CN104075769B - A kind of Residual Propellant measuring system and method - Google Patents
A kind of Residual Propellant measuring system and method Download PDFInfo
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- CN104075769B CN104075769B CN201410302905.4A CN201410302905A CN104075769B CN 104075769 B CN104075769 B CN 104075769B CN 201410302905 A CN201410302905 A CN 201410302905A CN 104075769 B CN104075769 B CN 104075769B
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Abstract
The present invention provides a kind of Residual Propellant measuring system, including gas cylinder, pressure sensor, latching valve, differential manometer and propellant tank.The present invention also provides a kind of Residual Propellant measuring method, including the state for setting latching valve；Control latching valve, makes two gas cylinders and two tank original states consistent；Control latching valve, abandons one of gas cylinder, and a state of air cylinders keeps, a tank supercharging, and a tank state keeps, and records the pressure of measuring system, thermometer pressure difference；Control latching valve, goes back the original state of original system；Measuring system pressure, temperature and pressure difference according to record calculate the residual volume of propellant.Using the method for the present invention, the gas that can not only save original gas injection method holds configuration, pendulous frequency is also greatly improved, can reach more than 50 times.
Description
Technical field
The present invention relates to a kind of the Residual Propellant measuring system and method for efficient utilization bipropellant, belong to and defend
Star bipropellant propulsion system technical field.
Background technology
With satellite technology development and application prospect it is increasingly extensive, particularly long-life satellite comes into operation, right
Satellite holistic management level and satellite service efficiency propose higher and higher requirement.Satellite booster agent residue measurement is satellite
One important component of in-orbit management, due to exhausting satellite once propellant once finish the life-span, therefore by propulsion
The accurate measurement of agent just can effectively manage the working life of satellite, so as to obtain significant economic benefit.Due to satellite operation
The particularity and this body structure of satellite of environment and the limitation of weight so that directly the propulsion dosage in accurate measurement tank turns into one
The relatively difficult work of item.For the working life of the satellite that calculates to a nicety, those skilled in the art's amount of liquid under microgravity
Measurement aspect has been carried out many effort, especially to the prediction side of a small amount of residual propellant at the end of the lifetime of satellite is close
Face --- certainty of measurement now can drastically decline with the continuous consumption of propellant.They successively develop and apply flow
Meter technology, pressure-volume-temperature (PVT) technology, Radioactive tracer techniques, radioactivity absorption techniques, thin note (BK) technology, penetrate
Frequency technology, ultrasonic technology, gas injection exciting technique, volume exciting technique, propellant sloshing amplitude-frequency phase techniques and
Other technologies.It is summed up, the subject matter that space propultion agent residue measurement is present has：The uncertainty of conventional measuring method
It is high；Degree of certainty measuring method poor universality higher；Certain methods are immature, its stability and reliability it cannot be guaranteed that；Some
Certainty of measurement method pendulous frequency high is limited, it is impossible to be used for multiple times.
The content of the invention
The technical problem to be solved in the present invention is, for deficiency of the prior art, there is provided a kind of Residual Propellant is surveyed
Amount system and method.
The technical scheme that the present invention solves above-mentioned technical problem use includes：
According to an aspect of the present invention, it provides a kind of Residual Propellant measuring system, including：First gas cylinder and
Second gas cylinder, the first gas cylinder and the second gas cylinder are respectively positioned on the most upstream of system, and the first temperature biography is provided with the first gas cylinder
Sensor, second temperature sensor is provided with the second gas cylinder；6th latching valve and the first differential manometer are connected in the first gas cylinder in parallel
And second between gas cylinder；The downstream connection of the first gas cylinder has first pressure sensor；5th latching valve, is connected to first pressure biography
The downstream of sensor；First latching valve and the 3rd latching valve, are connected in the downstream of the 5th latching valve in parallel；The downstream of the first latching valve
The second pressure that is linked in sequence sensor, the first tank and the second latching valve；The downstream of the 3rd latching valve is linked in sequence the 3rd pressure
The downstream of force snesor, the second tank and the 4th latching valve, the second latching valve and the 4th latching valve is connected in parallel to downstream jointly
Fluid path；Also, the two ends of the second differential manometer are respectively connecting to the downstream of the first latching valve and the downstream of the 3rd latching valve, the
Three-temperature sensor is provided with one tank, the 4th temperature sensor is provided with the second tank.
According to another aspect of the present invention, it provides a kind of Residual Propellant measuring method, it is characterised in that should
Method is comprised the following steps：
(1) the step of measuring the Residual Propellant in the first tank includes：
(11) the second latching valve, the 3rd latching valve, the 5th latching valve are set all in closed mode, and the first self-locking
Valve, the 4th latching valve, the 6th latching valve are in opening；
(12) the 3rd latching valve is opened, waits the temperature and pressure of two tanks to reach stabilization；
(13) the 3rd latching valve and the 6th latching valve are closed, the 5th latching valve is opened, to the first tank aerating；Then, close
Close the 5th latching valve, after the temperature and pressure in the first gas cylinder and the first tank keeps stabilization, record deflated the
The pressure value and temperature value of the pressure value and temperature value of two gas cylinders and the second propellant tank being pressurized are used as calculating
First state value, meanwhile, record the first differential manometer pressure difference and the second gas cylinder pressure value additive value as the first gas cylinder pressure
The additive value of the pressure value of the final states value of power, the pressure difference of the second differential manometer and the second propellant tank is used as the first tank pressure
Final states value, temperature value in the first gas cylinder and the first tank is used as the final states value for calculating temperature；
(14) the 3rd latching valve and the 6th latching valve are opened, the first gas cylinder and the second gas cylinder and the first tank and the is treated
After pressure in two propellant tanks no longer changes, the 3rd latching valve and the 6th latching valve are closed；
(15) according to the pressure, pressure difference and temperature data obtained in abovementioned steps, and the advance gas cylinder for measuring, tank
Volume data, applied satellite Residual Propellant Measuring System Models are that can determine that the residual propellant volume in the first tank,
Wherein, Residual Propellant Measuring System Models are as follows：
Wherein
In above formula, VlIt is the volume of propellant；PpiIt is the initial state pressure value of gas cylinder；PpfIt is the final states pressure value of gas cylinder；Tpi
It is the initial state temperature value of gas cylinder；TpfIt is the final states temperature value of gas cylinder；VpIt is the volume of gas cylinder；VtIt is the volume of tank；PuiIt is storage
Initial state pressure value in case；PufIt is final states pressure value in tank；TuiIt is initial state helium temperature in tank；TufIt is final states helium in tank
Temperature degree；ZpiIt is the initial state helium compressibility factor of gas cylinder, ZpfIt is the final states helium compressibility factor of gas cylinder, ZuiIt is initial state in tank
Helium compressibility factor, ZufIt is final states helium compressibility factor, Z in tankpi、Zpf、Zui、ZufObtained according to experiment.
(2) the step of measuring the Residual Propellant in the second propellant tank includes：
(21) the second latching valve, the 3rd latching valve, the 5th latching valve are set all in closed mode, and the first self-locking
Valve, the 4th latching valve, the 6th latching valve are in opening；
(22) the 3rd latching valve is opened, waits the temperature and pressure of two tanks to reach stabilization；
(23) the first latching valve and the 6th latching valve are closed, the 5th latching valve is opened, to the second propellant tank aerating；So
The 5th latching valve is closed afterwards, and after the temperature and pressure in the first gas cylinder and the second propellant tank keeps stabilization, record does not enter
The pressure value and the pressure value and temperature value conduct of temperature value and the first tank being pressurized of the second gas cylinder that row is deflated
Just state value is calculated, meanwhile, the additive value of the pressure value of pressure difference and the second gas cylinder in the first differential manometer of record is used as gas cylinder pressure
The final states value of power, the additive value of the pressure value of pressure difference and the second propellant tank in the second differential manometer is used as tank pressure
Final states value, the temperature value in the first gas cylinder and the second propellant tank is used as the final states value for calculating temperature；
(24) the first latching valve and the 6th latching valve are opened, the first gas cylinder and the second gas cylinder and the first tank and the is treated
After pressure in two propellant tanks no longer changes, the 3rd latching valve and the 6th latching valve are closed；
(25) according to the pressure, pressure difference and temperature data obtained in abovementioned steps, and the advance gas cylinder for measuring, tank
Volume data, applied satellite Residual Propellant Measuring System Models are that can determine that the residual propellant in the second propellant tank
Volume, wherein, Residual Propellant Measuring System Models are as follows：
Wherein
In above formula, VlIt is the volume of propellant；PpiIt is the initial state pressure value of gas cylinder；PpfIt is the final states pressure value of gas cylinder；Tpi
It is the initial state temperature value of gas cylinder；TpfIt is the final states temperature value of gas cylinder；VpIt is the volume of gas cylinder；VtIt is the volume of tank；PuiIt is storage
Initial state pressure value in case；PufIt is final states pressure value in tank；TuiIt is initial state helium temperature in tank；TufIt is final states helium in tank
Temperature degree；ZpiIt is the initial state helium compressibility factor of gas cylinder, ZpfIt is the final states helium compressibility factor of gas cylinder, ZuiIt is initial state in tank
Helium compressibility factor, ZufIt is final states helium compressibility factor, Z in tankpi、Zpf、Zui、ZufObtained according to experiment.
The volume of the afterburning agent in the first incendiary agent tank is measured using the step identical with step (11)-(15),
Similarly, the volume of the afterburning agent in the second incendiary agent tank is measured using the step identical with step (21)-(25), by
This, can obtain the residual volume of the propellant and incendiary agent in propulsion system.
Residual Propellant measuring system of the invention and method have beneficial technique effect, including：
Residual Propellant e measurement technology based on pressure calculus of finite differences of the invention is noted using pressure difference measuring gas
Enter front and rear pressure difference, higher than delta pressure accuracy before and after the measurement gas injection of conventionally employed two pressure sensors is more, thus,
The remaining accuracy of measurement that surplus computation model based on the equation of gas state is calculated accordingly is improved.And due to differential manometer measurement
Delta pressure accuracy 2 orders of magnitude more taller than existing high-precision pressure sensor so that the amount of helium of excitation may decrease to original every time
Less than/10th for coming, therefore the gas appearance configuration of original gas injection method can not only be saved, measurement is also greatly improved
Number of times, can reach more than 50 times.
Pressure calculus of finite differences high accuracy Residual Propellant measuring method of the invention is applied to all tank knots in parallel
The bipropellant propulsion system of structure, simplifies system architecture, alleviates system weight, improves the measurement essence of Residual Propellant
Degree, for the bipropellant propulsion system devoid of risk of tank structure in parallel, can be widely applied to truss-like satellite platform.
Brief description of the drawings
Fig. 1 is the schematic diagram according to Residual Propellant measuring system of the invention；
Fig. 2 is the schematic diagram according to Residual Propellant measuring method of the invention.
Specific embodiment
Residual Propellant measuring system of the invention and method are done below in conjunction with the drawings and specific embodiments
Further details of explanation.
The technology for being presently used for Residual Propellant measurement under microgravity all relies on greatly the bookkeeping of propellant waste
(BK) method and basic propellant thermodynamics measuring method (PVT methods), in-orbit period are mainly PVT methods, theoretical error for ±
1.63% (tank total measurement (volume)), but, actual error is 3% or so.Therefore, those skilled in the art are on the basis of existing platform
On, it is main measurement method to use gas injection method, and revised PVT methods and BK methods are auxiliary measuring method, and certainty of measurement can
To reach ± 0.8% (tank total measurement (volume)).But certainty of measurement still has to be supplied, and pendulous frequency is also extremely limited, can only
Reach within 5 times.
Residual Propellant e measurement technology based on pressure calculus of finite differences injects front and rear pressure difference using pressure difference measuring gas,
Than high many of delta pressure accuracy before and after the measurement gas injection of conventionally employed two pressure sensors, gaseous state side is hereby based on
The remaining accuracy of measurement that the surplus computation model of journey is calculated accordingly is improved.And because differential manometer measures delta pressure accuracy than existing
Taller 2 orders of magnitude of high-precision pressure sensor so that every time excitation amount of helium may decrease to original 1/10th with
Under, thus can not only save original gas injection method gas hold configuration, pendulous frequency is also greatly improved, can reach 50 times
More than.
The double elements that pressure calculus of finite differences high accuracy Residual Propellant e measurement technology is applied to all tank structures in parallel is pushed away
Enter system, technique is a simplified system architecture, alleviates system weight, improve the certainty of measurement of Residual Propellant,
For the bipropellant propulsion system devoid of risk of tank structure in parallel, truss-like satellite platform is can be widely applied to.
The general principle of the Residual Propellant measuring method based on pressure calculus of finite differences is：Gas injects it from a gas cylinder
In a tank, the measurement pressure difference that injects between two tanks of former and later two gas cylinders and same media of gas, not participate in wherein
The gas cylinder of injection and the pressure of tank are the preflood initial value of gas, participate in the gas cylinder of injection and the pressure of tank for gas injects
End value afterwards, gas body in tank is calculated by the measurement data of Dalton's law (of partial pressures) and loading pressure temperature change
Product, equally calculates liquid volume and liquid quality in case by tank cumulative volume and fluid density again.
Gas cylinder, pressure sensor, latching valve, differential manometer are provided with Residual Propellant measuring system of the invention
And propellant tank.The function of all parts is as follows in system：
1st, gas cylinder is used for storage high pressure pressurization gas, and the two is each provided with the first temperature sensor and second temperature above
Sensor, the temperature for measuring gas cylinder inner high voltage gas；
2nd, pressure sensor is used to measure two gas cylinders and the pressure of each propellant tank；
3rd, latching valve (that is, the first latching valve, the second latching valve, the 3rd latching valve, the 4th latching valve, the 5th latching valve, with
And the 6th latching valve) for giving the supercharging of corresponding propellant tank and cut-off two gas cylinders, two propellant tanks；
4th, each propellant tank is used to store propellant, above also mounting temperature sensor, for measuring gas in tank
The temperature of body or liquid；
5th, differential manometer is used to measure two pressure differences and two pressure differences of propellant tank of gas cylinder；
Specifically, Residual Propellant measuring system of the invention includes：First gas cylinder 1 and the second gas cylinder 2, two
Gas cylinder is respectively positioned on the most upstream of system.The first temperature sensor is provided with first gas cylinder 1, second is provided with the second gas cylinder 2
Temperature sensor.6th latching valve LV6 and the first differential manometer DP1 are connected in parallel between two gas cylinders, and the 6th latching valve LV6 is used
Break-make between two gas cylinders, the first differential manometer DP1 is used for measuring the pressure difference between two gas cylinders.The downstream of the first gas cylinder 1
It is connected with first pressure sensor P1.First pressure sensor P1 is used to measure two pressure of gas cylinder.5th latching valve LV5 connects
It is connected on the downstream of first pressure sensor P1；First latching valve LV1 and the 3rd latching valve LV3, is connected in the 5th latching valve in parallel
The downstream of LV5.First latching valve LV1 downstreams are linked in sequence second pressure sensor P2, the first tank TANK-A, the second latching valve
LV2；3rd latching valve LV3 downstreams are linked in sequence the 3rd pressure sensor P3, the second propellant tank TANK-B and four selfs
Locking-valve LV4.The downstream of the second latching valve LV2 and the 4th latching valve LV4 is connected in parallel to downstream fluid path jointly；Also, the second pressure difference
The two ends for counting DP2 are respectively connecting to the downstream of the first latching valve LV1 and the downstream of the 3rd latching valve LV3, the first tank
Three-temperature sensor is provided with TANK-A, the 4th temperature sensor is provided with the second tank TANK-B.
With reference to Fig. 2, the method according to the invention is comprised the following steps：
1st, the step of measuring the Residual Propellant in the first tank (TANK-A) includes：
(11) the second latching valve LV2, the 3rd latching valve LV3, the 5th latching valve LV5 are set all in closed mode, and
First latching valve LV1, the 4th latching valve LV4, the 6th latching valve LV6 are in opening.This step purpose measures system to connect
System.
(12) the 3rd latching valve LV3 is opened, waits the temperature and pressure of two tanks to reach stabilization.
The purpose of this step is to ensure that the pressure and temperature of two propellant tanks is consistent so that propellant tank
State can be as the original state before following 13rd step aerating.Due to being all correspondingly provided with pressure sensing on two tanks
Device and temperature sensor, therefore, by respective pressure sensor and temperature sensor be measurable two tanks pressure and
Temperature.Generally, through the time of left and right after one minute, the temperature and pressure of two tanks is that can reach stabilization.
(13) the 3rd latching valve LV3 and the 6th latching valve LV6 is closed, the is opened according to the pressure in the first tank TANK-A
The five latching valve LV5 several seconds, with to the first tank TANK-A aeratings；It is then shut off the 5th latching valve LV5；Treat the first gas cylinder and first
After temperature and pressure stabilization in tank TANK-A, the pressure value of the second gas cylinder that record is deflated and temperature value and
The pressure value and temperature value of the second propellant tank TANK-B being pressurized are used as the first state value of calculating；Meanwhile, record first
The additive value of the pressure value (i.e. previously as the pressure value for calculating just state value) of the pressure difference of differential manometer DP1 and the second gas cylinder 2 is made
It is the final states value of the first storage pressure, the pressure value of the pressure difference of the second differential manometer DP2 and the second propellant tank TANK-B is (i.e.
Previously as the pressure value for calculating just state value) additive value as the first tank pressure final states value, the first gas cylinder 1 and the first storage
Temperature value in case TANK-A is used as the final states value for calculating temperature；
(14) the 3rd latching valve LV3 and the 6th latching valve LV6 is opened, the pressure in two gas cylinders and two propellant tanks is treated
After power stabilization, the 3rd latching valve LV3 and the 6th latching valve LV6 is closed.The purpose of this step is first before making system recover to measure
Beginning state.
(15) according to the pressure, pressure difference and temperature data obtained in abovementioned steps, and the advance gas cylinder for measuring, tank
Volume data, applied satellite Residual Propellant Measuring System Models are that can determine that the remaining propulsion in the first tank (TANK-A)
Agent volume, wherein, Residual Propellant Measuring System Models are as follows：
Wherein
In above formula, VlIt is the volume of propellant；PpiIt is the initial state pressure value of gas cylinder；PpfIt is the final states pressure value of gas cylinder；Tpi
It is the initial state temperature value of gas cylinder；TpfIt is the final states temperature value of gas cylinder；VpIt is the volume of gas cylinder；VtIt is the volume of tank；PuiIt is storage
Initial state pressure value in case；PufIt is final states pressure value in tank；TuiIt is initial state helium temperature in tank；TufIt is final states helium in tank
Temperature degree；ZpiIt is the initial state helium compressibility factor of gas cylinder, ZpfIt is the final states helium compressibility factor of gas cylinder, ZuiIt is initial state in tank
Helium compressibility factor, ZufIt is final states helium compressibility factor, Z in tankpi、Zpf、Zui、ZufObtained according to experiment.
2nd, the step of measuring the Residual Propellant in the second tank (TANK-B) includes：
(21) the second latching valve LV2, the 3rd latching valve LV3, the 5th latching valve LV5 are set all in closed mode, and
First latching valve LV1, the 4th latching valve LV4, the 6th latching valve LV6 are in opening；Meanwhile, detonate the first normally closed electric blasting valve
PV1；
(22) the 3rd latching valve LV3 is opened, waits the temperature and pressure of two tanks to reach stabilization；
(23) the first latching valve LV1 and the 6th latching valve LV6 is closed, according to the pressure in the second propellant tank TANK-B
Open for the 5th latching valve LV5 several seconds to the second tank (TANK-B) aerating；Then, the 5th latching valve LV5 is closed；Treat the first gas cylinder
After the temperature and pressure stabilization in the second propellant tank TANK-B, the pressure value of the second gas cylinder that record is deflated and
The pressure value and temperature value of temperature value and the first tank TANK-A being pressurized are used as the first state value of calculating；Meanwhile, record
The phase of pressure difference in the first differential manometer DP1 and the pressure value (i.e. previously as the pressure value for calculating just state value) of the second gas cylinder 1
The value added final states value as storage pressure, the pressure of pressure difference and the second propellant tank TANK-B in the second differential manometer DP2
It is worth the additive value of (i.e. previously as the pressure value for calculating just state value) as the final states value of tank pressure, the first gas cylinder 2 and second
Temperature value in propellant tank TANK-B is used as the final states value for calculating temperature；
(24) the first latching valve LV1 and the 6th latching valve LV6 is opened, the pressure in two gas cylinders and two propellant tanks is treated
After power stabilization, the 3rd latching valve LV3 and the 6th latching valve LV6 is closed.The purpose of this step is first before making system recover to measure
Beginning state.
(25) according to the pressure, pressure difference and temperature data obtained in abovementioned steps, and the advance gas cylinder for measuring, tank
Volume data, applied satellite Residual Propellant Measuring System Models are that can determine that the remaining propulsion in the second tank (TANK-B)
Agent volume, wherein, Residual Propellant Measuring System Models are as follows：
Wherein
In above formula, VlIt is the volume of propellant；PpiIt is the initial state pressure value of gas cylinder；PpfIt is the final states pressure value of gas cylinder；Tpi
It is the initial state temperature value of gas cylinder；TpfIt is the final states temperature value of gas cylinder；VpIt is the volume of gas cylinder；VtIt is the volume of tank；PuiIt is storage
Initial state pressure value in case；PufIt is final states pressure value in tank；TuiIt is initial state helium temperature in tank；TufIt is final states helium in tank
Temperature degree；ZpiIt is the initial state helium compressibility factor of gas cylinder, ZpfIt is the final states helium compressibility factor of gas cylinder, ZuiIt is initial state in tank
Helium compressibility factor, ZufIt is final states helium compressibility factor, Z in tankpi、Zpf、Zui、ZufObtained according to experiment.
It is those skilled in the art by this theory here, it should be noted that the content not described in detail in this specification
What description and prior art in bright book can be realized, therefore, do not repeat.
The preferred embodiments of the present invention are the foregoing is only, not for limiting the scope of the invention.For ability
For the technical staff in domain, on the premise of not paying creative work, some modifications and replacement can be made to the present invention,
All such modifications and replacement should all be included within the scope of the present invention.
Claims (1)
1. a kind of Residual Propellant measuring method based on Residual Propellant measuring system, Residual Propellant measurement system
System, including：
First gas cylinder (1) and the second gas cylinder (2), the first gas cylinder (1) and the second gas cylinder (2) are respectively positioned on the most upstream of system, and
The first temperature sensor is provided with first gas cylinder (1), the second gas cylinder is provided with second temperature sensor on (2)；
6th latching valve (LV6) and the first differential manometer (DP1) are connected in parallel between the first gas cylinder (1) and the second gas cylinder (2)；The
The downstream connection of one gas cylinder (1) has first pressure sensor (P1)；
5th latching valve (LV5), is connected to the downstream of first pressure sensor (P1)；
First latching valve (LV1) and the 3rd latching valve (LV3), are connected in the downstream of the 5th latching valve (LV5) in parallel；First self-locking
The downstream of valve (LV1) is linked in sequence second pressure sensor (P2), the first tank (TANK-A) and the second latching valve (LV2)；
The downstream of the 3rd latching valve (LV3) is linked in sequence the 3rd pressure sensor (P3), the second tank (TANK-B) and the 4th self-locking
The downstream of valve (LV4), the second latching valve (LV2) and the 4th latching valve (LV4) is connected in parallel to downstream fluid path jointly；Also, second
The two ends of differential manometer (DP2) are respectively connecting to the downstream of the first latching valve (LV1) and the downstream of the 3rd latching valve (LV3),
Three-temperature sensor is provided with first tank (TANK-A), the 4th TEMP is provided with the second tank (TANK-B)
Device；
Characterized in that, the method is comprised the following steps：
(1) the step of measuring the Residual Propellant in the first tank (TANK-A) includes：
(11) the second latching valve (LV2), the 3rd latching valve (LV3), the 5th latching valve (LV5) are set all in closed mode, and
And first latching valve (LV1), the 4th latching valve (LV4), the 6th latching valve (LV6) are in opening；
(12) the 3rd latching valve (LV3) is opened, waits the temperature and pressure of two tanks to reach stabilization；
(13) the 3rd latching valve (LV3) and the 6th latching valve (LV6) are closed, the 5th latching valve (LV5) is opened, to the first tank
(TANK-A) aerating；Then, the 5th latching valve (LV5) is closed, the temperature in the first gas cylinder (1) and the first tank (TANK-A) is treated
After pressure remained steady, the pressure value of the second gas cylinder (2) that record is deflated and temperature value and it is pressurized
The pressure value and temperature value of the second tank (TANK-B) as calculate first state value, meanwhile, record the first differential manometer (DP1) pressure
The additive value of the pressure value of difference and the second gas cylinder (2) as the first storage pressure final states value, the pressure of the second differential manometer (DP2)
The additive value of the pressure value of difference and the second tank (TANK-B) as the first tank pressure final states value, the first gas cylinder (1) and
Temperature value in first tank (TANK-A) is used as the final states value for calculating temperature；
(14) open the 3rd latching valve (LV3) and the 6th latching valve (LV6), treat the first gas cylinder (1) and the second gas cylinder (2) and
After pressure in first tank (TANK-A) and the second tank (TANK-B) no longer changes, the 3rd latching valve (LV3) and the are closed
Six latching valves (LV6)；
(15) according to the pressure, pressure difference and temperature data obtained in abovementioned steps, and gas cylinder, the volume of tank of measurement in advance
Data, applied satellite Residual Propellant Measuring System Models are that can determine that the residual propellant body in the first tank (TANK-A)
Product, wherein, Residual Propellant Measuring System Models are as follows：
Wherein
In above formula, VlIt is the volume of propellant；PpiIt is the initial state pressure value of gas cylinder；PpfIt is the final states pressure value of gas cylinder；TpiIt is gas
The initial state temperature value of bottle；TpfIt is the final states temperature value of gas cylinder；VpIt is the volume of gas cylinder；VtIt is the volume of tank；PuiIt is in tank
Initial state pressure value；PufIt is final states pressure value in tank；TuiIt is initial state helium temperature in tank；TufIt is final states helium temperature in tank
Degree；ZpiIt is the initial state helium compressibility factor of gas cylinder, ZpfIt is the final states helium compressibility factor of gas cylinder, ZuiIt is initial state helium in tank
Compressibility factor, ZufIt is final states helium compressibility factor, Z in tankpi、Zpf、Zui、ZufObtained according to experiment；
(2) the step of measuring the Residual Propellant in the second tank (TANK-B) includes：
(21) the second latching valve (LV2), the 3rd latching valve (LV3), the 5th latching valve (LV5) are set all in closed mode, and
And first latching valve (LV1), the 4th latching valve (LV4), the 6th latching valve (LV6) are in opening；
(22) the 3rd latching valve (LV3) is opened, waits the temperature and pressure of two tanks to reach stabilization；
(23) the first latching valve (LV1) and the 6th latching valve (LV6) are closed, the 5th latching valve (LV5) is opened, to the second tank
(TANK-B) aerating；The 5th latching valve (LV5) is then shut off, the temperature in the first gas cylinder (1) and the second tank (TANK-B) is treated
After pressure remained steady, the pressure value of the second gas cylinder (2) that record is deflated and temperature value and it is pressurized
The pressure value and temperature value of the first tank (TANK-A) state value at the beginning of as calculating, meanwhile, the pressure in the first differential manometer of record (DP1)
The additive value of the pressure value of difference and the second gas cylinder (2) as storage pressure final states value, the pressure difference in the second differential manometer (DP2)
The additive value of value and the pressure value of the second tank (TANK-B) as tank pressure final states value, the first gas cylinder (1) and second stores
Temperature value in case (TANK-B) is used as the final states value for calculating temperature；
(24) open the first latching valve (LV1) and the 6th latching valve (LV6), treat the first gas cylinder (1) and the second gas cylinder (2) and
After pressure in first tank (TANK-A) and the second tank (TANK-B) no longer changes, the 3rd latching valve (LV3) and the are closed
Six latching valves (LV6)；
(25) according to the pressure, pressure difference and temperature data obtained in abovementioned steps, and gas cylinder, the volume of tank of measurement in advance
Data, applied satellite Residual Propellant Measuring System Models are that can determine that the residual propellant body in the second tank (TANK-B)
Product, wherein, Residual Propellant Measuring System Models are as follows：
Wherein
In above formula, VlIt is the volume of propellant；PpiIt is the initial state pressure value of gas cylinder；PpfIt is the final states pressure value of gas cylinder；TpiIt is gas
The initial state temperature value of bottle；TpfIt is the final states temperature value of gas cylinder；VpIt is the volume of gas cylinder；VtIt is the volume of tank；PuiIt is in tank
Initial state pressure value；PufIt is final states pressure value in tank；TuiIt is initial state helium temperature in tank；TufIt is final states helium temperature in tank
Degree；ZpiIt is the initial state helium compressibility factor of gas cylinder, ZpfIt is the final states helium compressibility factor of gas cylinder, ZuiIt is initial state helium in tank
Compressibility factor, ZufIt is final states helium compressibility factor, Z in tankpi、Zpf、Zui、ZufObtained according to experiment.
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| CN107702758B (en) * | 2017-08-30 | 2019-07-12 | 北京控制工程研究所 | One kind being based on Capacity method large size tank Residual Propellant accurate measurement method |
| CN112729498B (en) * | 2020-12-24 | 2021-10-29 | 上海空间推进研究所 | Method, system and medium for measuring residual propellant mass of propulsion system |
| CN113252131B (en) * | 2021-04-06 | 2022-10-18 | 上海宇航系统工程研究所 | System and method for measuring propellant allowance in storage tank of ascending section of carrier rocket |
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