• 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:
    Engine (10) for a spacecraft comprising a chemical thruster comprising a nozzle (30) for the ejection of combustion gases, as well as a Hall effect thruster. The engine is arranged such that the nozzle serves as ejection channel particles ejected by the Hall effect thruster when it is in operation. The engine can deliver a high thrust with a small specific impulse or a relatively low thrust with a strong specific impulse.
    公开号:FR3021301A1
    申请号:FR1454553
    申请日:2014-05-21
    公开日:2015-11-27
    发明作者:Stephan Joseph Zurbach；Frederic Raphael Jean Marchandise
    申请人:SNECMA SAS；
    IPC主号:
    专利说明:

    [0001] The present invention relates to the field of engines for spacecraft, in particular satellites. In the context of certain applications, it may be desirable for a spacecraft to have two modes of operation, either high thrust or high specific impulse. There are two examples: Posting and keeping a satellite in orbit: the setting up of a satellite requires a strong thrust in order to transfer it to geostationary orbit as quickly as possible; and a propulsion with a high specific impulse to maintain the position of the satellite for fifteen years. Exploration: it could be interesting to have a thruster to take off from a celestial object and once in space, to implement a propulsion with a high specific impulse. In a known manner, the propulsion of satellites is generally done by means of two technologies: chemical propulsion and electric propulsion. These two modes of propulsion each have a specific operating range in a Specific Impulse (Isp) / Boost diagram: Schematically, chemical propulsion makes it possible to reach high thrusts, but the specific impulse remains limited to 450 seconds. Conversely, electric propulsion achieves high specific pulses (2000 seconds), but the thrust remains relatively low. For the propulsion of the satellites, Hall effect thrusters have thus been used in steering and / or trajectory control systems (AOCS) of spacecraft and particularly in AOCS of geostationary satellites. The Hall effect thrusters allow to obtain a very high specific impulse (Isp), of the order of 1500 s, which makes it possible to obtain precise steering of the orientation and / or the position of the vehicle with a considerably less complexity and complexity than conventional systems using inertial devices, such as, for example, reaction wheels, in combination with chemical thrusters for their desaturation. 3 02 13 0 1 2 However, a Hall effect thruster with a high specific impulse can normally only achieve a very small thrust. As a consequence, AOCs incorporating Hall effect thrusters are typically supplemented by chemical thrusters for certain fast maneuvers, such as orbit transfer or positioning. However, this has the disadvantage of increasing the cost and overall complexity of the spacecraft, to the detriment of its reliability. In conclusion, none of the available technologies (chemical propulsion, electric propulsion) makes it possible to ensure propulsion in the two operating domains envisaged, that is to say on the one hand with a strong thrust and a relatively specific impulse. In addition, it is an object of the invention to provide a motor for spacecraft capable of providing propulsion in these two operating domains, and this without rendering it possible. the overly heavy or complex spacecraft. To achieve this objective, in the context of the invention there is provided a spacecraft motor comprising a chemical thruster comprising a nozzle for the ejection of combustion gases and a Hall effect thruster, the engine being arranged in such a way said nozzle serves as a channel for ejecting particles ejected by the Hall effect thruster when the latter is in operation. Thus, the two technologies, namely chemical propulsion and electric propulsion, are integrated within the same engine. The pooling of certain means, in particular the nozzle, makes it possible to make the engine thus constituted relatively compact. As a result, the engine thus formed remains relatively simple and inexpensive, given its extended operating capabilities thanks to the simultaneous presence of two thrusters. In one embodiment, the Hall effect thruster comprises a magnetic circuit; and in a section following a meridian half-plane, the magnetic circuit has a horseshoe shape with an air gap open to a downstream side of the nozzle, so that the magnetic circuit is able to generate a magnetic field in the gap of the magnetic circuit.
    [0002] The magnetic field generated in the gap is preferably substantially radial. The terms "upstream" and "downstream", in the present context, are defined with respect to the direction of normal circulation of the propellant gas in the direction defined by the central axis of the nozzle. The magnetic field is not necessarily generated throughout the air gap but at least in a part thereof, generally located at the downstream end thereof. A half-meridian plane is a half-plane delimited by an axis, in this case that of the nozzle.
    [0003] In this embodiment, obtaining a radial magnetic field in the nozzle is made possible in particular by the fact that it, instead of being hollow and empty like most conventional chemical thrusters, contains a portion of the magnetic circuit. This inner portion of the magnetic circuit is disposed generally along the axis of the nozzle and has a usually axisymmetric shape or even of revolution around this axis. Preferably, the meridian half-planes in which the section of the magnetic circuit has a horseshoe shape are angularly distributed regularly around the axis of the nozzle. Ideally, the magnetic circuit has such a section in all meridian half-planes, that is to say 360 ° around the axis of the nozzle. Preferably, in view in a meridian half-plane, the combustion chamber of the chemical thruster is arranged inside the magnetic circuit.
    [0004] In one embodiment, the nozzle has an annular axial section, and passes through the air gap of the magnetic circuit. The air gap therefore also has an annular axial section. An axial section here designates a section in a plane perpendicular to the axis of the nozzle. In one embodiment, the magnetic circuit comprises at least one outer magnetic core located around the nozzle and an inner magnetic core located radially inside the nozzle, and in a section along a meridian half-plane, sections of said inner core and said at least one outer core form the branches of said horseshoe shape.
    [0005] In one embodiment, the Hall effect thruster further comprises an electric circuit capable of generating an electric field in the nozzle, and the electrical circuit comprises an anode and a cathode respectively disposed upstream and downstream of the air gap of the circuit. magnetic. The anode and the cathode can be arranged in different ways. In one embodiment, the anode comprises a portion of the nozzle. It may for example be part of the wall of the nozzle. In another embodiment, the anode is disposed within the nozzle. In one embodiment, and in particular in the previous embodiment, the anode is electrically isolated from the nozzle. The anode may be disposed in the vicinity of fluid injectors (propellant injectors) in the combustion chamber, for the chemical propellant, and / or in the vicinity of particle injectors, for the effect propellant. Hall: that is to say, in general quite at the upstream end of the flow path of the fluids in the engine. In one embodiment, axially of the air gap, inner and outer walls of the nozzle are electrically insulating material. These inner and outer walls of the nozzle may in particular be made of ceramic material, which is particularly suitable for its electrical, magnetic and erosion resistance characteristics. The insulating walls may for example be formed by two electrically insulating rings 25 which delimit said air gap respectively inwardly and outwardly. In one embodiment, the nozzle has a combustion chamber at an upstream end, connected to a diverging at a downstream end. The Hall effect thruster further comprises at least one particle injector. In one embodiment, this particle injector is capable of injecting particles into said combustion chamber. The particles may be an inert gas, for example xenon. The present invention also relates to a spacecraft 35 incorporating at least one engine as described above.
    [0006] The invention will be better understood and its advantages will appear better, on reading the detailed description which follows, of two embodiments shown by way of non-limiting examples. The description refers to the accompanying drawings in which: Figure 1 is a partial schematic view in axial section of a spacecraft comprising a motor according to a first embodiment of the invention. FIG. 2 is a partial schematic perspective view of the engine illustrated in FIG.
    [0007] Figures 1 and 2 show a motor 10 according to the invention. It is part of a spacecraft 100, in this case a satellite. This engine is a hybrid engine, capable of operating as a chemical propellant or as a Hall effect thruster. To allow its operation as a chemical propellant or Hall effect propellant, the engine 10 is connected to propellant tanks (not shown, it may be a single propellant or two propellants), as well as to a tank of propellant gas. This motor 10 generally has a shape of revolution about an X axis. It is arranged inside a casing 20 of substantially cylindrical shape X axis. A first axial end 22 of this casing, on one side upstream, is closed by a substantially flat bottom 24 perpendicular to the axis X, while the other end 26 (downstream end) is partially closed by a substantially flat bottom 25 also perpendicular to the axis X. The bottom 25 is traversed by a large annular passage 28 of gas ejection. The bottom 25 has a generally disk-like shape perpendicular to the axis X. Due to the presence of the annular passage 28, the bottom 25 is constituted by a disc 56, and by an annular ring 58 located radially around the annular passage 28 The ring gear 58 is integrally formed with the casing 20. The motor 10 comprises a chemical propellant 11. This chemical propellant 11 comprises a nozzle 30 arranged inside the casing 20.
    [0008] The nozzle 30 is of generally annular shape around the axis X. More generally, the nozzle 30 may also be axisymmetric. However, non-axisymmetric shapes can alternatively be envisaged, for example, with an oval cross-section or racetrack.
    [0009] Whether or not the section of the nozzle 30 has a revolution or axisymmetric shape, the nozzle 30 is generally annular in shape and therefore comprises not only a radially outer wall 34, but also a radially inner wall 32. These walls are concentric around the X axis.
    [0010] The nozzle 30 is closed on the upstream side (left in FIG. 1) and open on the downstream side. From upstream to downstream, the nozzle 30 has firstly a combustion chamber 36, a convergent 38, then a divergent 40. These elements are arranged to allow the operation of the engine 10 as a chemical propellant 11 The chemical thruster 11 further comprises injectors 42 for the injection of propellants. These are arranged to allow the injection of propellants at the upstream end of the combustion chamber 36. For this purpose, they are connected to sources of propellants (not shown) 20 by a circuit of The motor 10 also comprises a Hall effect thruster 50. This thruster 50 firstly comprises a magnetic circuit 52. This magnetic circuit 52 comprises: the casing 20 itself, which is made of ferromagnetic material and forms thus an external magnetic core; the bottoms 24 and 25, made of ferromagnetic material; and a shaft-shaped central magnetic core 54 which extends along the axis X. The disk 56 which constitutes a portion of the bottom 25 forms the downstream end of the shaft 54. magnetic circuit 52 indicated above are arranged to allow a lossless circulation of a magnetic field through the magnetic circuit. To protect the downstream portion of the nozzle from wear and to contain the electronic cloud formed in the air gap of the magnetic circuit, the axially downstream portions of the walls 32 and 34 are formed by rings of ceramic material, respectively referenced 82 and 84. These rings are positioned at the air gap of the magnetic circuit 52. The magnetic circuit 52 further comprises an inner annular coil 70 and an outer annular coil 72, which serve to generate the magnetic field necessary for the operation of the effect thruster. Lobby. These two coils are concentrically formed about the X axis. The coil 70 is formed around the shaft 54 inside (radially) of the wall 32 (i.e., between the shaft 54 and the wall 32). The coil 72 is formed on the inner face of the cylindrical casing 20, and more precisely between this inner face and the outer wall 34 of the nozzle 30. Axially, the coils 70 and 72 are placed slightly downstream of the convergent 38 of the nozzle 30. More generally, these coils can be axially at any level on the X axis from the combustion chamber, upstream, and up to a position immediately upstream of the ceramic rings 82 and 84, downstream. The coils 70 and 72 are powered by a source of electrical energy not shown. In the magnetic circuit 52, the central magnetic core 54 and the outer magnetic core (the housing 20) are arranged in such a way that their polarities are opposite. The circuit 52 is arranged to generate a substantially radial magnetic field in the annular passage 28, which thus constitutes the air gap of the circuit 52. In other embodiments, the magnetic circuit may have a different structure than the Circuit 52. The important thing is that the magnetic circuit is able to generate a radial magnetic field in the ejection passage (here, the passage 28) of the Hall effect thruster. The intensity of this magnetic field gradually decreases from the ejection passage (28) to the convergent 38 of the nozzle. In the embodiment shown, the attenuation of the magnetic field (which is maximum at the axial level of the passage 28) is caused by internal and external magnetic screens 77, so as to reduce the intensity of the magnetic field in the vicinity of the anode 62.
    [0011] These are respectively formed on the inner surface of the housing 20 and on the outer surface of the shaft 54 and mechanically support the coils 70 and 72. These coils 70 and 72 are substantially cylindrical coils, each of which turns is substantially an X-axis circle. In another embodiment, the coil 72 may be replaced by a plurality of identical coils 72, each having an axis parallel to the X axis, the coils 72 being arranged axisymmetrically around of the outer wall 34 of the nozzle 30. The downstream part of the nozzle 30 passes or extends in the gap 28 of the circuit 52. In a section along a meridian half-plane (FIG. therefore has a horseshoe shape, with an air gap 28 open to the downstream side 26 of the nozzle 30. The horseshoe shape is formed from the bottom 24, respectively the section of the housing 20, to the outside, and the central core section 54, at the int which form the two branches of the horseshoe. The thruster 50 also comprises an electric circuit 60. This circuit comprises an anode 62 situated axially about halfway up the divergent 40, a cathode 64 located downstream of the end 26 of the nozzle 30, and a source of electrical voltage. 66 connecting the anode 62 to the cathode 64. More generally, the anode 62 may be axially at any level on the X axis from the combustion chamber, upstream, and to a position immediately in position. upstream of the ceramic rings 82 and 84, downstream. The anode 62 is constituted mainly by the inner wall 34 of the nozzle 30: it is thus integrated with the nozzle 30, while being electrically isolated from it. The cathode 64 is fixed on the disk 56, on the outer side, that is to say downstream of the shaft 54. In FIG. 2, the cathode 64 is shown in dotted lines. The cathode 64 is connected to the voltage source 66 by a cable flowing inside the inner wall 32 of the nozzle 30. Advantageously, this cable flows inside the shaft 54.
    [0012] Finally, the thruster comprises, at the upstream end of the nozzle 30, propellant gas injectors 75. These are arranged to allow the injection of propellant gas at the upstream end of the combustion chamber 36. this purpose, they are connected to a source of propellant gas (not shown) by an injection circuit 76. The propellant gas may be xenon, which has the advantages of a high molecular weight and comparatively low ionization potential . However, as in other Hall effect thrusters, a wide variety of propellant gases could be used.
    [0013] The engine 10 has two main modes of operation, namely electric propulsion and chemical propulsion. In chemical propulsion, propellants are injected into the combustion chamber 36 via the injectors 42. They are burned in this chamber; The combustion gases are accelerated by the convergent 38 and the divergent 40 and ejected at a high speed by the downstream opening 28 of the nozzle 30. In Hall effect propulsion, the engine 10 operates in the following manner. An electrical voltage, typically of the order of 150 to 800 V when xenon is used as a propellant gas, is established between the cathode 64 downstream of the downstream end of the nozzle 30 and the anode 62. The cathode 64 then begins to emit electrons, which are largely trapped in a magnetic chamber formed by the magnetic field created by the magnetic circuit 52, adapted to the desired performance 25 and the propellant gas used, and which is typically of the order of 100 at 300 gauss with xenon as propellant gas. The electrons trapped in this magnetic chamber will thus form a virtual cathode grid. High energy electrons (typically 10 to 40 eV) escape the magnetic chamber in the direction of the anode 62, while propellant gas is injected into the nozzle 30 through the injectors 70. The impacts between these electrons and propulsive gas atoms ionize the propellant gas, which is then accelerated to the downstream end 26 of the nozzle 30 by the electric field E generated by the coils 70 and 72. As the mass of the propellant gas ions is of several orders of magnitude. Magnitude higher than that of electrons, the magnetic field does not confine these ions in the same way as electrons. The thruster 50 thus generates a plasma jet which is ejected at an extremely high speed through the downstream end of the nozzle 30, which produces a thrust substantially aligned with the central axis X.
    [0014] The operation of the thruster 50 is similar to that of the thruster described in document US2003 / 0046921 A1. Optionally, the engine 10 could furthermore comprise, downstream of the rings 82 and 84, an additional nozzle section, in order to allow additional expansion. combustion gases, when the chemical thruster is in operation. The annular shape of the nozzle 30 thus makes it possible to use it not only as a channel for the combustion of propellants and the ejection of combustion gases, in chemical propulsion, but also as an ion acceleration channel. in electrical operation. In particular, the arrangement of the magnetic core 54 in the form of a shaft on the axis of the nozzle does not prevent the operation of the chemical thruster 11. In addition, the position of the cathode downstream of the bottom 25 and protected by the the end of the shaft 54 (the cathode 64 is in direct contact with the center 20 of the disc 56) allows that it is not touched by the flow of combustion gas, which it could not be permanently exposed. Although the present invention has been described with reference to a specific exemplary embodiment, it is obvious that various modifications and changes can be made to this example without departing from the general scope of the invention as defined by the claims. In addition, individual features of the mentioned embodiment may be combined in additional embodiments. Therefore, the description and drawings should be considered in an illustrative rather than restrictive sense. 30
    权利要求:
    Claims (11)
    [0001]
    REVENDICATIONS1. An engine (10) for a spacecraft comprising a chemical propellant (11) comprising a nozzle (30) for the ejection of combustion gases; the engine being characterized in that it comprises a Hall effect thruster (50), arranged in such a way that said nozzle serves as a channel for ejecting particles ejected by the Hall effect thruster when the latter is in operation.
    [0002]
    An engine according to claim 1, wherein the Hall effect thruster (50) comprises a magnetic circuit (52); and in a section following a meridian half-plane, the magnetic circuit has a horseshoe shape with an air gap (28) open towards a downstream side (26) of the nozzle, so that the magnetic circuit is able to generate a magnetic field in the gap of the magnetic circuit.
    [0003]
    3. Engine according to claim 2, characterized in that the nozzle (30) has an axial section of annular shape, and passes through the gap of the magnetic circuit (52).
    [0004]
    4. Motor according to claim 3, characterized in that the magnetic circuit comprises at least one outer magnetic core (20) located around the nozzle (30) and an inner magnetic core (54) located radially on the inside. of the nozzle, and in a section along a meridian half-plane, sections of said inner core and said at least one outer core form the branches of said horseshoe shape. 30
    [0005]
    5. Motor according to any one of claims 2 to 4, wherein the Hall effect thruster further comprises an electric circuit (60) capable of generating an electric field in the nozzle, and the electric circuit comprises an anode (62). and a cathode (64) respectively disposed upstream and downstream of said gap (28). 35
    [0006]
    The engine of claim 5, wherein the anode (62) comprises a portion of the nozzle (30).
    [0007]
    The engine of claim 5, wherein the anode (62) is disposed in the nozzle and electrically isolated therefrom.
    [0008]
    8. Motor according to any one of claims 2 to 7, characterized in that at the axial level of the gap (28), inner and outer walls (32,34) of the nozzle are of electrically insulating material. , especially ceramic.
    [0009]
    9. Engine according to any one of claims 1 to 8, characterized in that the nozzle has a combustion chamber (36) at an upstream end, connected to a divergent (40) at a downstream end.
    [0010]
    10. Motor according to claim 9, wherein the Hall effect thruster further comprises at least one particle injector (72), capable of injecting particles into said combustion chamber (36). 20
    [0011]
    Spatial machine incorporating at least one motor (1) according to any one of claims 1 to 10.
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    法律状态:
    2015-05-19| PLFP| Fee payment|Year of fee payment: 2 |
    2015-11-27| PLSC| Publication of the preliminary search report|Effective date: 20151127 |
    2016-05-25| PLFP| Fee payment|Year of fee payment: 3 |
    2017-04-27| PLFP| Fee payment|Year of fee payment: 4 |
    2018-02-02| CD| Change of name or company name|Owner name: SAFRAN AIRCRAFT ENGINES, FR Effective date: 20170719 |
    2018-04-23| PLFP| Fee payment|Year of fee payment: 5 |
    2019-04-19| PLFP| Fee payment|Year of fee payment: 6 |
    2020-04-22| PLFP| Fee payment|Year of fee payment: 7 |
    2021-04-21| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1454553A|FR3021301B1|2014-05-21|2014-05-21|MOTOR FOR SPACE ENGINE, AND SPACE ENGINE COMPRISING SUCH AN ENGINE|FR1454553A| FR3021301B1|2014-05-21|2014-05-21|MOTOR FOR SPACE ENGINE, AND SPACE ENGINE COMPRISING SUCH AN ENGINE|
    JP2016568567A| JP6645987B2|2014-05-21|2015-05-13|Engine for spacecraft and spacecraft equipped with the above-mentioned engine|
    US15/312,421| US10023328B2|2014-05-21|2015-05-13|Engine for a spacecraft, and spacecraft comprising such an engine|
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    PCT/FR2015/051258| WO2015177438A1|2014-05-21|2015-05-13|Engine for a spacecraft, and spacecraft comprising such an engine|
    RU2016150114A| RU2678240C2|2014-05-21|2015-05-13|Engine for spacecraft and spacecraft comprising such engine|
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    IL249063A| IL249063A|2014-05-21|2016-11-20|Engine for a spacecraft, and spacecraft comprising such an engine|
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