation engine propellant flow rate bimodulus measuring device, which is characterized in that including function reality
Existing auxiliary unit, parameter detection module, barrel support component and peripheral assembly；
Function realizes that auxiliary unit for cooperating propellant flow rate to measure, controls the flow pipe of propellant (21)；
Parameter detection module is used to measure the characteristic parameter in propellant flow process, and obtains propulsion by calculation of characteristic parameters
Agent flux value；
Barrel support component includes outer barrel (1), inner cylinder (22), and the outer barrel (1) is interior for closing pressurization gas space
Cylinder (22) is for storing propellant (21)；
Peripheral assembly is for ensureing that propellant flow rate measures stability；
Barrel support component realizes that auxiliary unit is connected with function by propellant outlet tube (18), and propellant (21) passes through propulsion
Agent outlet tube (18) is realized in inner cylinder (22) and function to be flowed between auxiliary unit.
2. fault identification pulse operation engine propellant flow rate bimodulus measuring device according to claim 1, feature
It is, the characteristic parameter includes scene inside device, pressure, flow, liquid level, temperature and propellant concentration, realizes volumetric method
With the bimodulus flow measurement of weight method.
3. fault identification pulse operation engine propellant flow rate bimodulus measuring device according to claim 1, feature
It is, parameter detection module mainly includes pressure sensor (5), force snesor (6), temperature sensor (13), liquid level sensor
(17) and propellant concentration sensor (27)；
First pressure sensor (5), force snesor (6), temperature sensor (13) and propellant concentration sensor (27) setting exist
On outer barrel (1), liquid level sensor (17) setting is in inner cylinder (22)；
The temperature sensor (13) is close by temperature value and the corresponding relationship of density acquisition propellant for detecting temperature value
Degree；
The propellant concentration sensor (27) is able to detect the propellant concentration of pressurization gas in outer barrel (1), in conjunction with first
The measurement parameter of pressure sensor (5), liquid level sensor (17), can be calculated the evaporation capacity of propellant (21)；
The force snesor (6) is able to detect that the reduction amount of propellant in unit time inner cylinder (22), by evaporation capacity
Amendment, can obtain high-precision propellant flow rate parameter.
4. fault identification pulse operation engine propellant flow rate bimodulus measuring device according to claim 1, feature
It is, the function realizes that auxiliary unit mainly includes test run hold-up vessel (28), vessel pressurization control valve (29)；
For storing propellant (21), vessel pressurization control valve (29) is used for test run hold-up vessel test run hold-up vessel (28)
(28) it is pressurized, propellant (21) flows into inner cylinder (22) by test run hold-up vessel (28) after pressurization.
5. fault identification pulse operation engine propellant flow rate bimodulus measuring device according to claim 1, feature
It is, the peripheral assembly mainly includes the reversed spray head of gas (3), boost electromagnetic valve (4), fluid path solenoid valve (7), filter
(8), manual liquid outlet valve (9), the first lateral damper (16), the second lateral damper (23)；
The reversed spray head of gas (3), boost electromagnetic valve (4) are used to control the pressure of outer barrel (1), and boost electromagnetic valve (4) can be right
Outer barrel (1) carries out pressurization or pressure release；
Fluid path solenoid valve (7), filter (8) and manual liquid outlet valve (9) are used to control the circulation of propellant (21)；
First lateral damper (16), the second lateral damper (23) setting outer barrel (1) inner wall and inner cylinder (22)
Between outer wall, it is able to suppress the vibration of inner cylinder (22) caused by propellant (21) flows out under engine impulse operating condition.
6. fault identification pulse operation engine propellant flow rate bimodulus measuring device according to claim 5, feature
It is, the top of the reversed spray head of gas (3) is the close pore structure of hemispherical, and pressurization gas is from the close pore structure stream of upper hemispherical shape
Out, pressurized air stream will not measure the weight change of the propellant (21) in inner cylinder (22) and generate disturbance.
7. intelligent trouble according to claim 1 identifies pulse operation engine propellant flow rate bimodulus measuring device,
It is characterized in that, the inner surface of the inner cylinder (22) passes through high-accuracy processing, can reach surface best bright finish, reduces cylindricity
Form variations.
8. a kind of fault identification pulse operation engine propellant flow rate bimodulus measurement method, which is characterized in that including walking as follows
It is rapid:
The mass flow calculation step of the unit time of propellant: the mass flow Q of the unit time of corresponding propellantmYWith following
Formula calculates:
QmY=ρT×QVY
Wherein, ρTThe propellant density being denoted as at temperature corresponding to the detection temperature value of temperature sensor (13)；QVYIt is denoted as unit
The parameter variation value of liquid level sensor (17) in time；
The evaporation capacity of the unit time of propellant calculates step: the evaporation capacity ξ following formula of the unit time of corresponding propellant
It calculates:
ξ=δ × QVY
Wherein, δ is denoted as the content of propellant in unit volume propellant saturated vapor；
Weight method calculates step: by the first mass flow Q of the propellant that weight method obtainsClaimAre as follows:
QClaim=QL-ξ
Wherein, QLIt is denoted as the parameter variation value of unit time inner force sense device (6)；
Volumetric method calculates step: by the second mass flow Q of the propellant that volumetric method obtainsBodyAre as follows:
QBody=QmY-ξ
Weight method and volumetric method mean value computation step: mass-flow rate of propellant takes two kinds of flow-measuring methods of weight method and volumetric method
The mean value Q of parameters obtainedMatter:
QMatter=(QClaim+QBody)/2。
9. fault identification pulse operation engine propellant flow rate bimodulus measurement method according to claim 8, feature
It is, further includes flow alarm function step；
Flow alarm function step: the engine flow error of weight method and volumetric method measurement is set as η, as | QClaim+QBody| when > η, stream
Measurement parameter is overproof, carries out alarm feedback.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110864752A (en) * | 2019-11-22 | 2020-03-06 | 西安航天计量测试研究所 | Single-pulse flow measuring device and method based on volume tube and displacement sensor |
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