• 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 method of regulating pressure within a first rocket engine propellant tank comprising a first propellant tank (16) containing a first propellant and a second propellant tank (18) containing a second propellant, and a pressure regulating device within the first reservoir comprising a gas generator (60) and a heat exchanger (74) cooperating with the gas generator so as to vaporize the first propellant before it is reintroduced into the first reservoir (16), the gas generator and the heat exchanger are both fed first ergol by a single first pump (64) while the gas generator is fed second propellant by a single second pump, in which the flow of the first motor pump is driven according to a first parameter while the flow rate of the second motor pump is controlled according to a second parameter.
    公开号:FR3042821A1
    申请号:FR1502259
    申请日:2015-10-26
    公开日:2017-04-28
    发明作者:Valentin Hue；Gonidec Serge Le
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    FIELD OF THE INVENTION
    The present invention relates to a method for regulating the pressure within a first rocket engine propellant tank.
    STATE OF THE PRIOR ART
    A rocket engine is usually a motor in which the gases at the outlet of the combustion chamber are discharged via a nozzle so as to develop a thrust. The gases are generally derived from the combustion of a first propellant with a second propellant. For example, the first propellant is an oxidant, such as oxygen, while the second propellant is a fuel, such as hydrogen or methane.
    The propellants are stored in tanks in the liquid state, and these tanks are kept under pressure to ensure that the flow of propellant directed to the combustion chamber is regular. For this, a sample of each propellant from its reservoir passes into a heat exchanger in order to be heated and vaporized, before being reinjected in the gaseous state into its reservoir so as to form, in each reservoir, a gaseous propellant under pressure.
    Such a rocket engine is generally designed to respect flight phases called "propulsion phases", during which the engine must develop a thrust capable of steering the rocket, and phases called "ballistic phases" during which the engine is off, so that the rocket is subject only to the laws of ballistics.
    The first part of the flight is a propulsion phase, during which a strong thrust is necessary to put the rocket into orbit. Then, for orbital maneuvers and return to earth, propulsion phases alternate with ballistic phases, a small thrust applied over relatively short periods of time being sufficient.
    It is important however that the engine can restart quickly and in good conditions after a ballistic phase. This means that, even during a ballistic phase, during which the engine is not active, sufficient pressure must be provided in the liquid propellant tanks so that the flow required to restart the engine can be obtained without delay. . In other words, it is important to vaporize propellant samples and reinject them into the tanks, even during a ballistic phase, while the engine is inactive. At the same time, it is important to ensure that propellant vaporization is achieved without significantly degrading engine performance during the propulsion phase.
    Known pressure regulating devices for regulating the pressure within rocket engine propellant tanks, and their implementation are generally complex, and notably involve the presence and control of several valves with variable openings. There is therefore a need for simplification.
    PRESENTATION OF THE INVENTION
    One embodiment relates to a method for regulating pressure within a first rocket engine propellant tank, said rocket engine comprising a first propellant tank containing a first propellant and a second propellant tank containing a propellant. second ergol distinct from the first propellant, and a device for regulating the pressure within the first reservoir comprising a gas generator and a heat exchanger (or first heat exchanger) cooperating with the gas generator so as to vaporize the first propellant before its reintroduction into the first tank, the gas generator and the heat exchanger being both fed first propellant by a single first variable flow motor pump while the gas generator is fed second propellant by a single second pump motor variable flow rate , characterized in that the flow rate of the first motor pump is controlled as a function of a first parameter ta in that the flow rate of the second motor pump is controlled according to a second parameter distinct from the first parameter.
    It is therefore understood that the gas generator generates heat by the combustion of a mixture of first and second propellants, this heat being used at least in part by the heat exchanger to vaporize the first propellant, this first propellant vaporized (ie in gaseous form) is then reintroduced into the first tank, whereby one can increase the pressure within the first tank.
    It is also understood that the first motor pump is common to the gas generator and the heat exchanger. Thus, the flow from the first motor pump is distributed between the gas generator and the heat exchanger. Of course, the first motor pump is separate from the second motor pump.
    The inventors have found that by controlling the flow rate of each motor pump independently of one another, and according to parameters which are distinct and uncorrelated, it is possible to regulate in a simple and reliable manner the pressure within the first reservoir. . Of course, the parameters are parameters relating to the elements of the regulating device, including the first tank. For example, these parameters may be the propellant flow, the pressure or the temperature at a given point of the regulating device, including the first reservoir.
    It is thus possible to eliminate the variable opening valves of the pressure regulating devices of the state of the art, and to retain only any on-off valves component isolation, the latter valves having only one safety function and no regulation. Such on-off valves are of course simpler, more reliable, and less expensive than the valves with variable opening of the state of the art.
    Furthermore, the pressure regulation being carried out by motor pumps, these motor pumps being part of auxiliary circuits, ie not being part of the supply circuits of the rocket engine combustion chamber, the regulation method is applicable both during the propulsion phases only during the ballistic phases.
    In some embodiments, the first parameter is the pressure within the first reservoir.
    In other words, the regulation method comprises a step of measuring the actual pressure within the first reservoir, a step of comparing the actual pressure with a predetermined pressure, and a step of controlling the flow rate of the first motor pump in according to the result of the comparing step so as to reduce the difference between the actual pressure and the predetermined pressure. For example, the predetermined pressure is the desired pressure (or set pressure) within the first reservoir.
    Thus, to increase / decrease the pressure within the first reservoir, the flow rate of the first motor pump is increased / decreased. Indeed, by increasing / decreasing the flow rate of the first motor pump, it increases / decreases the amount of first propellant brought to the heat exchanger, and therefore the volume of first ergol vaporized and reinjected into the first reservoir, thanks to which one increases / decreases the pressure within the first tank.
    In some embodiments, the second parameter is the temperature of the gas generator.
    In other words, the regulation method comprises a step of measuring the actual temperature within the gas generator, a step of comparing the actual temperature with a predetermined temperature, and a step of controlling the flow rate of the second motor pump. depending on the result of the comparing step so as to reduce the difference between the actual temperature and the predetermined temperature. For example, the predetermined temperature is the desired temperature (or set temperature) within the gas generator to ensure the proper functioning of the gas generator in order to prevent its extinction (ie to ensure a sufficient heat flow to vaporize the propellant at within the exchanger) while remaining below the maximum acceptable temperature.
    The temperature within the gas generator is a function of the mixing ratio between the two propellants, namely the flow rate of first propellant injected into the gas generator divided by the flow rate of the second propellant injected into the gas generator. In addition, in normal operation, this ratio is always less than one (1), so that the flow rate of the first propellant is always lower than the flow rate of the second propellant. Thus, in order to increase / decrease the temperature of the gas generator, for a flow rate of the first given motor pump, the flow rate of the second motor pump is decreased / increased so as to make the mixing ratio of the two propellants tend towards an away (ie at most the ratio is close to 1, at most the temperature is high, and vice versa).
    To summarize, the pressure within the first reservoir and the temperature of the gas generator must be equal to predetermined values for the proper operation of the rocket engine. When the first parameter is the pressure within the first reservoir and the second parameter is the temperature of the gas generator, controlling the flow of the first motor pump makes it possible to adjust the pressure within the first reservoir while controlling the flow rate of the second motor pump makes it possible to adjust the flow rate of the second propellant in the gas generator as a function of the flow variation of the first motor pump to adjust the pressure within the first reservoir, so that the temperature within the generator gas remains at the desired value, and thus ensure the durability of the heat supply of the heat exchanger. For example, these two parameters, which are the pressure within the first reservoir and the temperature of the gas generator, are each regulated by a regulatory sub-process, these two subprocesses being coupled for example by a multivariable corrector.
    In some embodiments, the flow rate of the first motor pump is controlled solely according to the first parameter while the flow rate of the second motor pump is controlled solely according to the second parameter.
    These two parameters being sufficient to regulate the pressure within the first tank, by limiting themselves to taking into account these two parameters, only the control method and the associated control device are simplified.
    In some embodiments, the pressure regulation within the second propellant tank is independent of the pressure regulation within the first tank.
    In other words, the regulation of the pressure within the second reservoir is performed independently of the flow rate of the first and second motor pumps. This ensures that the regulation of a reservoir is not carried out at the expense of regulating the other reservoir.
    In some embodiments, the first propellant and the second propellant are cryogenic liquid propellants.
    The method is indeed particularly well suited to regulating the pressure in a first tank containing a cryogenic liquid propellant.
    In some embodiments, the first propellant is oxygen while the second propellant is hydrogen or methane.
    The method is in fact particularly well suited to regulating the pressure in a first reservoir containing oxygen.
    One embodiment also relates to a computer program comprising instructions for executing the pressure control method according to any one of the embodiments described herein when said program is executed by a computer.
    One embodiment also relates to a computer readable recording medium on which the computer program according to any one of the embodiments described in this disclosure is recorded.
    The recording medium may be any entity or device capable of storing a program. For example, the medium may comprise storage means, such as a ROM, for example a CD-ROM or a microelectronic circuit ROM, or a magnetic recording medium, for example a floppy disk. or a hard drive.
    Alternatively, the recording medium may be an integrated circuit in which the program is incorporated, the circuit being adapted to execute or to be used in the execution of the method in question.
    BRIEF DESCRIPTION OF THE DRAWINGS The invention and its advantages will be better understood on reading the detailed description given below of various embodiments of the invention given as non-limiting examples. This description refers to the pages of appended figures, in which: FIG. 1 represents a rocket engine, and FIG. 2 represents the various steps of a method of regulating the pressure within the first tank of the rocket engine. of Figure 1.
    DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS
    Figure 1 shows a rocket engine 10 having a combustion chamber 12 and a nozzle 14 having a diverging. The combustion chamber 10 is fed with propellants from a first reservoir 16 containing a first propellant, for example an oxidizing propellant such as oxygen, and is also supplied with second propellant from a second reservoir 18 containing a second propellant, for example a reducing propellant, for example hydrogen or methane. The reducing propellant serves as fuel, while the oxidizing propellant serves as an oxidizer for combustion. The first propellant feed from the first tank 16 comprises a first main pipe 22 discharging into a first turbopump 24 and a first injection pipe 26 connecting the outlet of the first turbopump 24 to the combustion chamber 12. in the second propellant from the second reservoir 18 comprises a second supply main pipe 30 in a second turbopump 32 and a second injection line 34 connected to the outlet of the second turbopump 32.
    Permit valves 22A and 30A are respectively disposed on the main supply lines 22 and 30.
    In this case, the engine 10 of the "expander" type, that is to say a motor in which the second propellant is removed and vaporized to provide energy to parts of the engine. More specifically, the second injection pipe 34 discharges into a heater 36 which cooperates with the wall of the combustion chamber 12 to, in the propulsion phase, heat the second propellant flowing in the heater so as to vaporize it. At the outlet of the heater 36, the second propellant is fed through a supply line 38 into the turbine portion 32A of the second turbopump 32 to drive its turbine so as to actuate its pump portion 32B. At the outlet of the turbine portion 32A, the second propellant is fed through a feed line 40 to the inlet of the turbine portion 24A of the first turbopump 24 to drive its turbine so as to actuate its pump portion 24B. At the outlet of the turbine part 24A, the second propellant is brought to the inlet of the combustion chamber 12 via an injection pipe 42. An isolation valve 44 is disposed on this injection pipe 42 which is connected to the second reservoir 18 via a system of pressurizing and expansion valves 47. Thus, the second vaporized propellant returns to the reservoir 18 to form a gaseous sky whose pressure can be regulated by the system 47.
    Thus, the rocket engine 10 comprises a regenerative heat exchange circuit that uses the combustion heat of the combustion chamber 12 to vaporize the second propellant. This regenerative heat exchange circuit includes the heater 36 and the lines 38, 40, 42 and 46. A bypass line 48 with a variable opening valve 48A is disposed between the lines 38 and 42 to bypass the turbine inlets. Another bypass line 50 with a variable opening valve 50A is disposed between the outlet of the turbine portion of the second turbopump 32 and the injection line 42 to bypass the turbine portion 24A of the first turbopump 24. The injection first propellant in the combustion chamber 12 operates directly through the injection pipe 26 which extends between the outlet of the first turbopump 26 and the inlet of the injection chamber 12. An isolation valve 52 is disposed on the pipe 26 to allow or stop the injection flow.
    The rocket engine 10 comprises a device for regulating the pressure within the first tank 16 comprising a gas generator 60 and a first heat exchanger 74 which cooperates with the gas generator 60. A single first variable flow pump pump 64 feeds the gas generator 60 and the first heat exchanger 74 first ergol. A single second motor pump 70 with variable flow supplies the gas generator 60 in the second propellant. The gas generator 60 also cooperates with a second heat exchanger 90 separate and independent of the first heat exchanger 74, which in this example is also fed by the second motor pump 70 in second propellant.
    The gas generator 60 is fed first ergol by a first supply line 62 connected to the first tank 16 by the first motor pump 64 variable rate. A first supply valve 66 is disposed on the first supply line 62. The gas generator 60 is supplied with the second propellant by a second supply line 68 connected to the second reservoir 18 by the second variable flow pump pump 70. A second supply valve 72 is disposed on the second supply line 68. It will be noted that the supply lines 62 and 68 connecting the tanks to the gas generator 60 form auxiliary lines in comparison with the main supply lines 22. and 30.
    The first heat exchanger 74 cooperates with the gas generator 60 to vaporize the first propellant, the first propellant feed being carried out by the first motor pump 64. This first heat exchanger 74 may for example be formed by a double-walled tube, which cooperates with the exhaust 76 of the gas generator 60, and wherein the first propellant can circulate. For this purpose, the first heat exchanger 74 may be supplied by a first branch pipe 78 connected to the first supply line 62. In this case, this connection is made upstream of the first supply valve 66. In this case, the first stitching line 78 is connected to the first supply line 62 by a stitching valve 80 which can be opened or closed to allow or not to feed the first heat exchanger 74 in the first propellant. The output of the first heat exchanger 74 is connected to the first tank 16 by a first return line 82 so that the first propellant vaporized in the first heat exchanger 74 supplies the gas of the first tank 16.
    The second heat exchanger 90 cooperates with the gas generator 60 to vaporize the second propellant feeding second propellant being performed by the second pump. For example, this second heat exchanger 90 may comprise a double-walled tube disposed around the exhaust 76 of the gas generator 60. This second heat exchanger 90 can be supplied with the second propellant by a second branch pipe 94 connected to the second supply line 68. In the present case, this connection is made upstream of the second feed valve 72. In this case, the second tapping pipe 94 is connected to the second supply line 68 by a valve stitching 88 which can be opened or closed to allow or not the supply of the second heat exchanger second ergol. The output of the second heat exchanger 90 is connected to the second tank 18 by a return line 100 so that the second propellant vaporized in the second heat exchanger 90 can be reinjected into the gas of the second tank 18 via the valve system 47 .
    In FIG. 1, the arrows represent the direction of circulation of the propellants in the hydraulic circuits. FIG. 1 represents a state where the rocket engine 10 is in operation (propulsion phase), ie a phase in which combustion is carried out in the combustion chamber 12, so that the regulation of the pressure in the second tank 18 is performed in a manner known otherwise by the system 47, the valve 88 being closed. When the rocket engine 10 does not operate (ballistic phase), ie when no combustion is carried out in the combustion chamber 12, the valve 88 is open so that the pressure regulation in the second tank is carried out from otherwise known manner using the second heat exchanger 90 and the system 47.
    In this example, for the regulation of the pressure within the first reservoir 16, the rocket engine 10 also comprises a control unit 110 connected to a pressure sensor 112 for measuring the pressure within the first reservoir 16 and to a sensor temperature controller 114 for measuring the temperature within the gas generator 60. The control unit 110 is also connected to the first and second motor pumps 64 and 70 to control their respective flow rate. It should be noted that the links with the control unit 110 are shown in broken lines to distinguish them from the previously described propellant circuits.
    The method of regulating the pressure within the first reservoir 16 will now be described with reference to FIG.
    During step I, the actual pressure Pr within the first reservoir 16 and the actual temperature Tr within the gas generator 60 are measured. In step II, the actual pressure Pr is compared with a pressure P and the actual temperature Tr is compared with a predetermined temperature T. In step III, the flow rate of the first turbopump 64 is controlled according to the result of the comparison between the actual pressure Pr and the predetermined pressure P of in order to reduce the difference between the actual pressure and the predetermined pressure while controlling the flow rate of the second turbopump 70 as a function of the result of the comparison between the actual temperature Tr and the predetermined temperature T so as to reduce the difference between the actual temperature and the predetermined temperature. In this example, the control unit 110 performs the various steps of this method. Thus, by controlling the flow rate of each of the motor pumps 64 and 70, the pressure within the first reservoir 16 is regulated in a perennial manner, that is to say while ensuring the proper operation of the gas generator 60. Of course, when stage III is completed, the process is repeated from stage I to ensure a continuous regulation of the pressure within the first tank.
    Of course, the measurement and comparison of the actual pressure within the first reservoir with the predetermined pressure and the measurement and comparison of the actual temperature within the gas generator with the predetermined temperature can be performed simultaneously or sequentially, or in parallel within two independent or coupled subprocesses. Likewise, the driving of the first and of the second motor pump can be carried out simultaneously, sequentially or alternatively in two independent or coupled subprocesses.
    Although the present invention has been described with reference to specific exemplary embodiments, it is obvious that modifications and changes can be made to these examples without departing from the general scope of the invention as defined by the claims. In particular, individual features of the various embodiments illustrated / mentioned can be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense.
    It is also obvious that all the features described with reference to a method can be transposed, alone or in combination, to a device, and conversely, all the features described with reference to a device can be transposed, alone or in combination, to a method.
    权利要求:
    Claims (8)
    [1" id="c-fr-0001]
    A method of regulating pressure within a first rocket engine propellant tank, said rocket engine (10) comprising a first propellant tank (16) containing a first propellant and a second propellant tank. (18) containing a second propellant distinct from the first propellant, and a device for regulating the pressure within the first reservoir comprising a gas generator (60) and a heat exchanger (74) cooperating with the gas generator (60) of in order to vaporize the first propellant before it is reintroduced into the first tank (16), the gas generator (60) and the heat exchanger (74) both being fed first propellant by a single first pump (64) with a flow rate variable while the gas generator (60) is supplied with second ergol by a single second motor pump (70) variable flow, characterized in that the flow rate of the first motor pump (64) is controlled according to a first tand parameter is that the flow rate of the second motor pump (70) is controlled according to a second parameter distinct from the first parameter.
    [2" id="c-fr-0002]
    The control method of claim 1, wherein the first parameter is the pressure within the first reservoir (16).
    [3" id="c-fr-0003]
    3. Control method according to claim 1 or 2, wherein the second parameter is the temperature of the gas generator (60).
    [4" id="c-fr-0004]
    4. Method according to any one of claims 1 to 3, wherein the flow rate of the first motor pump (64) is controlled solely according to the first parameter while the flow rate of the second motor pump (70) is controlled solely according to the second parameter.
    [5" id="c-fr-0005]
    5. Control method according to any one of claims 1 to 4, wherein the first propellant and the second propellant are cryogenic liquid propellants,
    [6" id="c-fr-0006]
    6. The method of regulation according to any one of claims 1 to 5, wherein the first propellant is oxygen while the second propellant is hydrogen or methane.
    [7" id="c-fr-0007]
    A computer program comprising instructions for executing the pressure control method according to any one of claims 1 to 6 when said program is executed by a computer.
    [8" id="c-fr-0008]
    8. Computer-readable recording medium on which the computer program according to claim 7 is recorded.
    类似技术:
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    同族专利:
    公开号 | 公开日
    EP3163063B1|2018-12-05|
    FR3042821B1|2017-12-01|
    RU2016141644A|2018-04-28|
    JP2017089625A|2017-05-25|
    JP6843582B2|2021-03-17|
    US10415507B2|2019-09-17|
    US20170114753A1|2017-04-27|
    EP3163063B8|2019-01-16|
    EP3163063A1|2017-05-03|
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    CN111120150B|2019-12-13|2021-05-04|上海空间推进研究所|Method and device for improving performance of liquid path management system of spacecraft propulsion system|
    CN113495590A|2021-07-09|2021-10-12|中国人民解放军63796部队|Small-sized design of simulated filling storage tank and parallel filling and discharging dynamic control method thereof|
    法律状态:
    2016-10-13| PLFP| Fee payment|Year of fee payment: 2 |
    2017-04-28| PLSC| Publication of the preliminary search report|Effective date: 20170428 |
    2017-10-23| PLFP| Fee payment|Year of fee payment: 3 |
    2018-10-23| PLFP| Fee payment|Year of fee payment: 4 |
    2019-10-23| PLFP| Fee payment|Year of fee payment: 5 |
    2021-07-09| ST| Notification of lapse|Effective date: 20210605 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1502259A|FR3042821B1|2015-10-26|2015-10-26|METHOD OF CONTROLLING PRESSURE WITHIN A FIRST ERGOL TANK OF FIRED ENGINE|FR1502259A| FR3042821B1|2015-10-26|2015-10-26|METHOD OF CONTROLLING PRESSURE WITHIN A FIRST ERGOL TANK OF FIRED ENGINE|
    US15/333,339| US10415507B2|2015-10-26|2016-10-25|Method of regulating the pressure within a first rocket engine propellant tank|
    EP16195416.9A| EP3163063B8|2015-10-26|2016-10-25|Method for adjusting the pressure inside a first propellant tank of a rocket engine|
    RU2016141644A| RU2016141644A|2015-10-26|2016-10-25|METHOD FOR REGULATING THE PRESSURE INSIDE THE FIRST FUEL TANK OF THE ROCKET ENGINE|
    JP2016208428A| JP6843582B2|2015-10-26|2016-10-25|How to regulate the pressure in the rocket engine's first propellant tank|
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