CN103017852B - Method for measuring quantity of liquid propellant in storage tank - Google Patents
Method for measuring quantity of liquid propellant in storage tank Download PDFInfo
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- CN103017852B CN103017852B CN201210583876.4A CN201210583876A CN103017852B CN 103017852 B CN103017852 B CN 103017852B CN 201210583876 A CN201210583876 A CN 201210583876A CN 103017852 B CN103017852 B CN 103017852B
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Abstract
The invention provides a method for measuring a quantity of a liquid propellant in a storage tank, which comprises the following steps of: step S1, measuring initial pressures and temperatures of the storage tank and a gas cylinder and forecasting an initial gas volume V0 and a quantity m10 of the residual liquid propellant in the storage tank by utilizing a propellant quantity static measurement method; step S2, establishing a heat and mass transfer mathematical model used in the pressurizing process of a storage tank open system and carrying out simulation calculation by utilizing the measured initial conditions so as to obtain a relation that a gas phase temperature and a gas phase pressure are changed with time and the propellant quantity in the storage tank; step S3, injecting pressurizing gas into the storage tank by the gas cylinder, enabling holding time to be consistent with simulation calculation time and keeping a pipeline having excellent sealing performance; step S4, measuring a gas pressure and a gas temperature of the gas part in the storage tank at a preset moment and comparing the gas pressure and the gas temperature with a simulation result; and step S5, fitting actual propellant flow according to the simulation result and an experimental result and calculating the quantity of the residual propellant in the storage tank at any moment by a formula shown in the description under the condition of the known initial propellant quantity.
Description
Technical field
The present invention relates to Tank of Spacecraft and advance dosage measurement field, in particular to a kind of tank liquid propellant measuring method.
Background technology
Dosage information is advanced all to be of great importance in space flight and aviation and low temperature field, the number of spacecraft liquid propellant amount is directly connected to the life-span of spacecraft and the arrangement to spacecraft task, therefore in space flight mission period, as far as possible accurately estimate in tank and advance dosage.Such as, in survey of deep space task, when aircraft is in the unpowered earth free flight stage and leaves Earth's orbit, engine will restart once, even repeatedly.Therefore, must guarantee there are enough propellants before execution detection mission, the orbit maneuver ability of aircraft is estimated accurately, thus make a kind of high precision, stable, become key for the liquid propellant measuring method under microgravity condition reliably.
For the space liquid propellant loading technique in-orbit risen at present, need equally to measure liquid propellant amount exactly, thus determine the opportunity of annotating in-orbit and the propelling dosage needing filling; Advance the In-flight measurement result of dosage, directly impact provides the selection of the spacecraft of filling-up service and the reaction time of emission coefficient.Particularly for the filling task in-orbit of " multi-to-multi " scene, namely multiple Servicing spacecraft is implemented to annotate in-orbit to multiple passive space vehicle, advance the accurate testing result of dosage as the input quantity of the path optimization that annotates in-orbit, reliable reference can be provided for optimizing path of annotating in-orbit.
Conventional propellant measuring method carries out propelling dosage measurement mainly for closed system static on satellite, and measuring accuracy is not high yet, the method be successfully applied at present on satellite comprises bookkeeping method and gas law method, the former is subject to cumulative errors impact, measuring accuracy reduces gradually, and the latter does not have an applicability under tank leak case.The use of these methods also has many restrictive conditions: one is have requirement to tank type, as radioactivity survey method can only be used for barrier film tank; Two is that propellant type has requirement, as calorimetry can not be applied to cryogenic propellant; Three is need to apply extra disturbance to tank system, applies certain acceleration, obtain regular liquid level and measure as hydrodynamic method needs to increase propulsion system to tank system; Four is that measuring method is subject to modeling accuracy impact, fluid dynamics behavior all has relatively big difference with ground in micro-gravity conditions, certain heat is applied to tank system and can there is thermal stratification phenomenon, the light path that optical method applies light walking has very large uncertainty, in addition, also need many-sided restrictive conditions such as measurement mechanism quality is light, volume is little, low in energy consumption, reproducible, these restrictive conditions often cause measuring difficulty and even can not survey.And for the tank open system having fluid to flow out, also do not have good method to realize advancing dosage to measure in real time to it at present.For the rocket engine of the work of restarting that needs repeatedly to light a fire, real-time estimate advance dosage to ensure interior the sufficient fuel supply of tank is its normal reliable guarantee worked.
Summary of the invention
The present invention aims to provide the tank liquid propellant measuring method advancing dosage in a kind of high-precision real-time measurement tank, have external pressurization gas to enter tank to solve in prior art, when simultaneously having again propellant to flow out in tank residual propellant amount cannot the problem of kinetic measurement.
The invention provides a kind of tank liquid propellant measuring method, comprise the following steps: step S1: the original pressure being measured the gas fraction in tank by tank pressure transducer, utilizes the gas fraction initial temperature in tank temperature sensor measurement tank and tank wall initial temperature; By original pressure and initial temperature in storage pressure sensor and gas cylinder temperature sensor measurement gas cylinder; Utilize and advance dosage static measurement method to estimate initial gas volume V
0dosage m is advanced with remaining liq in tank
l0; Step S2: the heat and mass mathematical model setting up tank open system pressurization, utilizes and surveys measured starting condition and carry out simulation calculation, obtain gas phase temperature, gaseous pressure and advance the variation relation of dosage in time with in tank; Step S3: inject pressurization gas to tank by gas cylinder, holds time and analogue simulation time consistency, and keeps pipeline to have good sealing property; Step S4: gaseous tension and the gas temperature of measuring the gas fraction in predetermined time tank, and contrast with simulation result; Step S5: according to simulation result and experimental result, matching is actual propellant flow rate out, when known initial propulsion dosage, passes through formula
calculate the residual propellant amount in any moment tank.
Further, in step s 2, mathematical model comprises: wherein, and subscript g represents gas phase, and subscript l is liquid phase; Gas phase continuity equation:
liquid phase continuity equation:
wherein m
g1for pressurization gas quality in gas phase, m
g2for propellant vapor quality in gas phase, m
lfor liquid propellant quality, m
l0for the initial liquid mass utilizing static propellant to measure; Pressurization gas mass flow equation: work as P/P
hduring > 0.528, pressurization gas is subcritical flowing, has:
work as P/P
hwhen≤0.528, pressurization gas is overcritical flowing, has:
wherein, α is coefficient of flow, and P is gas phase stagnation pressure in tank, P
hfor pressurization gas dividing potential drop in tank, T
hfor pressurization gas temperature, A
minfor restricting element area, k is adiabatic exponent, and R is normalized molar specific heat, M
1for pressurization gas molal weight; Liquid oxygen surface volatilization mass transfer equation:
wherein, K
mfor mass transfer coefficient, A is that mass transfer surfaces is amassed, P
satfor liquid oxygen saturated vapour pressure, P
2for propellant partial vapour pressure in gas-phase space, M
2for propellant steam molal weight, T
satfor propellant saturation temperature; Energy conservation equation: Δ Q=Δ E+ ∑ h
inΔ m
in, in formula, Δ Q is gas-phase space to liquid propellant surface and vessel surface heat transfer capacity, and Δ E is the change of internal energy of gas-phase space, Δ m
infor flowing into the gaseous mass of gas-phase space, h
infor flowing into the enthalpy of gas-phase space; The heat transfer equation of container wall and gas-phase space comprises: the tank wall amount of stored heat of gas-phase space is: Δ Q
w=M
w1c
w(T
w, τ+Δ τ-T
w, τ)+M
w2c
w(T
w, τ+Δ τ-T
0); The heat exchange amount of gas and tank wall is: Δ Q
f=α
1f
1(T-T
w, τ+Δ τ)+α
2f
2(T-T
0); Wherein, C
wfor tank wall specific heat, M
w1for the quality of the tank wall that the τ moment contacts with gas-phase space, M
w2for the τ+Δ τ moment tank area that comes out is corresponding due to the outflow of liquid propellant and liquid oxygen volatilization tank quality, T
w, τ+Δ τfor τ+Δ τ moment tank wall surface temperature, T
0for propellant body temperature, T is gas-phase space temperature, F
1for the tank surface area in τ moment, F
2be τ+Δ τ moment due to the outflow of liquid propellant and volatilization and the tank surface area come out, have Δ Q
f=Δ Q
w.
Further, in step sl, dosage static measurement method is advanced to be gas inject method; By injecting the external high pressure gas of preset quality to tank, injecting rear tank temperature and pressure change by measuring, calculating the volume of liquid propellant.
Further, in step sl, dosage static measurement method is advanced to be volume advocate approach; By making tank change preset vol, utilize aerothermodynami equation and initial final state temperature, pressure measurement data and volume excitation amplitude to calculate gas volume, then calculate liquid propellant volume and quality in tank by tank cumulative volume and fluid density.
Further, in step sl, dosage static measurement method is advanced to be optical attenuator method; By at tank top to the known light of tank internal emission, light ray energy density is measured by the receiver being arranged on tank inside, and with the light ray energy density ratio of known light comparatively, by the relation of light ray energy density knots modification and amount of liquid, calculate liquid propellant volume or quality in tank.
According to tank liquid propellant measuring method of the present invention, utilize the gas cylinder that spacecraft carries, by measurement starting condition with after injecting the gaseous tension after certain gas and temperature by gas cylinder in tank, simulation calculation, thus simulate actual propellant flow rate, and then the residual propellant amount in any moment tank can be measured exactly.Measuring method precision of the present invention is high, and without the need to extra device, can meet Tank of Spacecraft and enter tank at outside pressurization gas, time when having again propellant to flow out in tank simultaneously, and the requirement of the measurement residual propellant amount of real-time high-precision.
Accompanying drawing explanation
The accompanying drawing forming a application's part is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is the principle schematic according to tank liquid propellant measuring method of the present invention; And
Fig. 2 is the simulation result schematic diagram according to tank liquid propellant measuring method of the present invention.
Embodiment
Below with reference to the accompanying drawings and describe the present invention in detail in conjunction with the embodiments.
As shown in Figure 1, tank liquid propellant measuring method provided by the invention, comprise the following steps: step S1: the original pressure being measured the gas fraction 3 in tank 1 by tank pressure transducer 5, utilize tank temperature sensor 6 to measure gas fraction 3 initial temperature in tank 1 and tank 1 wall initial temperature; Original pressure and initial temperature in gas cylinder 4 is measured by storage pressure sensor 5 ' and gas cylinder temperature sensor 6 '; Utilize and advance dosage static measurement method to estimate initial gas volume V
0dosage m is advanced with remaining liq in tank
l0; Step S2: the heat and mass mathematical model setting up tank open system pressurization, utilizes and surveys measured starting condition and carry out simulation calculation, obtain gas phase temperature, gaseous pressure and advance the variation relation of dosage in time with in tank; Step S3: inject pressurization gas to tank 1 by gas cylinder 4, holds time and analogue simulation time consistency, and keeps pipeline to have good sealing property; Step S4: gaseous tension and the gas temperature of measuring the gas fraction 3 in predetermined time tank 1, and contrast with simulation result; Step S5: according to simulation result and experimental result, matching is actual propellant flow rate out, when known initial propulsion dosage, passes through formula
calculate the residual propellant amount in any moment tank 1.The gas cylinder that the present invention utilizes spacecraft to carry, by measurement starting condition with after injecting the gaseous tension after certain gas and temperature by gas cylinder in tank, simulation calculation, thus simulate actual propellant flow rate, and then the residual propellant amount in any moment tank can be measured exactly.Measuring method precision of the present invention is high, and without the need to extra device, can meet Tank of Spacecraft and enter tank at outside pressurization gas, time when having again propellant to flow out in tank simultaneously, and the requirement of the measurement residual propellant amount of real-time high-precision.
Particularly, as shown in Figure 1, first utilize pressure transducer 5 to measure the original pressure of gas fraction 3 in tank 1, utilize temperature sensor 6 measurement gas part 3 initial temperature and tank 1 wall initial temperature, and utilize propelling dosage high precision static measurement method to estimate initial gas volume V
0with residual propellant amount m in tank
l0; Equally, another set of pressure transducer 5 ' and temperature sensor 6 ' is utilized to measure original pressure and initial temperature in gas cylinder 4;
Then set up the heat and mass mathematical model of tank open system pressurization, utilize and survey measured starting condition and carry out simulation calculation, obtain gas phase temperature, gaseous pressure and advance the variation relation of dosage in time with in tank.
Usually, mathematical model comprises the continuity equation, energy conservation equation, the heat transfer equation between gas phase and tank wall, the heat and mass equation between gas-liquid, actual gas Constitute equation etc. of gas phase and liquid phase; Meanwhile, as shown in Figure 2, set pre-supercharging 9, stop the time of supercharging 10 and maintenance supercharging 11, as time reference during experiment measuring.Subscript g, l represent gas phase and liquid phase respectively, and 1,2 pressurization gas and the propellant steams representing gas phase respectively, derivation process of establishing is as follows.
1) continuity equation is:
Wherein m
g1for pressurization gas quality in gas phase, m
g2for propellant vapor quality in gas phase, m
lfor liquid propellant quality, m
l0for the initial liquid mass utilizing static propellant to measure.
2) pressurization gas mass flow equation: work as P/P
hduring > 0.528, pressurization gas is subcritical flowing, has:
Work as P/P
hwhen≤0.528, pressurization gas is overcritical flowing, has:
In formula, α is coefficient of flow, and P is gas phase stagnation pressure in tank, P
hfor pressurization gas dividing potential drop in tank, T
hfor pressurization gas temperature, A
minfor restricting element area, k is adiabatic exponent, and R is normalized molar specific heat, M
1for pressurization gas molal weight.
3) liquid oxygen surface volatilization mass transfer equation is:
In formula, K
mfor mass transfer coefficient, A is that mass transfer surfaces is amassed, P
satfor liquid oxygen saturated vapour pressure, P
2for propellant partial vapour pressure in gas-phase space, M
2for propellant steam molal weight, T
satfor propellant saturation temperature.
In above formula, mass transfer coefficient K
mcalculated by following formula and obtain:
K
m=0.0292u
0.78X
-0.11Sc
-0.67 （6）
Wherein: u is liquid propellant airflow on surface flow velocity; X is liquid propellant surface mass transfer characteristic yardstick; Sc is Schmidt number,
wherein υ is kinematic viscosity coefficient, and D is coefficient of diffusion.
If liquid propellant is liquid oxygen, then the saturation pressure that the saturation temperature on liquid oxygen surface is corresponding with it is:
lgP
sat=9.13427-374.5/T
sat （7）
There is intrinsic relational expression in the saturation pressure that the saturation temperature of liquid propellant is corresponding with it.
4) energy conservation equation is
ΔQ=ΔE+∑h
in·Δm
in （8）
In formula, Δ Q is that gas-phase space is to liquid propellant surface and vessel surface heat transfer capacity; Δ E is the change of internal energy of gas-phase space; Δ m
infor flowing into the gaseous mass of gas-phase space; h
infor flowing into the enthalpy of gas-phase space.
5) heat transfer of container wall and gas-phase space:
The tank wall amount of stored heat of gas-phase space is: Δ Q
w=M
w1c
w(T
w, τ+Δ τ-T
w, τ)+M
w2c
w(T
w, τ+Δ τ-T
0) (9)
The heat exchange amount of gas and tank wall is: Δ Q
f=α
1f
1(T-T
w, τ+Δ τ)+α
2f
2(T-T
0) (10)
In above two formulas, C
wfor tank wall specific heat, M
w1for the quality of the tank wall that the τ moment contacts with gas-phase space; M
w2for the τ+Δ τ moment tank area that comes out is corresponding due to the outflow of liquid propellant and liquid oxygen volatilization tank quality; T
w, τ+Δ τfor τ+Δ τ moment tank wall surface temperature, T
0for propellant body temperature, T is gas-phase space temperature, F
1for the tank surface area in τ moment, F
2be τ+Δ τ moment due to the outflow of liquid propellant and volatilization and the tank surface area come out, obviously have Δ Q
f=Δ Q
w.
6) Constitute equation of actual gas
P
1V=Z
1m
g1RTM
g1,P
2V=Z
2m
g2RTM
g2 （11）
In formula: Z
1, Z
2the compressibility factor of pressurization gas and propellant steam respectively; R is universal gas constant; T is gas-phase space temperature in tank; M
g1, M
g2the molal weight of pressurization gas and propellant steam respectively.
To (11), arrangement abbreviation is carried out to formula (1), obtains gas phase temperature, gaseous pressure and advance the variation relation of dosage in time with in tank.
Then, as shown in Figure 2, pressurization comprises pre-supercharging 9, stop supercharging 10 and keep supercharging 11 three phases, pre-pressurization stages 9 starts after the primary data measuring tank 1 and gas cylinder 4, propellant is not had to flow out by gas cylinder below tank to tank injecting gas during pre-supercharging, by the time after in tank, gas-phase space pressure arrives predetermined pressure, gas cylinder stops to tank aerating, enter and stop pressurization stages 10, leave standstill a period of time (the general time is shorter), keeping the existing external pressurization gas of pressurization stages 11 tank to enter also has propellant to flow out with constant rate, the different propellant rates of outflow will produce different gaseous pressure growth curves.In tank 1, inject pressurization gas by gas cylinder 4 during experiment, hold time and analogue simulation time consistency; Pipeline is kept to have good sealing property; And measure the pressure and temperature of the gas fraction 3 in predetermined time tank 1, and contrast with simulation result.
According to simulation result and experimental result, simulate actual propellant flow rate, when known initial propulsion dosage, pass through formula
the surplus in any moment tank can be predicted.
The method that the present invention advances dosage static measurement used to tank can be one of following technology:
1, gas inject method: the gas being injected certain mass by external high pressure gas by connection valve pipeline to tank, the arousal effect that pressure increases is produced in tank, by the tank temperature variation that temperature sensor measurement excitation produces, measure the gas pressure change of excitation generation with pressure transducer, obtain the volume of liquid propellant.This method can make full use of the gas cylinder of spacecraft self.
2, volume advocate approach: the volume telescopic variation according to volume exciting bank, tank system being applied to certain form, consider the approximate incompressibility of liquid, the volume change applied is carried by gas completely, utilize aerothermodynami equation and initial final state temperature, pressure measurement data and volume excitation amplitude to calculate gas volume, then calculate liquid propellant volume and quality in case by tank cumulative volume and fluid density.
3, optical attenuator method: launch known light at tank top in tank, light is by liquid absorption, and simultaneously through the reflection many times of tank wall, last light is consistent in the energy density of any position of tank wall.By being arranged on the receiver of tank wall, light ray energy density can be measured, compare with luminous energy density known when launching and can obtain its knots modification, and the change of light ray energy density is relevant with amount of liquid, therefore can calculate liquid propellant volume or quality in tank.
As can be seen from the above description, the above embodiments of the present invention achieve following technique effect:
According to tank liquid propellant measuring method of the present invention, utilize the gas cylinder that spacecraft carries, by measurement starting condition with after injecting the gaseous tension after certain gas and temperature by gas cylinder in tank, simulation calculation, thus simulate actual propellant flow rate, and then the residual propellant amount in any moment tank can be measured exactly.Measuring method precision of the present invention is high, and without the need to extra device, can meet Tank of Spacecraft and enter tank at outside pressurization gas, time when having again propellant to flow out in tank simultaneously, and the requirement of the measurement residual propellant amount of real-time high-precision.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (5)
1. a tank liquid propellant measuring method, is characterized in that, comprises the following steps:
Step S1: the original pressure being measured the gas fraction (3) in tank (1) by tank pressure transducer (5), utilizes tank temperature sensor (6) to measure gas fraction (3) initial temperature in described tank (1) and described tank (1) wall initial temperature; Gas cylinder (4) interior original pressure and initial temperature is measured by storage pressure sensor (5 ') and gas cylinder temperature sensor (6 '); Utilize and advance dosage static measurement method to estimate initial gas volume V
0dosage m is advanced with original liquid in tank
l0;
Step S2: the heat and mass mathematical model setting up tank open system pressurization, utilizes and surveys measured starting condition and carry out simulation calculation, obtains gas phase temperature, gaseous pressure liquid propellant amount m in t and tank in time
lvariation relation;
Step S3: inject pressurization gas by described gas cylinder (4) to described tank (1), hold time and analogue simulation time consistency, and keep pipeline to have good sealing property;
Step S4: gaseous tension and the gas temperature of measuring the gas fraction (3) in predetermined time tank (1), and contrast with simulation result;
Step S5: according to simulation result and experimental result, matching is actual propellant flow rate out
dosage m is advanced at known original liquid
l0when, pass through formula
the remaining liq calculated in tank (1) described in any moment t advances dosage m
l.
2. tank liquid propellant measuring method according to claim 1, is characterized in that, in described step S2, described mathematical model comprises: wherein, and subscript g represents gas phase, and subscript l is liquid phase;
Gas phase continuity equation:
Liquid phase continuity equation:
Wherein m
g1for pressurization gas quality in gas phase, m
g2for propellant vapor quality in gas phase, m
lfor liquid propellant quality, m
l0for the initial liquid mass utilizing static propellant to measure;
Pressurization gas mass flow equation:
Work as P/P
hduring >0.528, pressurization gas is subcritical flowing, has:
Work as P/P
hwhen≤0.528, pressurization gas is overcritical flowing, has:
wherein, α is coefficient of flow, and P is gas phase stagnation pressure in tank, P
hfor pressurization gas dividing potential drop in tank, T
hfor pressurization gas temperature, A
minfor restricting element area, k is adiabatic exponent, and R is normalized molar specific heat, M
1for pressurization gas molal weight;
Liquid oxygen surface volatilization mass transfer equation:
wherein, K
mfor mass transfer coefficient, A is that mass transfer surfaces is amassed, P
satfor liquid oxygen saturated vapour pressure, P
2for propellant partial vapour pressure in gas-phase space, M
2for propellant steam molal weight, T
satfor propellant saturation temperature;
Energy conservation equation: Δ Q=Δ E+ ∑ h
inΔ m
in, in formula, Δ Q is gas-phase space to liquid propellant surface and vessel surface heat transfer capacity, and Δ E is the change of internal energy of gas-phase space, Δ m
infor flowing into the gaseous mass of gas-phase space, h
infor flowing into the enthalpy of gas-phase space;
The heat transfer equation of container wall and gas-phase space comprises:
The tank wall amount of stored heat of gas-phase space is: Δ Q
w=M
w1c
w(T
w, τ+Δ τ-T
w, τ)+M
w2c
w(T
w, τ+Δ τ-T
0);
The heat exchange amount of gas and tank wall is: Δ Q
f=α
1f
1(T-T
w, τ+Δ τ)+α
2f
2(T-T
0);
Wherein, C
wfor tank wall specific heat, M
w1for the quality of the tank wall that the τ moment contacts with gas-phase space, M
w2for the τ+Δ τ moment tank area that comes out is corresponding due to the outflow of liquid propellant and liquid oxygen volatilization tank quality, T
w, τ+Δ τfor τ+Δ τ moment tank wall surface temperature, T
0for propellant body temperature, T is gas-phase space temperature, F
1for the tank surface area in τ moment, F
2be τ+Δ τ moment due to the outflow of liquid propellant and volatilization and the tank surface area come out, have Δ Q
f=Δ Q
w.
3. tank liquid propellant measuring method according to claim 1, is characterized in that, in described step S1, described propelling dosage static measurement method is gas inject method;
By injecting the external high pressure gas of preset quality to described tank (1), injecting rear tank temperature and pressure change by measuring, calculating the volume of liquid propellant.
4. tank liquid propellant measuring method according to claim 1, is characterized in that, in described step S1, described propelling dosage static measurement method is volume advocate approach;
Preset vol is changed by making described tank (1), utilize aerothermodynami equation and initial final state temperature, pressure measurement data and volume excitation amplitude to calculate gas volume, then calculate the interior liquid propellant volume of described tank (1) and quality by tank cumulative volume and fluid density.
5. tank liquid propellant measuring method according to claim 1, is characterized in that, in described step S1, described propelling dosage static measurement method is optical attenuator method;
By at described tank (1) top to the known light of described tank (1) internal emission, light ray energy density is measured by being arranged on the inner receiver of described tank (1), and with the light ray energy density ratio of known light comparatively, by the relation of light ray energy density knots modification and amount of liquid, calculate the interior liquid propellant volume of described tank (1) or quality.
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