CN109443781A - Self feed back fault identification engine impulse operating condition flow measurement device and method - Google Patents
Self feed back fault identification engine impulse operating condition flow measurement device and method Download PDFInfo
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- CN109443781A CN109443781A CN201811096482.XA CN201811096482A CN109443781A CN 109443781 A CN109443781 A CN 109443781A CN 201811096482 A CN201811096482 A CN 201811096482A CN 109443781 A CN109443781 A CN 109443781A
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- propellant
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- 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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01F—MEASURING VOLUME, VOLUME FLOW, MASS FLOW OR LIQUID LEVEL; METERING BY VOLUME
- G01F25/00—Testing or calibration of apparatus for measuring volume, volume flow or liquid level or for metering by volume
Abstract
The present invention provides a kind of self feed back fault identification engine impulse operating condition flow measurement device and methods, including detection unit, function to realize auxiliary unit, and detection unit includes parameter detection module, barrel support component and peripheral assembly；Detection unit linkage function realizes auxiliary unit.Core of the invention is parameter detection module, the high-acruracy survey of propellant flow rate is completed by the module and the organic assembling of other units and flow measurement working condition is fed back and intelligent fault identifies that the parameter detection module includes explosion-proof video camera (2), first pressure sensor (5), force snesor (6), first pressure gauge (11), temperature sensor (13), liquid level sensor (17), propellant concentration sensor (27).The present invention carries out double mode measurement, mutual school and the fault detection of propellant flow rate using mass method and volumetric method, improves the stability and reliability of propellant flow rate detection.
Description
Technical field
The present invention relates to fault identification, sensor technology and measurement control fields, more particularly to self feed back fault identification
Engine impulse operating condition flow measurement device and method.
Background technique
In the flow technical field of high-precision measurement of liquid-propellant rocket engine, propellant flow rate directly reacts the property of engine
Can parameter, therefore, propellant flow rate is important Testing index during liquid propellant rocket engine test.Liquid rocket at this stage
The method that volume pipe is widely used in engine propellant pulse flow measures, and measurement accuracy is processed essence by volume bore
The influence of degree, volume pipe are elongate cylinder structure, and the high-accuracy of internal diameter is machined with bigger difficulty.The density of propellant by
The influence of the external factor such as temperature, pressure, causing flow measurement, there are biggish uncertainties.Therefore, it is necessary to develop a kind of energy
The engine propellant flow rate measuring device enough to solve the above problems.
Summary of the invention
For the defects in the prior art, the object of the present invention is to provide a kind of self feed back fault identification engine impulse works
Condition flow measurement device and method.
According to an aspect of the present invention, a kind of self feed back fault identification engine impulse operating condition flow measurement dress is provided
It sets, including detection unit, detection unit includes parameter detection module, barrel support component and peripheral assembly.
Preferably, the barrel support component includes outer barrel, outer barrel flange, outer cylinder inner cylinder, pedestal；Wherein, outside
Cylinder, outer barrel flange collectively define an accommodation space, and the inner cylinder is located at outer barrel, outer barrel flange limits jointly
Accommodation space in, at the top of inner cylinder with collectively define the first installation space inside outer barrel flange, inner cylinder it is circumferential with it is outer
Cylinder circumferentially collectively defines the second installation space, and pedestal is mounted on the bottom of outer barrel, pressurization is equipped on outer barrel flange
Pipeline, pressure piping end are located in the first installation space.
Preferably, the peripheral assembly include the reversed spray head of gas, boost electromagnetic valve, fluid path solenoid valve, filter, manually
Liquid valve, explosion-proof illuminating lamp, the first filter washing water inlet, first manual purge valve, the first lateral damper, propellant outlet tube,
Blowdown valve, sewage pipe, the second lateral damper, the second manual purge valve and the second filter washing water inlet；
Wherein, the reversed spray head of gas is mounted on pressure piping end and is located in the first installation space, boost electromagnetic valve peace
Outside on pressure piping and positioned at outer barrel flange；Propellant outlet tube is installed through on outer barrel flange, is promoted
One end of agent outlet tube is located inside inner cylinder, and the other end of propellant outlet tube is located at the outside of outer barrel flange；Go out manually
Liquid valve, fluid path solenoid valve, filter are sequentially arranged on the propellant outlet tube outside outer barrel flange；Explosion-proof illuminating lamp
It is mounted on outer barrel and is located in the first installation space；First filter washing water inlet connects outer cylinder by first manual purge valve
Body, second the second manual purge valve of filter washing water inlet clearance connect outer barrel；First lateral damper, the second lateral damper are equal
In the second installation space and connect outer barrel and inner cylinder；Sewage pipe is mounted on outer barrel bottom and is located at outer barrel pedestal
Interior, blowdown valve is mounted on sewage pipe.
Preferably, the parameter detection module includes explosion-proof video camera, first pressure sensor, force snesor, the first pressure
Power table, temperature sensor, liquid level sensor, propellant concentration sensor；
Wherein, explosion-proof video camera is mounted on outer barrel and is located in the first installation space；First pressure sensor installation
On outer shell flange, the end of probe of first pressure sensor is located in the first installation space；Force snesor is mounted on the first peace
In dress space and connect outer barrel flange and inner cylinder；First pressure gauge is mounted on outer barrel flange, the spy of first pressure gauge
End is surveyed to be located in the first installation space；Temperature sensor, propellant concentration sensor are installed on outer barrel；Liquid level sensor
It is mounted on inner cylinder, the test side of liquid level sensor is located in inner cylinder.
Preferably, including function realizes that auxiliary unit, function realize auxiliary unit connecting detection unit；The function is realized
Auxiliary unit includes test run hold-up vessel, vessel pressurization control valve, second pressure sensor, second pressure gauge, container bottom valve, examination
Car owner's valve, test run control valve, device fill control valve；
Wherein, vessel pressurization control valve is mounted on the pressure pipeline at the top of test run hold-up vessel, second pressure sensor
It is mounted at the top of test run hold-up vessel, one end of second pressure sensor is located inside test run hold-up vessel, second pressure sensing
The other end of device is located at outside test run hold-up vessel；Second pressure gauge is mounted at the top of test run hold-up vessel, second pressure gauge
One end is located inside test run hold-up vessel, and the other end of second pressure gauge is located at outside test run hold-up vessel；Test run hold-up vessel
Bottom connects propellant feed pipes, and container bottom valve, device filling control valve, test run control are successively installed on propellant feed pipes
Valve processed, test run main valve, test run main valve connect engine, and test run control valve connects the filter of peripheral assembly.
Preferably, the close pore structure of hemispherical of the reversed spray head of the gas makes to be pressurized gas towards outer barrel flange side
Body is flowed out from shell flange side outwardly, and pressurized air stream will not generate disturbance to the propellant weight measure of the change in inner cylinder；
First lateral damper, the second lateral damper are able to suppress under engine impulse operating condition in caused by propellant outflow
The vibration of cylinder.
Preferably, inner cylinder has the function of graduated cylinder；The liquid level sensor is used to detect the liquid level of propellant；It is described
Temperature sensor real-time detection outer barrel in temperature, the propellant density under corresponding temperature is obtained, in conjunction with level sensing
The volume change of device and the propellant of inner cylinder bulk measurement obtains propellant flow rate parameter with volumetric method and with the volatilization of propellant
Measure parameters revision；
The propellant concentration that the volatile quantity of the propellant is detected by propellant concentration sensor, in conjunction with pressure sensing
The relevant parameter of device, liquid level sensor and inner cylinder is calculated.
Preferably, the force snesor is used to detect the mass change amount of propellant in unit time inner cylinder；By
The parameters revision of propellant volatile quantity obtains propellant flow rate parameter with mass method.
Preferably, by using force snesor obtain propellant flow rate parameter and liquid level sensor obtain flow parameter into
Mobile state comparison, carries out working condition feedback, when deviation is greater than critical value, that is, carries out fault alarm, realizes flow status
The intelligent recognition of automatic feedback and failure.
According to another aspect of the present invention, a kind of self feed back fault identification engine impulse operating condition flow measurement side is provided
Method remembers that the parameter variation value of liquid level sensor in the unit time is LVY, the mass parameter of note unit time inner force sense device conversion
Changing value is QL, temperature sensor detects real-time temperature in the course of work, obtained pair according to the detection temperature of temperature sensor
The density p of propellant at a temperature of answeringT, further according to the dimensional parameters D of inner cylinder internal diameter, obtain the mass flow Q of unit timeMY
Are as follows:
QMY=ρT×LVY×πD2/4
According to concentration and the first pressure sensing of propellant saturated vapor in the outer barrel of propellant concentration sensor detection
The pressure of gas in the outer barrel that device measures obtains the content δ of propellant in unit volume propellant saturated vapor, then propellant
The evaporation capacity ξ of unit time are as follows:
ξ=δ × LVY×πD2/4
By the mass flow Q for the engine test that mass method obtainsMatterAre as follows:
QMatter=QL-ξ
By the mass flow Q for the engine test that volumetric method obtainsBodyAre as follows:
QBody=QMY-ξ
The mass-flow rate of propellant of engine takes the mean value of two kinds of flow-measuring method parameters obtaineds of mass method and volumetric method
Q:
Q=(QMatter+QBody)/2
The engine flow error of mass method and volumetric method measurement is set as η, as | QMatter-QBody| when > η, flow measurement parameter
Overproof, device carries out alarm feedback.
Compared with prior art, the present invention have it is following the utility model has the advantages that
1, the present invention using mass method and volumetric method carry out the double mode measurement of propellant flow rate during engine test,
Mutual school and fault detection, can be realized the high-acruracy survey of pulse flow, improve propellant flow rate detection stability and can
By property, and it is able to achieve test constantly.
2, the present invention is able to carry out working condition Real-time Feedback and fault identification, improves the intelligent water of flow measurement
It is flat, invalid, mistake data on flows generation during engine test is effectively prevented, experimentation cost has been saved, has improved examination
The quality of data is tested, 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 the structural schematic diagram of detection unit of the present invention.
Fig. 2 is structural schematic diagram of the invention.
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.
A kind of self feed back fault identification engine impulse operating condition flow measurement device provided according to the present invention, including detection
Unit, detection unit include parameter detection module, barrel support component and peripheral assembly.Core of the invention is parameter detecting mould
Block completes the high-acruracy survey and flow measurement work shape of propellant flow rate by the module and the organic assembling of other units
State feedback and intelligent fault identification.
As shown in Figure 1, the barrel support component includes outer barrel 1, outer barrel flange 10, outer cylinder inner cylinder 22, pedestal
24；Wherein, outer barrel 1, outer barrel flange 10 collectively define an accommodation space, and the inner cylinder 22 is located at outer barrel 1, outer
In the accommodation space that shell flange 10 limits jointly, the first peace is collectively defined inside 22 top of inner cylinder and outer barrel flange 10
Space is filled, inner cylinder 22 is circumferential circumferentially to collectively define the second installation space with outer barrel 1, and pedestal 24 is mounted on outer barrel 1
Bottom is equipped with pressure piping on outer barrel flange 10, and pressure piping end is located in the first installation space.Barrel support component
It is mainly used for other component installations, inner cylinder 22 stores propellant 21, and outer barrel 1 plays sealing process to pressurization gas, and right
Propellant in inner cylinder 22 is squeezed, and for realizing the propellant volume flow measurement of volume flow measurement method.
As shown in Figure 1, the peripheral assembly 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, 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, the second lateral damper 23, the second manual purge valve 25 and second are clear
Wash liquor inlet 26；Wherein, the reversed spray head 3 of gas is mounted on pressure piping end and is located in the first installation space, is pressurized electromagnetism
Valve 4 is mounted on the outside on pressure piping and being located at outer barrel flange 10；Propellant outlet tube 18 is installed through outer barrel method
On orchid 10, one end of propellant outlet tube 18 is located inside inner cylinder 22, and the other end of propellant outlet tube 18 is located at outer barrel
The outside of flange 10；Manual liquid outlet valve 9, fluid path solenoid valve 7, filter 8 are sequentially arranged at outside outer barrel flange 10
On propellant outlet tube 18；Explosion-proof illuminating lamp 12 is mounted on outer barrel 1 and is located in the first installation space；First cleaning solution enters
Mouth 14 connects outer barrel 1 by first manual purge valve 15, and 26 the second manual purge valve 25 of clearance of the second filter washing water inlet connects
Outer barrel 1；First lateral damper 16, the second lateral damper 23 are respectively positioned in the second installation space and connect 1 and of outer barrel
Inner cylinder 22；Sewage pipe 20 is mounted on 1 bottom of outer barrel and is located in 24 pedestal of outer barrel, and blowdown valve 19 is mounted on sewage pipe 20
On.Peripheral assembly plays the role of ensuring device flow measurement function-stable reliably.Preferably, the reversed spray head 3 of the gas
The close pore structure of hemispherical towards 10 side of outer barrel flange, flow out pressurization gas from 10 side of shell flange outwardly, pressurization
Air-flow will not generate disturbance to the propellant weight measure of the change in inner cylinder 22；First lateral damper 16, second
Lateral damper 23 is able to suppress the vibration that propellant under engine impulse operating condition flows out caused inner cylinder 22, so that measurement ginseng
Number is more reliable and more stable.
As shown in Figure 1, the parameter detection module include explosion-proof video camera 2, first pressure sensor 5, force snesor 6,
First pressure gauge 11, temperature sensor 13, liquid level sensor 17, propellant concentration sensor 27；Wherein, explosion-proof video camera 2 is pacified
On outer barrel 1 and it is located in the first installation space；First pressure sensor 5 is mounted on outer barrel flange 10, the first pressure
The end of probe of force snesor 5 is located in the first installation space；Force snesor 6 is mounted in the first installation space and connects outer barrel
Flange 10 and inner cylinder 22；First pressure gauge 11 is mounted on outer barrel flange 10, and the end of probe of first pressure gauge 11 is located at the
In one installation space；Temperature sensor 13, propellant concentration sensor 27 are installed on outer barrel 1；Liquid level sensor 17 is pacified
On inner cylinder 22, the test side of liquid level sensor 17 is located in inner cylinder 22.Parameter detection module can be realized inside device
The detection of scene, pressure, flow, liquid level, temperature and propellant concentration, the explosion-proof video camera 2 can observe internal component
Working condition.
As shown in Fig. 2, measuring device further includes that function realizes that auxiliary unit, function realize auxiliary unit connecting detection list
Member；The function realize auxiliary unit include test run hold-up vessel 28, vessel pressurization control valve 29, second pressure sensor 30,
Second pressure gauge 31, container bottom valve 32, test run main valve 33, test run control valve 34, device fill control valve 35；Wherein, container increases
Pressure control valve 29 is mounted on the pressure pipeline at 28 top of test run hold-up vessel, and second pressure sensor 30 is mounted on test run storage
The top of container 28, one end of second pressure sensor 30 are located inside test run hold-up vessel 28, second pressure sensor 30 it is another
One end is located at outside test run hold-up vessel 28；Second pressure gauge 31 is mounted on 28 top of test run hold-up vessel, second pressure gauge 31
One end be located inside test run hold-up vessel 28, the other end of second pressure gauge 31 is located at outside test run hold-up vessel 28；Test run
28 bottom of hold-up vessel connects propellant feed pipes, and container bottom valve 32, device filling are successively installed on propellant feed pipes
Control valve 35, test run control valve 34, test run main valve 33, test run main valve 33 connect engine 36, and test run control valve 34 connects periphery
The filter 8 of component.Function realizes that the auxiliary unit cooperation present apparatus realizes that propellant flow rate measures function, test run hold-up vessel 28
Equipped with propellant 21, flow measurement device and main propellant supply line are realized by the unlatching of test run control valve 34, closing
On-off, device fill control valve 35 can be by the repropellenting in test run hold-up vessel 28 into flow measurement device.
Preferably, inner cylinder 22 has the function of graduated cylinder；The liquid level sensor 17 is used to detect the liquid level of propellant；
Temperature in the 13 real-time detection outer barrel 1 of temperature sensor, obtains the propellant density under corresponding temperature, in conjunction with liquid
The volume change for the propellant that level sensor 17 and inner cylinder 22 measure obtains propellant flow rate parameter with volumetric method and with pushing away
Into the volatile quantity parameters revision of agent；The volatile quantity of the propellant is dense by the propellant that propellant concentration sensor 27 detects
Degree, is calculated in conjunction with the relevant parameter of pressure sensor 5, liquid level sensor 17 and inner cylinder 22.Preferably, the power passes
Sensor 6 is used to detect the mass change amount of propellant in unit time inner cylinder 22；It is repaired by the parameter of propellant volatile quantity
Just, propellant flow rate parameter is obtained with mass method.Preferably, the propellant flow rate parameter and liquid that will be obtained using force snesor 6
Level sensor 17 obtain flow parameter carry out dynamic contrast, carry out working condition feedback, when deviation be greater than critical value when, i.e., into
Row fault alarm realizes the automatic feedback of flow status and the intelligent recognition of failure.
Specific measurement method is as follows:
All valves are in closed state in the initial state, without propellant 21, test run hold-up vessel in inner cylinder 22
Propellant 21 is filled in 28.Vessel pressurization control valve 29 is opened, test run hold-up vessel 28 is pressurized, container is successively opened
Bottom valve 32, device filling control valve 35, test run control valve 34, fluid path solenoid valve 7 and manual liquid outlet valve 9 are filled into inner cylinder 22
Propellant 21；It opens boost electromagnetic valve 4 and pressure release deflation is carried out to outer barrel 1；According to force snesor 6, liquid level sensor 17 it is aobvious
Indicating value determines the adding amount of propellant 21, after adding amount is met the requirements, closes device and fills control valve 35, opens pressurization electricity
Magnet valve 4 is pressurized outer barrel 1, opens test run main valve 33, and propellant 21 is flowed out from propellant outlet tube 18, controlled through test run
Valve 34, test run main valve 33 flow into engine 36 and carry out 36 fire trial of engine；The unlatching of boost electromagnetic valve 4 can either can be pressurized
Also it can deflate, mainly be determined by the gas pressure of external pipe.
Propellant 21 is discharged from inner cylinder 22, can cause the variation of 6 detection parameters of force snesor, and unit time internal force passes
The mass parameter changing value that sensor 6 converts is QL.Propellant 21 is discharged from inner cylinder 22,17 detection parameters of liquid level sensor
It can change, the parameter variation value of liquid level sensor 17 is L in the unit timeVY, temperature sensor 13 detect the course of work in
Real-time temperature obtains the density p of the propellant 21 under corresponding temperature according to the detection temperature of temperature sensor 13T, further according to
The dimensional parameters D of 22 internal diameter of inner cylinder obtains the mass flow Q of unit timeMYAre as follows:
QMY=ρT×LVY×πD2/4
The concentration and first pressure of propellant saturated vapor pass in the outer barrel 1 detected according to propellant concentration sensor 27
The pressure of gas in the outer barrel 1 that sensor 5 measures, obtains the content δ of propellant in unit volume propellant saturated vapor, then pushes away
Into the evaporation capacity ξ of agent unit time are as follows:
ξ=δ × LVY×πD2/4
By the mass flow Q for the engine test that mass method obtainsMatterAre as follows:
QMatter=QL-ξ
By the mass flow Q for the engine test that volumetric method obtainsBodyAre as follows:
QBody=QMY-ξ
The mass-flow rate of propellant of engine takes the mean value of two kinds of flow-measuring method parameters obtaineds of mass method and volumetric method
Q:
Q=(QMatter+QBody)/2
The engine flow error of mass method and volumetric method measurement is set as η, as | QMatter-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.
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 (10)
1. a kind of self feed back fault identification engine impulse operating condition flow measurement device, which is characterized in that including detection unit, inspection
Surveying unit includes parameter detection module, barrel support component and peripheral assembly.
2. self feed back fault identification engine impulse operating condition flow measurement device according to claim 1, which is characterized in that
The barrel support component includes outer barrel (1), outer barrel flange (10), outer cylinder inner cylinder (22), pedestal (24)；Wherein, outside
Cylinder (1), outer barrel flange (10) collectively define an accommodation space, and the inner cylinder (22) is located at outer barrel (1), outer cylinder
In the accommodation space that body flange (10) limits jointly, at the top of inner cylinder (22) with the is collectively defined inside outer barrel flange (10)
One installation space, inner cylinder (22) is circumferential circumferentially to collectively define the second installation space with outer barrel (1), and pedestal (24) is mounted on
The bottom of outer barrel (1) is equipped with pressure piping on outer barrel flange (10), and pressure piping end is located at the first installation space
It is interior.
3. self feed back fault identification engine impulse operating condition flow measurement device according to claim 2, which is characterized in that
The peripheral assembly includes the reversed spray head of gas (3), boost electromagnetic valve (4), fluid path solenoid valve (7), filter (8), goes out manually
Liquid 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), the second lateral damper (23), the second manual purge valve
(25) and the second filter washing water inlet (26)；
Wherein, the reversed spray head of gas (3) is mounted on pressure piping end and is located in the first installation space, boost electromagnetic valve (4)
It is mounted on pressure piping and is located at the outside of outer barrel flange (10)；Propellant outlet tube (18) is installed through outer barrel method
On blue (10), one end of propellant outlet tube (18) is located at inner cylinder (22) inside, the other end position of propellant outlet tube (18)
In the outside of outer barrel flange (10)；Manual liquid outlet valve (9), fluid path solenoid valve (7), filter (8) are sequentially arranged at positioned at outer
On the external propellant outlet tube (18) of shell flange (10)；Explosion-proof illuminating lamp (12) is mounted on outer barrel (1) and is located at the
In one installation space；First filter washing water inlet (14) passes through first manual purge valve (15) connection outer barrel (1), the second cleaning solution
The manual purge valve (25) of entrance (26) clearance second connects outer barrel (1)；First lateral damper (16), the second lateral damper
(23) it is respectively positioned in the second installation space and connects outer barrel (1) and inner cylinder (22)；Sewage pipe (20) is mounted on outer barrel (1)
Bottom is simultaneously located in outer barrel (24) pedestal, and blowdown valve (19) is mounted on sewage pipe (20).
4. self feed back fault identification engine impulse operating condition flow measurement device according to claim 2, which is characterized in that
The parameter detection module includes explosion-proof video camera (2), first pressure sensor (5), force snesor (6), first pressure gauge
(11), temperature sensor (13), liquid level sensor (17), propellant concentration sensor (27)；
Wherein, explosion-proof video camera (2) is mounted on outer barrel (1) and is located in the first installation space；First pressure sensor (5)
It is mounted on outer barrel flange (10), the end of probe of first pressure sensor (5) is located in the first installation space；Force snesor
(6) it is mounted in the first installation space and connects outer barrel flange (10) and inner cylinder (22)；First pressure gauge (11) is mounted on
On outer barrel flange (10), the end of probe of first pressure gauge (11) is located in the first installation space；Temperature sensor (13) promotes
Agent concentration sensor (27) is installed on outer barrel (1)；Liquid level sensor (17) is mounted on inner cylinder (22), level sensing
The test side of device (17) is located in inner cylinder (22).
5. self feed back fault identification engine impulse operating condition flow measurement device according to claim 1, which is characterized in that
Realize that auxiliary unit, function realize auxiliary unit connecting detection unit including function；The function realizes that auxiliary unit includes examination
Vehicle hold-up vessel (28), vessel pressurization control valve (29), second 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)；
Wherein, vessel pressurization control valve (29) is mounted on the pressure pipeline at the top of test run hold-up vessel (28), and second pressure passes
Sensor (30) is mounted at the top of test run hold-up vessel (28), and one end of second pressure sensor (30) is located at test run hold-up vessel
(28) internal, it is external that the other end of second pressure sensor (30) is located at test run hold-up vessel (28)；Second pressure gauge (31) peace
At the top of test run hold-up vessel (28), one end of second pressure gauge (31) is located at test run hold-up vessel (28) inside, the second pressure
It is external that the other end of power table (31) is located at test run hold-up vessel (28)；Test run hold-up vessel (28) bottom connects Propellant Supply pipe
Road successively installs container bottom valve (32), device filling control valve (35), test run control valve (34), examination on propellant feed pipes
Car owner's valve (33), test run main valve (33) connect engine (36), and test run control valve (34) connects the filter (8) of peripheral assembly.
6. self feed back fault identification engine impulse operating condition flow measurement device according to claim 3, which is characterized in that
The close pore structure of hemispherical of the reversed spray head of the gas (3) makes pressurization gas from outwardly towards outer barrel flange (10) side
The outflow of shell flange (10) side, pressurized air stream will not generate disturbance to the propellant weight measure of the change in inner cylinder (22)；
First lateral damper (16), the second lateral damper (23) are able to suppress propellant under engine impulse operating condition and flow out
The vibration of caused inner cylinder (22).
7. self feed back fault identification engine impulse operating condition flow measurement device according to claim 4, which is characterized in that
Inner cylinder (22) has the function of graduated cylinder；The liquid level sensor (17) is used to detect the liquid level of propellant；The temperature
Temperature in sensor (13) real-time detection outer barrel (1) obtains the propellant density under corresponding temperature, in conjunction with level sensing
Device (17) and inner cylinder (22) measurement propellant volume change, with volumetric method obtain propellant flow rate parameter and with propulsion
The volatile quantity parameters revision of agent；
The volatile quantity of the propellant passes through the propellant concentration that propellant concentration sensor (27) are detected, in conjunction with pressure sensing
The relevant parameter of device (5), liquid level sensor (17) and inner cylinder (22) is calculated.
8. self feed back fault identification engine impulse operating condition flow measurement device, feature according to claim 4 or 7 exist
In the force snesor (6) is used to detect the mass change amount of propellant in unit time inner cylinder (22)；By propellant
The parameters revision of volatile quantity obtains propellant flow rate parameter with mass method.
9. self feed back fault identification engine impulse operating condition flow measurement device according to claim 4, which is characterized in that
It will be right dynamic will to be carried out with the flow parameter that liquid level sensor (17) obtains using the propellant flow rate parameter that force snesor (6) obtain
Than carrying out working condition feedback, when deviation is greater than critical value, that is, carrying out fault alarm, realize the automatic feedback of flow status
With the intelligent recognition of failure.
10. a kind of self feed back fault identification engine impulse operating condition flow-measuring method, which is characterized in that liquid in the note unit time
The parameter variation value of level sensor (17) is LVY, the mass parameter changing value of note unit time inner force sense device (6) conversion is QL,
Temperature sensor (13) detects real-time temperature in the course of work, obtains corresponding temperature according to the detection temperature of temperature sensor (13)
The density p of propellant (21) under degreeT, further according to the dimensional parameters D of inner cylinder (22) internal diameter, obtain the quality stream of unit time
Measure QMYAre as follows:
QMY=ρT×LVY×πD2/4
It is passed according to the concentration and first pressure of propellant saturated vapor in the outer barrel (1) of propellant concentration sensor (27) detection
The pressure of outer barrel (1) interior gas that sensor (5) measures, obtains the content δ of propellant in unit volume propellant saturated vapor,
The then evaporation capacity ξ of propellant unit time are as follows:
ξ=δ × LVY×πD2/4
By the mass flow Q for the engine test that mass method obtainsMatterAre as follows:
QMatter=QL-ξ
By the mass flow Q for the engine test that volumetric method obtainsBodyAre as follows:
QBody=QMY-ξ
The mass-flow rate of propellant of engine takes the mean value Q of two kinds of flow-measuring method parameters obtaineds of mass method and volumetric method:
Q=(QMatter+QBody)/2
The engine flow error of mass method and volumetric method measurement is set as η, as | QMatter-QBody| when > η, flow measurement parameter is super
Difference, device carry out alarm feedback.
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Citations (5)
| 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 |
| CN104191176A (en) * | 2014-08-25 | 2014-12-10 | 沈阳航天新光集团有限公司 | Method for manufacturing low-temperature flow weighing container |
| EP2824430A1 (en) * | 2013-07-12 | 2015-01-14 | Japan Aerospace Exploration Agency | Method and apparatus for measuring a pulsatingly fluctuating flow rate |
| CN107131931A (en) * | 2017-06-06 | 2017-09-05 | 西安航天动力试验技术研究所 | Attitude control engine high-temperature propellant steady state flow calibrated in situ device and calibration method |
| CN107843330A (en) * | 2017-12-08 | 2018-03-27 | 上海悟道机电设备有限公司 | The measuring apparatus that a kind of flow is weighed |
-
2018
- 2018-09-19 CN CN201811096482.XA patent/CN109443781B/en active Active
Patent Citations (5)
| 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 |
| EP2824430A1 (en) * | 2013-07-12 | 2015-01-14 | Japan Aerospace Exploration Agency | Method and apparatus for measuring a pulsatingly fluctuating flow rate |
| CN104191176A (en) * | 2014-08-25 | 2014-12-10 | 沈阳航天新光集团有限公司 | Method for manufacturing low-temperature flow weighing container |
| CN107131931A (en) * | 2017-06-06 | 2017-09-05 | 西安航天动力试验技术研究所 | Attitude control engine high-temperature propellant steady state flow calibrated in situ device and calibration method |
| CN107843330A (en) * | 2017-12-08 | 2018-03-27 | 上海悟道机电设备有限公司 | The measuring apparatus that a kind of flow is weighed |
Non-Patent Citations (1)
| Title |
|---|
| 赵万明 等: "《液体火箭发动机试验流量测量技术研究》", 《火箭推进》 * |
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