EP3350441B1 - Verfahren zur treibmittelversorgung des antriebs eines satelliten und nach diesem verfahren angetriebenes satellitenantriebsmodul - Google Patents

Verfahren zur treibmittelversorgung des antriebs eines satelliten und nach diesem verfahren angetriebenes satellitenantriebsmodul Download PDF

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EP3350441B1
EP3350441B1 EP16778690.4A EP16778690A EP3350441B1 EP 3350441 B1 EP3350441 B1 EP 3350441B1 EP 16778690 A EP16778690 A EP 16778690A EP 3350441 B1 EP3350441 B1 EP 3350441B1
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cathode
plasma
anodes
propulsion
helical
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French (fr)
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EP3350441A1 (de
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Luc HERRERO
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Comat Concept Mecanique Et Assistance Technique
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00—Using plasma to produce a reactive propulsive thrust
    • F03H1/0006—Details applicable to different types of plasma thrusters
    • F03H1/0012—Means for supplying the propellant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H1/00—Using plasma to produce a reactive propulsive thrust
    • F03H1/0087—Electro-dynamic thrusters, e.g. pulsed plasma thrusters

Definitions

  • the invention relates to a power supply method for vacuum arc spatial propulsion, called VAT - acronym for "Vacuum Arc Thruster” in English terminology - and to a space vehicle propulsion module (also called satellite “in the present text) intended to implement such a method.
  • VAT - acronym for "Vacuum Arc Thruster” in English terminology -
  • space vehicle propulsion module also called satellite “in the present text
  • the invention relates to the field of satellite propulsion with a storage of the propulsive material in solid form.
  • plasma propulsion modules operate using a gas (usually xenon) stored in tanks, the engines having the role of ionizing and accelerating this gas to create the thrust needed to put the satellite in motion.
  • the gas storage propulsion module has been replaced by a solid storage propulsion module.
  • the solid storage propulsion systems can be classified according to several types: pulsed plasma propulsion systems or PPT, acronym for “Pulsed Plasma Thruster”, vacuum arc systems known as VAT, acronym for “Vacuum Arc Thruster”, and PLT laser ablation systems, the acronym for “Photonic Laser Thruster”, which uses a solid material (PTFE or metal) as a propellant. Ablation of this material is achieved by the impact of a high power density laser on the surface of the propellant solid.
  • a PPT propulsion system consists of conductive electrodes - anode and cathode - separated by an insulation serving as a propellant material, generally PTFE (acronym for "poly-tetrafluoroethylene").
  • the electrodes are connected via a high voltage circuit. When the voltage at the terminals of a capacitor of this circuit is sufficient to form an intense current on the surface of the insulator, the latter vaporizes. This vaporization causing an increase in the number of neutral particles available in the vacuum, the electronic avalanche can then occur between the electrodes.
  • the high temperature of the plasma thus causes the Laplace force to cause the acceleration of the plasma in the direction of thrust.
  • the ionized plasma thus formed is engaged at high speed through a channelized outlet to produce a pulsed propulsive reaction force.
  • This type of PPT propulsion has the advantage of being able to consume large quantities of PTFE, namely several kilograms, which ensures a long thrust time for the propulsion unit.
  • this technology offers a low propulsive efficiency, of the order of a few percent, and a specific impulse level (less than 800s) much lower than that obtained by the propulsion technology VAT, which provides a much higher level of impulse. high (greater than 1400s).
  • the VAT type propulsion uses the material of the cathode and not the insulator as a propellant.
  • electrical energy is stored in a high voltage circuit and released during the implementation of an arc initiation system.
  • This arc initiation system is based on the creation of an initial plasma between the electrodes. This plasma generates an electronic discharge between the cathode and the anode.
  • the electronic current takes place between the anode and the cathode and warms it locally by Joule effect to create a cathode spot.
  • This cathode spot generates a temperature sufficient to emit by evaporation neutral metal particles which are then ionized and accelerated near the cathode surface by substantially faster electrons.
  • each plasma pulse corresponds to a push pulse.
  • the repetition frequency of the pulses as well as their durations and intensities are determined by a power electronics.
  • the amount of material ejected at each pulse is substantially the same.
  • VAT propulsion examples are described in patent documents US 7,053,333 and US 2011/258981 A1 .
  • These systems generally comprise a hollow tube-shaped cathode and a central cylindrical anode (or vice versa) coaxial, separated by an electrical insulation of aluminum silicate over substantially their entire length.
  • the insulation is covered with a metal film to promote the formation of micro-plasmas that extend along the propulsion initiator plasma.
  • the superheated and consumed metal film is replaced by redeposition of the cathode material through the plasma arc.
  • a magnetic core coupled to a coil creates a magnetic field to orient the particles in the same direction to provide effective propulsion.
  • a spring - arranged in the propulsion module against the rear end face of the cathode - exerts a pressure on the cathode to bring its other end facing an end of the cathode. anode that is not separated by insulation.
  • This spring advance mechanism allows to consume only a few grams of cathode, which greatly limits the duration of thrust and is still insufficient to perform missions typically dedicated to space vehicles.
  • the invention aims to achieve a consumption of several kilograms of cathode, or even tens of kilograms or more, in the context of a propulsion type VAT, without degrading the performance of this type of propulsion.
  • the invention provides for driving the cathode in an optimized helical movement so as to allow the consumption of substantially all the usable cathode material.
  • the subject of the present invention is a feeding method for the vacuum type electric arc satellite propulsion, consisting in guiding an annular cathode in a helical path around a central axis, to be arranged at immediate proximity and radially to the cathode - several anodes regularly distributed in a plane perpendicular to the central axis, to adjust the pitch of the helical path of the cathode, as well as the advance of the cathode on its helical path and the intensity of the electronic discharge impact cycles between the cathode and the anodes, so that the helices formed by the electronic discharges between the cathode and each of the anodes are juxtaposed, and straighten the plasma jet formed by the electronic discharges according to the central axis to form a plasma that generates a propulsive reaction force parallel to this axis (X'X).
  • the consumption of cathode material is optimized by an abrasion of substantially the entire surface of the cathode that can be used.
  • the increase in the number of anodes makes it possible to better parallelize the arcs and thus to increase the intensity of the thrust.
  • This method allows an excellent vectorization of the thrust thanks to the possibility of choosing the location of the site of creation of the arc by powering up the anode corresponding to this site.
  • the thrust can be pulsed with a variable frequency.
  • the invention also relates to a satellite propulsion module for implementing the method defined above.
  • a satellite propulsion module for implementing the method defined above.
  • Such a module comprises a generally annular frame having a central axis and wherein is arranged an annular metal cathode guided by threading / tapping in helical connection with this frame, and a central hollow shaft and coaxial with the frame.
  • On a transverse wall of this central shaft is fixed a circular support consisting of an insulating material and equipped with metal anodes regularly distributed in circumference.
  • energy storage capacitors connect each anode to the cathode to provide, after the formation of a pre-plasma, the energy to generate electronic discharge cycles.
  • a rotational drive mechanism is connected to the cathode to impart to it a movement of step-by-step movement in connection with the helical guide formed between the frame and the cathode.
  • This module presents in particular robustness and simplification qualities of the mechanism for raising the cathode and the integration of its constituent elements in the same frame.
  • a circular support 10 - in the form of disk - is equipped with eight anodes 1, fixed by screws 11 on its circumference.
  • the anodes 1 are distributed regularly in a radial symmetry.
  • An annular cathode 2 surrounds the circular support 10 at a small distance from the anodes 1, approximately 10 mm in the example illustrated, so that a circular end edge 2b of the cathode 2 is substantially in close proximity to the anodes 1.
  • the cathode 2 extends along a longitudinal axis coinciding with the central axis X'X of the support 10 which extends transversely with respect to the cathode 2, perpendicularly to the central axis X'X.
  • the cathode 2 is coupled to a frame 20 which encompasses it longitudinally.
  • the circular support 10 has radial stiffening ribs 12, terminated by connecting rivets 13, via spacing pins 14, to a plate 30 which is also circular and arranged inside the frame 20.
  • An electromagnetic coil 3 of cylindrical shape is integrated on the outer cylindrical face 20e of the frame 20, parallel to the cathode 2, so that the end edge 3b of the electromagnetic coil 3 is at the level of the anodes 1.
  • FIG. 1 The views of module 100 of Figures 2a and 2b , respectively in perspective cut along a longitudinal plane passing through the axis X'X ( figure 2a ) and in frontal section ( figure 2b ), show more precisely the interior of the frame 20.
  • This frame 20 has a longitudinal hollow central shaft 2A X'X axis which extends at its ends to form transverse walls 21A and 21B.
  • the transverse wall 21A serves as a base for the circular support 10 and the other transverse wall 21B forms an end wall of the frame 20.
  • the optical terminations 5 are coupled to optical fiber ends 6 integrated in the longitudinal central shaft 2A of the frame 20.
  • the other ends of the optical fibers are coupled to lasers (not shown) for emitting high power density radiation. for example, 10 8 W / m 2 .
  • a helical guidance system for the annular cathode 2 is made from a thread / tapping type 2L connection between the internal cylindrical face 20i of the frame 20 and the external cylindrical face 2e of the cathode 2.
  • This helical guidance is implemented movement by a mechanism comprising a ring gear 7 arranged under the cathode 2 and driven in rotation by a worm 8 mounted on the axis of an electric motor 9.
  • the annular cathode 2 thus describes a helical path around a central axis X'X according to the pitch of the helical connection 2L.
  • the cathode 2 is driven step-by-step by the helical guidance system with a frequency allowing to draw some million arcs between two advances corresponding to a 1 ⁇ 4 of degree in rotation.
  • the electric drive motor 9 ( Figures 2a and 2b ) rotates the cathode intermittently all these few million cycles.
  • An arc trip is generated in the immediate vicinity of each anode 1 by the cone of laser radiation 1p focused by each optical termination 5 on the cathode 2.
  • An initial plasma 2p is formed by a local heating and amplified during successive electronic discharges between the cathode 2 and each of the anodes 1.
  • the shots in this same zone form a crater of diameter equal to 1d and which will form a helix 1H as the helical advance of the cathode 2.
  • Each cycle of impacts of arcs corresponds to a few hundred thousands of bows.
  • the cathode 2 is set in motion on the helical guide path 2T. This movement is only a few degrees and allows each anode to begin the formation of a new crucible adjacent to the preceding one.
  • the crucibles formed by the cycles of impacts of successive arcs from two adjacent anodes 1 then describe parallel helices 1H.
  • the value of the pitch "p T " of the guide path 2T of the cathode 2 is predetermined so that the adjacent helices 1H of width 1d are juxtaposed because of the arc firing frequency used.
  • all consumable cathodic material is used, which can represent several tens to several hundred kilograms depending on the thickness and height of the cathode.
  • the initial or pre-plasma plasma jet 2p formed in the transverse plane of the support 10 by tearing off the cathode material 2 ( Figures 2a and 2b ) and amplified by successive electronic discharges, is straightened and accelerated along the central axis X'X to form a plasma 3p that generates a propulsive reaction force.
  • the recovery and acceleration are produced axially by the application of a magnetic field "B" induced by the electromagnetic coil 3.
  • the invention is not limited to the embodiments described and shown.
  • the arcing between the cathode and each anode can be caused by the establishment of a high voltage between these electrodes, for example greater than 1000V, or by spark plugs adapted.
  • the cathode can be rotated by indexing leaf springs or by any type of indexable rotary actuator (paddle, rack, etc.).
  • the number of anodes is advantageously adapted to the dimensions of the propulsion module and can reach for example 12 or 16 or more.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Plasma Technology (AREA)

Claims (9)

  1. Versorgungsverfahren für den Satellitenantrieb mit Vakuumlichtbogen, dadurch gekennzeichnet, dass es darin besteht, eine Ringkathode (2) gemäß einer Schraubenbahn (2T) um eine Mittelachse (X'X) zu führen, mehrere gleichmäßig in einer Ebene lotrecht zur Mittelachse (X'X) verteilte Anoden (1) - in direkter Nähe zu und radial bezüglich der Kathode (2) - anzuordnen, die Steigung (pT) der Schraubenbahn (2T) der Kathode (2) sowie den Vorschub der Kathode (2) auf ihrer Schraubenbahn (2T) und die Intensität der Stoßzyklen von Elektronenentladungen zwischen der Kathode (2) und den Anoden (2) so zu regeln, dass die durch die Elektronenentladungen zwischen der Kathode (2) und jeder der Anoden (1) gebildeten Schraubenlinien (1H) nebeneinander liegen, bis das ganze zur Verfügung stehende Kathodenmaterial verbraucht und der von den Elektronenentladungen gemäß der Mittelachse (X'X) gebildete Plasmastrahl (2p) gleichgerichtet wird, um ein Plasma (3p) zu bilden, das eine Antriebsreaktionskraft parallel zu dieser Achse (X'X) erzeugt.
  2. Versorgungsverfahren nach Anspruch 1, wobei ein Vorplasma (2p) in direkter Nähe jeder Anode (1) erzeugt wird, um eine von den Elektronenentladungen verstärkte Elektronenlawine auszulösen.
  3. Versorgungsverfahren nach einem der Ansprüche 1 oder 2, wobei die Steigung (pT) der Schraubenbahn (2T) der Kathode (2) abhängig von der Abmessung (1d) von Mulden bestimmt wird, die nacheinander durch jeden Zyklus von Lichtbogenstößen gebildet werden, die von der am nächsten liegenden Anode (1) kommen, wobei die Folge von benachbarten Mulden kombiniert mit der Schraubenbewegung der Kathode (2) dann für jede Anode (1) eine schraubenförmige Rille (1H) bildet, und die so gebildeten Schraubenlinien (1H) aneinandergrenzen.
  4. Versorgungsverfahren nach einem der Ansprüche 1 bis 3, wobei der radial in der Ebene der Anoden (2) erzeugte Plasmastrahl (2p) gleichgerichtet und axial durch ein Magnetfeld (B) beschleunigt wird.
  5. Satelliten-Antriebsmodul (100), das dazu bestimmt ist, das Verfahren nach einem der vorhergehenden Ansprüche anzuwenden, dadurch gekennzeichnet, dass es ein global ringförmiges Gestell (20), das eine Mittelachse (X'X) hat und in dem eine metallische Ringkathode (2) angeordnet ist, die durch Außengewinde/Innengewinde (2L) in Schraubenverbindung (2T) mit diesem Gestell (20) geführt wird, sowie eine mittlere und zum Gestell (20) koaxiale Hohlwelle (2A) aufweist, wobei die Mittelwelle (2A) eine Querwand (21A) aufweist, an der ein kreisförmiger Träger (10) befestigt ist, der aus einem Isoliermaterial besteht und mit Metallanoden (1) ausgestattet ist, die gleichmäßig am Umfang verteilt sind, dass dieses Gestell (20) ebenfalls Energiespeicher-Kondensatoren (4) aufweist, die jede Anode (1) mit der Kathode (2) verbinden, um die Energie zu liefern, um Zyklen von Elektronenentladungen nach der Bildung eines Vorplasmas (2p) zu erzeugen, und dass ein Drehantriebsmechanismus (7 bis 9) mit der Kathode (2) verbunden ist, um ihr eine schrittweise Verschiebebewegung in Verbindung mit der Schraubenführung (2T) zu verleihen, die zwischen dem Gestell (20) und der Kathode (2) gebildet ist.
  6. Antriebsmodul nach dem vorhergehenden Anspruch, wobei die Mittelwelle (2A) Lichtleitfasern (6) beinhaltet, die je mit optischen Endeinrichtungen (5) gekoppelt sind, die in direkter Nähe der Anoden (1) positioniert sind und in Richtung der Kathode (2) eine ionisierende elektromagnetische Strahlung emittieren können, die von mindestens einer elektromagnetischen Strahlungsquelle kommt, die die Initialisierung der Bildung eines Plasmastrahls (1p) ausgehend von einer Bogenerzeugung begünstigt.
  7. Antriebsmodul nach einem der Ansprüche 5 oder 6, wobei die ionisierende elektromagnetische Strahlungsquelle aus einem Laser besteht.
  8. Antriebsmodul nach einem der Ansprüche 5 bis 7, wobei eine ringförmige elektromagnetische Spule (3) ebenfalls an der Außenseite (20e) des Gestells (20) eingebaut ist, um ein induziertes Magnetfeld (B) zu erzeugen, um das von den aufeinanderfolgenden Elektronenentladungen gebildete Plasma (3p) axial gleichzurichten.
  9. Antriebsmodul nach einem der Ansprüche 5 bis 8, wobei der Drehantriebsmechanismus aus einem Tragring (7) der Kathode (2) in Verbindung mit einem elektrischen Schrittmotor (9) über eine Schnecke (8) besteht.
EP16778690.4A 2015-09-18 2016-09-14 Verfahren zur treibmittelversorgung des antriebs eines satelliten und nach diesem verfahren angetriebenes satellitenantriebsmodul Active EP3350441B1 (de)

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FR1558809A FR3041390B1 (fr) 2015-09-18 2015-09-18 Procede d'alimentation pour la propulsion de satellite et module de propulsion de satellite alimente selon ce procede
PCT/EP2016/071617 WO2017046115A1 (fr) 2015-09-18 2016-09-14 Procédé d'alimentation pour la propulsion de satellite et module de propulsion de satellite alimenté selon ce procédé

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CN111916326A (zh) * 2020-06-09 2020-11-10 哈尔滨工业大学 一种具有防护功能的离子源的导磁套筒结构

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US6818853B1 (en) 2003-05-30 2004-11-16 Alameda Applied Sciences Corp. Vacuum arc plasma thrusters with inductive energy storage driver
US8875485B2 (en) * 2010-04-06 2014-11-04 The George Washington University Micro-cathode thruster and a method of increasing thrust output for a micro-cathode thruster

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EP3350441A1 (de) 2018-07-25
WO2017046115A1 (fr) 2017-03-23
FR3041390A1 (fr) 2017-03-24

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