• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A system for regulating the flow rate of an electric propulsion thruster fluid of a spacecraft, comprising a propellant fluid reservoir and a flow regulator mounted at the outlet of said tank, the flow regulator comprising a heating element controlled by a computer and adapted to heat the propellant fluid and modify its physical properties in order to vary the flow of propellant fluid leaving the reservoir, said system being characterized in that the calculator further comprises a plurality of empirically determined empirical calibration curves defining the flow of propellant fluid according to the intensity of heating and environmental parameters, so that said computer also performs a function of determining the flow of propellant fluid.
    公开号:FR3014503A1
    申请号:FR1362430
    申请日:2013-12-11
    公开日:2015-06-12
    发明作者:Vanessa Vial；Anthony Lorand；Kevin Giboudeaux；Vaitua Leroi
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] GENERAL TECHNICAL FIELD The present invention relates to the field of electric thrusters such as in particular Hall effect motors, and more specifically the means for controlling the flow of propellant fluid delivered to an electric thruster in the context of an application for a spacecraft. STATE OF THE ART In electric thrusters, the propellant fluid is stored in a tank. It is equipped and connected control means to deliver a given flow to ensure the proper operation of the electric thruster. These control means typically include a flow controller commonly referred to as FCU "Flow Control Unit", or XFC "Xenon Flux Controller" when the propellant fluid is Xenon, which performs a controlled heating of the fluid by means of a thermocapillary in order to modify the physical properties of the fluid, and therefore its output flow of the reservoir.
    [0002] However, there is no definitive relationship between the thermocapillary heating current and the outflow taking into account the different variables influencing this relationship, and in particular the environmental parameters reflecting the ambient conditions in which the Flow regulator is used. An independent flow meter is therefore commonly associated with the flow controller, to measure the outgoing effective flow. However, in the case of space applications, such a multiplication of components to ensure the simple flow control function is problematic in that it adds additional mass, which is very restrictive given the power required to launch a given mass in geostationary orbit.
    [0003] A known alternative is to estimate the remaining mass of ergol by an analytical method, for example based on the pressure and temperature within the reservoir, to determine the consumption over time. Such a method makes it possible not to embark a flowmeter, but is however not very precise, and in order to maintain a margin of safety, space vehicles using such a method can thus be put to the end of life before the actual end of total consumption of the propellant fluid.
    [0004] PRESENTATION OF THE INVENTION The present invention thus aims to at least partially address this problem, by proposing a system for regulating the flow rate of an electric propulsion fluid of a spacecraft, comprising a propellant reservoir and a flow regulator. mounted at the outlet of said tank, the flow regulator comprising a heating element controlled by a computer and adapted to heat the propellant and modify its physical properties in order to vary the flow of propellant fluid leaving the tank, said system being characterized in that that the computer comprises a storage memory in which is loaded a plurality of empirically determined empirical calibration curves defining the flow of propellant fluid as a function of the heating intensity and the environmental parameters, so that said calculator also realizes a determinative function propellant flow rate. The present invention thus makes it possible to combine the flow control and flowmeter functions by a single component, namely a flow regulator without requiring structural modifications thereof, thereby reducing the total mass of the system with respect to a conventional system comprising two distinct components, and having increased accuracy with respect to a rate determining system from theoretical relationships. According to a particular embodiment, the empirical calibration curves are determined during ground tests of said control system under different environmental parameters. The calculator may also include a plurality of semi-empirical calibration curves, calculated from said empirical calibration curves, said semi-empirical calibration curves defining the propellant flow rate as a function of heating intensity for environment parameters distinct from those of empirical calibration curves.
    [0005] The computer may be configured to derive from these empirical calibration curves a semiempirical calibration curve defining the propellant flow rate as a function of heating intensity and environmental parameters.
    [0006] Said heating element is, for example, a thermocapillary tube providing heating as a function of the intensity of a heating current which passes through said thermocapillary tube. The invention also relates to a method for regulating the flow rate of the propulsion fluid supply of an electric thruster of a spacecraft by means of a flow regulator comprising a heating element controlled by a computer adapted to heat the propellant fluid at the outlet of the engine. a reservoir so as to modify the physical properties thereof and thus to modify the flow rate leaving the reservoir, characterized in that a plurality of empirical calibration curves are determined so as to define the flow of propellant fluid as a function of the heating intensity and environmental parameters, said calibration curves being loaded into the computer so that it also performs a function of determining the flow of propellant fluid. The empirical calibration curves are typically determined during ground testing of said control system under different temperature and pressure conditions. According to a particular embodiment, a plurality of semi-empirical calibration curves, calculated from said empirical calibration curves, are also determined, said theoretical calibration curves being loaded into the computer. According to a particular embodiment, when using the flow controller, said calculator calculates from said empirical calibration curves, a semi-empirical calibration curve defining the flow of propellant fluid as a function of the intensity of the heating and environment settings. PRESENTATION OF THE FIGURES Other features, objects and advantages of the invention will emerge from the description which follows, which is purely illustrative and nonlimiting, and which should be read with reference to the appended figures, in which: FIG. schematically represents a system according to one aspect of the invention; FIG. 2 is an example of empirical calibration curve of flow as a function of the intensity of the heating applied. DETAILED DESCRIPTION Figure 1 schematically illustrates a system according to one aspect of the invention.
    [0007] FIG. 1 illustrates a system for regulating the flow rate between a propellant fluid reservoir 2 and an electric thruster 3 connected by a conduit 23 on which a flow regulator 1 is arranged. The electric thruster may be, for example, an engine with an effect Hall, a pulsed plasma thruster, an ion thruster or more generally any electric thruster using a propellant. The flow regulator 1 comprises a heating element 11, typically supplied by a generator 12 and controlled by a computer 13. The heating element 11 applies direct or indirect heating to the propellant fluid circulating in the conduit 23, the intensity of which is driven by the computer 13. The flow regulator 1 is typically mounted at the outlet of the tank 2. The heating of the propellant fluid makes it possible to modify the physical properties of the propellant fluid, which modifies the pressure losses in the conduit 23, and modifies therefore the flow of propellant fluid conveyed to the electric thruster 3. The higher the propellant fluid temperature, the higher the viscosity of the latter, and therefore the flow of the propellant fluid in the conduit 23 decreases. The heating element 11 can be of different types. It may for example be a thermocapillary tube heating the conduit 23 as a function of the intensity of a heating current which passes through said thermocapillary tube, the heating current 25 then being delivered by the generator 12 and controlled by the computer 13. The propellant fluid flowing in the conduit 23 is thus heated indirectly by the thermocapillary tube, which heats it through the conduit 23. This embodiment is shown in FIG. 1. The thermocapillary tube then has for example a coil or spiral shape to increase the heating area relative to a cross section.
    [0008] The heating element 11 may also be a resistor disposed in the conduit 23, providing a direct heating of the propellant fluid in the conduit 23 as a function of the intensity of a heating current flowing through the resistor, the heating current then being delivered by the generator 12 and controlled by the computer 13. The heating element 11 may also be a heat exchanger, for example a fluid-fluid type heat exchanger, in which circulates a coolant whose temperature is controlled by the computer 13 so as to achieve a heat exchange with the propellant fluid flowing in the conduit 23 to bring it to the desired temperature. According to the present invention, the computer 13 is configured so as to also perform a flowmeter function, by delivering precise information relative to the flow of propellant fluid in the conduit 23 as a function of the intensity of the heating applied to the propellant by the element heating 11.
    [0009] The calculator 13 comprises a plurality of empirically determined empirical calibration curves defining the propellant flow rate as a function of the heating intensity and environmental parameters such as in particular the ambient temperature and the ambient pressure. These empirical calibration curves are loaded into a storage memory of the computer 13, so that they can be used during the operation of the system. These empirical calibration curves are loaded into a storage memory of the computer 13.
    [0010] The computer 13 is thus configured to include a set of empirical curves defining the flow rate value as a function of the heating intensity and as a function of the various environmental parameters considered. These empirical curves form a series of charts allowing the determination of the flow. Thus, depending on the environment parameters in use, for example depending on the parameters such as the system temperature and the input pressure of the system, the computer 13 determines the appropriate calibration curve, and determines the flow rate. propellant fluid in the conduit 23 depending on the intensity of the heating applied by the heating element 11. For example, from the system temperature, the system inlet pressure and the current applied to the heating element 11, the computer 13 determines the curve loaded in its storage memory that is closest to these different parameters, and thus deduces the flow rate value at this time.
    [0011] The flow controller 1 thus performs a flowmeter function via its computer 13, without requiring the addition of additional components, and therefore minimizing the overall mass of the system.
    [0012] The empirical calibration curves are, for example, determined during ground tests of the flow control system under different artificially applied environment parameters and substantially reproducing the environmental parameters to which the flow control system will be subjected during its control. use on a spacecraft. Figure 2 is an example of an empirical calibration curve of flow as a function of the applied heating intensity, for given environmental parameters. This curve was performed using a thermocapillary as a heating element, and indicates the flow through the thermocapillary as a function of the current in the thermocapillary which reflects the heating intensity.
    [0013] The computer 13 can thus, as a function of the change in the intensity of the heating applied during a duration T, determine the quantity of propellant fluid that has passed through the flow regulator 1 during this period T.
    [0014] Such curves establish a more precise relationship between the intensity of the heating and the flow rate than general theoretical formulas having a limited precision and not allowing a fine determination of the flow of propellant fluid as a function of the evolution of the different environmental parameters. such as, for example, temperature and ambient pressure. Advantageously, a plurality of semi-empirical calibration curves are made from the different empirical calibration curves obtained during tests, so as to have a finer increment between two successive curves and therefore an increased precision, without require an excessive number of tests. These semi-empirical calibration curves are for example obtained by considering a linear evolution between two empirical calibration curves. For example, if we consider two theoretical calibration curves for the change in flow as a function of the heating intensity, obtained for two distinct pressure values P1 and P2 and for the other environmental parameters which are constant, we can thus obtain a finer incrementation for pressure values between P1 and P2 from these two empirical calibration curves. It is of course also possible to apply the same principle for other parameters than the pressure, for example the ambient temperature. These semi-empirical calibration curves can be made by a ground computing unit following the realization of the empirical calibration curves, and then loaded into the computer 13.
    [0015] The semi-empirical calibration curves can also be directly performed by the computer 13 according to the conditions of use of the control system. Thus, it is then advantageous to load only the empirical calibration curves in the computer, reducing the memory required for storing the various information. The present invention thus makes it possible to perform the flowmeter function by the flow regulator 1, without requiring the addition of additional components, and thus makes it possible not to increase the total mass of the system while maintaining an accurate determination of the flow rate.
    权利要求:
    Claims (10)
    [0001]
    REVENDICATIONS1. A system for regulating the flow rate of a propulsion fluid of an electric thruster (3) of a spacecraft, comprising a reservoir (2) of propellant fluid and a flow regulator (1) mounted at the outlet of said reservoir (2), the regulator flow device (1) comprising a heating element (11) controlled by a computer (13) and adapted to heat the propellant and modify its physical properties in order to vary the flow of propellant fluid leaving the reservoir, said system being characterized in the computer (13) comprises a storage memory in which is loaded a plurality of empirically determined empirical calibration curves defining the propellant flow rate as a function of the heating intensity and environmental parameters, so that said computer (13) also performs a function of determining the flow of propellant fluid.
    [0002]
    2. System according to claim 1, wherein the empirical calibration curves are determined during ground tests of said control system under different environmental parameters.
    [0003]
    3. System according to one of claims 1 or 2, wherein said computer (13) comprises a plurality of semi-empirical calibration curves, calculated from said empirical calibration curves, said semi-empirical calibration curves. defining the propellant flow rate as a function of the heating intensity for environmental parameters distinct from those of the empirical calibration curves.
    [0004]
    4. System according to one of claims 1 to 3, wherein said computer (13) is configured for, from said empirical calibration curves, calculate a semi-empirical calibration curve defining the flow of propellant fluid based heating intensity and environmental parameters.
    [0005]
    5. System according to one of claims 1 to 4, wherein said heating element (11) is a thermocapillary tube providing heating as a function of the intensity of a heating current which passes through said thermocapillary tube.
    [0006]
    6. System according to one of claims 1 to 5 wherein said propellant fluid is Xenon.
    [0007]
    7. A method for regulating the flow rate of the propulsion fluid supply of an electric thruster (3) of a spacecraft by means of a flow regulator (1) comprising a heating element (11) controlled by a computer (13). ) adapted to heat the propellant fluid at the outlet of a reservoir (2) so as to modify the physical properties thereof and thus to modify the flow of propellant fluid leaving the reservoir (2), characterized in that a plurality of curves of The empirical calibration is determined so as to define the propellant fluid flow rate as a function of the heating intensity and the environmental parameters, said calibration curves being loaded into the computer (13) so that it also realizes a function of determining the flow rate of the propellant fluid. 25
    [0008]
    The method of claim 7, wherein the empirical calibration curves are determined during ground testing of said control system under different environmental parameters.
    [0009]
    The method according to one of claims 7 or 8, wherein a plurality of semiempirical calibration curves defined by interpolation from said empirical calibration curves are also determined, said theoretical calibration curves being loaded into the calculator. (13).
    [0010]
    The method according to one of claims 7 to 9, wherein when using the flow controller (1), said calculator (13) calculates from said empirical calibration curves a semi-standard calibration curve. empirical definition of the propellant fluid flow as a function of heating intensity and environmental parameters.
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    CN105814310B|2019-04-16|
    JP2016539852A|2016-12-22|
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    法律状态:
    2015-12-14| PLFP| Fee payment|Year of fee payment: 3 |
    2016-12-05| PLFP| Fee payment|Year of fee payment: 4 |
    2017-11-21| PLFP| Fee payment|Year of fee payment: 5 |
    2018-02-09| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170717 |
    2019-11-20| PLFP| Fee payment|Year of fee payment: 7 |
    2020-11-20| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1362430A|FR3014503B1|2013-12-11|2013-12-11|IMPROVED FLOW CONTROL SYSTEM FOR THE SUPPLYING FLUID SUPPLY OF AN ELECTRIC SPRAY PROPELLER OF A SPATIAL VEHICLE|FR1362430A| FR3014503B1|2013-12-11|2013-12-11|IMPROVED FLOW CONTROL SYSTEM FOR THE SUPPLYING FLUID SUPPLY OF AN ELECTRIC SPRAY PROPELLER OF A SPATIAL VEHICLE|
    RU2016127842A| RU2667202C1|2013-12-11|2014-12-09|Improved flow regulating system for supplying propellant fluid to electric thruster of space vehicle|
    US15/103,240| US9828975B2|2013-12-11|2014-12-09|Flow regulating system for supplying propellant fluid to an electric thruster of a space vehicle|
    CN201480067644.0A| CN105814310B|2013-12-11|2014-12-09|The improved stream regulating system for promoting fluid is provided to the electric plating propulsion of spacecraft|
    JP2016538748A| JP6509866B2|2013-12-11|2014-12-09|Improved flow control system for supplying propellant fluid to spacecraft electric thrusters|
    EP14827482.2A| EP3080449B1|2013-12-11|2014-12-09|Improved flow regulating system for supplying propellant fluid to an electric thruster of a space vehicle|
    PCT/FR2014/053238| WO2015086982A1|2013-12-11|2014-12-09|Improved flow regulating system for supplying propellant fluid to an electric thruster of a space vehicle|
    IL246101A| IL246101A|2013-12-11|2016-06-07|Improved flow regulating system for supplying propellant fluid to an electric thruster of a space vehicle|
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