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EP3872441A1 - Method and facility for extracting propellant from a propeller - Google Patents

Method and facility for extracting propellant from a propeller Download PDF

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Publication number
EP3872441A1
EP3872441A1 EP21159491.6A EP21159491A EP3872441A1 EP 3872441 A1 EP3872441 A1 EP 3872441A1 EP 21159491 A EP21159491 A EP 21159491A EP 3872441 A1 EP3872441 A1 EP 3872441A1
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EP
European Patent Office
Prior art keywords
propellant
nozzle
jet
main axis
support pole
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP21159491.6A
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German (de)
French (fr)
Other versions
EP3872441B1 (en
EP3872441C0 (en
Inventor
Gregory TATE
Laurent CESARO
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
ArianeGroup SAS
Original Assignee
ArianeGroup SAS
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Publication date
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Application granted granted Critical
Publication of EP3872441B1 publication Critical patent/EP3872441B1/en
Publication of EP3872441C0 publication Critical patent/EP3872441C0/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B33/00—Manufacture of ammunition; Dismantling of ammunition; Apparatus therefor
    • F42B33/06—Dismantling fuzes, cartridges, projectiles, missiles, rockets or bombs
    • F42B33/062—Dismantling fuzes, cartridges, projectiles, missiles, rockets or bombs by high-pressure water jet means

Definitions

  • the invention proposes a method and an installation intended for dismantling a thruster, in order to extract the propellant from the loaded thruster body.
  • the propellant thus extracted from the structure of the propellant is then reprocessed, in order to extract the components of the propellant, in particular ammonium perchlorate.
  • the extraction of the propellant is carried out by cutting the propellant using jets of pressurized liquid.
  • the power of the jets is sometimes too great and when the intersection of jets is located near the wall, these jets can impact the structure.
  • the material of the structure is based on stainless steel, which makes it resistant to the impact of the jets.
  • this material can disintegrate under the effect of the liquid jet.
  • the propellant thus polluted cannot then be reprocessed; it must therefore be eliminated by combustion, together with the structural pieces, thus producing pollution.
  • the object of the invention is to provide a method and an installation for extracting propellant which make it possible to separate the whole of the propellant from the structure of the propellant body, without harming the integrity of the structure.
  • the invention relates to a method of extracting propellant from a charged propellant body, said charged propellant body comprising an elongated structure with a main axis A which is an element of revolution about said main axis A, and within it. which said structure, the propellant is located, the extraction process consisting in using at least one nozzle producing a jet of liquid which erodes the propellant, characterized in that the jet of liquid is a flat jet and in that the nozzle travels a helical path coaxial with the main axis A during the extraction of the propellant.
  • the method is implemented in several phases each consisting in eroding the propellant by the flat jet, to a predefined thickness.
  • an adjustment of the position of the nozzle is carried out between two successive phases, in order to bring the nozzle closer to the propellant according to a predefined pitch.
  • the path traveled by the nozzle has a pitch substantially equal to an axial extent along which the propellant is eroded by the flat jet.
  • the invention also relates to an installation for carrying out a method for extracting propellant from a charged propellant body according to any one of the preceding claims, which comprises a support pole which is supplied with liquid under pressure and which is movable in translation and rotation along its main axis which coincides with a main axis A of the loaded propellant body, at least one nozzle for projecting a jet of liquid which is carried by the support pole, supply means of said at least one pressurized liquid nozzle via the support pole, characterized in that said at least one nozzle is designed to project the liquid in a flat jet.
  • said flat jet is delimited by two straight lines which intersect at the level of the nozzle and which define an opening angle of the predefined flat jet.
  • the value of said angle of opening of the flat jet is degrees.
  • said at least one nozzle is carried by a support arm making it possible to carry out an adjustment of the position and the orientation of the nozzle relative to the support pole, and which provides fluid communication between the nozzle and the nozzle. support pole.
  • the installation comprises a plurality of interchangeable support arms which are able to be interchanged between two phases of the process, in order to modify the position of said nozzle with respect to the support pole.
  • each support arm is able to pivot relative to the support pole about an axis orthogonal to the main axis A during a phase of the method.
  • the loaded thruster body 12 comprises a structure 14 of tubular main shape of revolution and having a main axis A.
  • This structure is open at one of its axial ends 16, the other axial end can be open or closed.
  • Propellant 18 is present inside the structure 14 and is fixed to its internal face.
  • the installation 10 operates by the use of one or more jets 28 of pressurized liquid, causing abrasion of the propellant 18.
  • the pressurized liquid is water.
  • water to form the jets. It will be understood that other liquids can be considered and that the use of such another liquid will be deduced from the description by analogy.
  • the installation 10 comprises a support pole 22 which extends coaxially with the main axis A of the structure 14 and which is movable in rotation around this main axis A and in translation along the main axis A.
  • the support pole 22 carries at least one nozzle 24 for spraying pressurized water in the direction of the propellant 18 in the form of a jet 28.
  • the support pole 22 carries two projection nozzles 24 which are distributed over an axial end 22A of the support pole 22.
  • the installation 10 is not limited to those embodiments comprising two projection nozzles and that the installation 10 may include a single projection nozzle 24 or several nozzles 24 strategically distributed on the support pole. 22.
  • the installation 10 also comprises a support arm 26 for the nozzle 24, which connects the nozzle 24 to the support pole 22.
  • the support arm 26 makes it possible to achieve precise positioning of the nozzle 24 relative to the structure 14 and to the propellant 18 to be extracted, that is to say in particular the position relative to the main axis A and the orientation nozzle 24.
  • the pressurized water nozzle 24 is supplied by means of the support pole 22 and the support arm 26.
  • the support pole 22 thus comprises internal conduits for circulating pressurized water (not shown) which open into orifices formed in the external wall of the support pole 22.
  • the support arm 26 consists of a tubular element, one end of which is connected to the nozzle 24 which it carries and the other end of the support arm is in fluid communication with the internal conduits of the support pole 22, via an orifice of the support pole 22, at which the support arm 26 is mounted on the support pole 22.
  • the nozzle 24 is designed so that the water jet 28 is flared and flat.
  • the water jet 28 leaving the nozzle 24 is thus a flat jet.
  • the water jet 28 is of triangular main shape, and it is delimited by two straight lines 30 which intersect at a point located in the nozzle 24 and these two straight lines define an angle 32, which is the angle of opening of the water jet 28.
  • the value of the opening angle 32 is 10 degrees. It will be understood that the invention is not limited to this single value and that it can also relate to a nozzle 24 producing a water jet 28 for which the value of the opening angle 32 is between 10 and 40 degrees.
  • the water jet 28 extends in a plane defined by these two straight lines 30.
  • the support pole 22 rotates around the main axis A and translates along this main axis A.
  • the nozzle 24 thus performs a helical path coaxial with the main axis A.
  • the support arm 26 of the nozzle 24 is designed so that the plane in which the water jet 28 exiting the nozzle extends, is perpendicular to a direction tangential to this helical path.
  • the median axis B of the water jet 28 is inclined relative to a radial direction relative to the main axis A, in the direction of the direction of advance of the support pole 22 during the extraction of the propellant 18 .
  • the invention is not limited to this radial orientation of the median axis B and that the median axis B can be inclined differently, in particular, the median axis B can be radial with respect to the axis principal A.
  • a method of extracting the propellant 18 from the charged propellant body 12 using such a plant 10 is to use a nozzle 24 producing a flat water jet 28 and to cause it to travel a helical path coaxial with the main axis of the propellant body. thruster loaded 12.
  • the flat water jet 28 erodes part of the propellant 18, over a given thickness 34 and over the entire axial length of the loaded propellant body 12.
  • the helical path of the nozzle 24 has an axial pitch which is defined as a function of the axial extent 36 that propellant is eroded by the water jet 28.
  • the value of the axial pitch is equal to this axial extent 36.
  • the value of the axial pitch is less than this axial extent 36, in order to have an overlap of the passes of the water jet 28 on the propellant 18.
  • the value of the axial pitch may be less than this axial extent 36.
  • the method consists in successively implementing several phases during each of which a part of the propellant 18 is eroded along said thickness 34, the number of these phases is defined according to the total thickness of the propellant 18.
  • the nozzle 24 is positioned as close as possible to the propellant 18 to be extracted, in order to ensure optimum efficiency of the water jet 28. This positioning is carried out by choosing a support arm. 26 with the correct dimensions.
  • the pressurized water is conducted to the nozzle 24 to form the flat water jet 28.
  • the support pole is set in motion, that is to say in rotation around the main axis A and in translation along the main axis A, as represented by the arrows 38 at the figure 2 , to give the nozzle 24 and the flat water jet 28 a helical path, over the entire axial length of the loaded propellant body 12.
  • part of the propellant 18 was trimmed according to the erosion thickness 34 defined above.
  • An adjustment of the position of the nozzle 24 is carried out between two successive phases, so that the nozzle 24 is again at the best possible distance from the propellant 18 to be extracted for the phase which will be implemented.
  • This adjustment of the position consists in replacing the support arm 26 used during one phase with another support arm suitable for positioning the nozzle 24 for the following phase.
  • the support arm 26 used in the later phase has a length greater than that of the support arm 26 used in the earlier phase.
  • the support arm 26 is mounted articulated relative to the axial end 22A of the support pole 22 about a transverse axis perpendicular to the main axis A.
  • the support arm 26 is able to pivot about this transverse axis between two extreme positions shown in figure 4 by dotted lines.
  • a first extreme position 26A located in the extension of the axial end 22A of the support pole 22 is inclined 20 degrees below the main axis A
  • the second extreme position 26B is inclined 155 degrees above the axis main A, for a total angular travel of 175 degrees.
  • the arm 26 oscillates relative to the axial end 22A of the support pole 22 during each extraction phase, in addition to the rotation of the support pole 22 around the main axis A and the translation. axial direction of the support pole 22.
  • the thickness of propellant 18 present on the structure 14 is less than the thickness 34 that the flat water jet 28 can erode. This allows all of the remaining propellant to be extracted.
  • the flat water jet 28 reaches the wall of the structure 14, it cannot damage it, as has been said previously.
  • the structure 14 can then, depending on the case, be reused or reprocessed.

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • General Engineering & Computer Science (AREA)
  • Perforating, Stamping-Out Or Severing By Means Other Than Cutting (AREA)
  • Nozzles (AREA)

Abstract

L'invention concerne un procédé d'extraction de propergol (18) depuis un corps de propulseur chargé (12), ledit corps de propulseur chargé (12) comprenant une structure (14) allongée d'axe principal A qui est un élément de révolution autour dudit axe principal (A), et à l'intérieur de laquelle dite structure, le propergol (18) est situé, le procédé d'extraction consistant à utiliser au moins une buse (24) produisant un jet (28) de liquide qui érode le propergol (18),
caractérisé en ce que le jet (28) de liquide est un jet plat et en ce que la buse (24) parcourt une trajectoire hélicoïdale coaxiale à l'axe principal A lors de l'extraction du propergol (18).

Figure imgaf001
The invention relates to a method of extracting propellant (18) from a charged propellant body (12), said charged propellant body (12) comprising an elongated structure (14) with a main axis A which is an element of revolution. around said main axis (A), and within which said structure, the propellant (18) is located, the extraction process consisting in using at least one nozzle (24) producing a jet (28) of liquid which erodes the propellant (18),
characterized in that the jet (28) of liquid is a flat jet and in that the nozzle (24) follows a helical path coaxial with the main axis A during the extraction of the propellant (18).
Figure imgaf001

Description

DOMAINE TECHNIQUETECHNICAL AREA

L'invention propose un procédé et une installation destinés au démantèlement d'un propulseur, afin d'extraire le propergol du corps de propulseur chargé.The invention proposes a method and an installation intended for dismantling a thruster, in order to extract the propellant from the loaded thruster body.

ÉTAT DE LA TECHNIQUE ANTÉRIEURESTATE OF THE PRIOR ART

Dans le cadre du retraitement de propulseurs, que ce soit des propulseurs militaire ou spatiaux, un recyclage des différents composants d'un propulseur existe, en alternative à leur combustion.As part of the reprocessing of thrusters, whether military or space thrusters, recycling of the various components of a thruster exists, as an alternative to their combustion.

Pour cela, notamment, il faut séparer le propergol de la structure du propulseur.For this, in particular, it is necessary to separate the propellant from the structure of the propellant.

Le propergol ainsi extrait de la structure du propulseur est ensuite retraité, pour extraire les composants du propergol, notamment le perchlorate d'ammonium.The propellant thus extracted from the structure of the propellant is then reprocessed, in order to extract the components of the propellant, in particular ammonium perchlorate.

Selon un mode de réalisation connu, l'extraction du propergol est réalisée par découpe du propergol en utilisant des jets de liquide sous pression.According to a known embodiment, the extraction of the propellant is carried out by cutting the propellant using jets of pressurized liquid.

La trajectoire de ces jets ronds a pour conséquence qu'une partie du propergol reste attachée à la structure sous la forme de dents de propergol.The trajectory of these round jets results in part of the propellant remaining attached to the structure in the form of propellant teeth.

Aussi, la puissance des jets est parfois trop importante et lorsque l'intersection de jets est située à proximité de la paroi, ces jets peuvent impacter la structure.Also, the power of the jets is sometimes too great and when the intersection of jets is located near the wall, these jets can impact the structure.

Selon un mode de réalisation, le matériau de la structure est à base d'acier inoxydable, ce qui la rend résistante à l'impact des jets.According to one embodiment, the material of the structure is based on stainless steel, which makes it resistant to the impact of the jets.

Par contre, lorsque la structure est réalisée en matériau composite, ce matériau peut se désagréger sous l'effet du jet de liquide.On the other hand, when the structure is made of a composite material, this material can disintegrate under the effect of the liquid jet.

Il en résulte que l'intégrité mécanique de la structure est remise en cause, il faut alors la réparer ou bien la mettre au rebus. Aussi, la portion de la structure qui est désagrégée se mélange au propergol extrait.As a result, the mechanical integrity of the structure is called into question, it must then be repaired or else scrapped. Also, the portion of the structure which is broken up mixes with the extracted propellant.

Le propergol ainsi pollué ne peut alors pas être retraité, il doit donc être éliminé par combustion, avec les morceaux de structure, produisant ainsi de la pollution.The propellant thus polluted cannot then be reprocessed; it must therefore be eliminated by combustion, together with the structural pieces, thus producing pollution.

L'invention a pour but de proposer un procédé et une installation d'extraction de propergol qui permettent de désolidariser l'ensemble du propergol d'avec la structure du corps de propulseur, sans nuire à l'intégrité de la structure.The object of the invention is to provide a method and an installation for extracting propellant which make it possible to separate the whole of the propellant from the structure of the propellant body, without harming the integrity of the structure.

EXPOSÉ DE L'INVENTIONDISCLOSURE OF THE INVENTION

L'invention concerne un procédé d'extraction de propergol depuis un corps de propulseur chargé, ledit corps de propulseur chargé comprenant une structure allongée d'axe principal A qui est un élément de révolution autour dudit axe principal A, et à l'intérieur de laquelle dite structure, le propergol est situé, le procédé d'extraction consistant à utiliser au moins une buse produisant un jet de liquide qui érode le propergol, caractérisé en ce que le jet de liquide est un jet plat et en ce que la buse parcourt une trajectoire hélicoïdale coaxiale à l'axe principal A lors de l'extraction du propergol.The invention relates to a method of extracting propellant from a charged propellant body, said charged propellant body comprising an elongated structure with a main axis A which is an element of revolution about said main axis A, and within it. which said structure, the propellant is located, the extraction process consisting in using at least one nozzle producing a jet of liquid which erodes the propellant, characterized in that the jet of liquid is a flat jet and in that the nozzle travels a helical path coaxial with the main axis A during the extraction of the propellant.

L'utilisation d'un jet plat permet de répartir la puissance du liquide sous pression, ce qui limite les risques d'endommager la structure du corps de propulseur. Aussi, le fait que le jet soit évasé permet d'atteindre sensiblement toute la surface interne de la structure, afin de retirer tout le propergol.The use of a flat jet makes it possible to distribute the power of the pressurized liquid, which limits the risks of damaging the structure of the thruster body. Also, the fact that the jet is flared makes it possible to reach substantially the entire internal surface of the structure, in order to remove all the propellant.

De préférence, le procédé est mis en œuvre en plusieurs phases consistant chacune à éroder le propergol par le jet plat, sur une épaisseur prédéfinie.Preferably, the method is implemented in several phases each consisting in eroding the propellant by the flat jet, to a predefined thickness.

De préférence, un ajustement de la position de la buse est effectué entre deux phases successives, pour rapprocher la buse du propergol selon un pas prédéfini.Preferably, an adjustment of the position of the nozzle is carried out between two successive phases, in order to bring the nozzle closer to the propellant according to a predefined pitch.

De préférence, la trajectoire parcourue par la buse possède un pas sensiblement égal à une étendue axiale selon laquelle du propergol est érodée par le jet plat.Preferably, the path traveled by the nozzle has a pitch substantially equal to an axial extent along which the propellant is eroded by the flat jet.

L'invention concerne aussi une installation de mise en œuvre d'un procédé d'extraction de propergol depuis un corps de propulseur chargé selon l'une quelconque des revendications précédentes, qui comporte une perche de support qui est alimentée en liquide sous pression et qui est mobile en translation et rotation selon son axe principal qui est confondu avec un axe principal A du corps de propulseur chargé, au moins une buse de projection d'un jet de liquide qui est portée par la perche de support, des moyens d'alimentation de ladite au moins une buse en liquide sous pression par l'intermédiaire de la perche de support, caractérisée en ce que ladite au moins une buse est conçue pour projeter le liquide en un jet plat.The invention also relates to an installation for carrying out a method for extracting propellant from a charged propellant body according to any one of the preceding claims, which comprises a support pole which is supplied with liquid under pressure and which is movable in translation and rotation along its main axis which coincides with a main axis A of the loaded propellant body, at least one nozzle for projecting a jet of liquid which is carried by the support pole, supply means of said at least one pressurized liquid nozzle via the support pole, characterized in that said at least one nozzle is designed to project the liquid in a flat jet.

De préférence, ledit jet plat est délimité par deux droites qui sont sécantes au niveau de la buse et qui délimitent un angle d'ouverture du jet plat prédéfini.Preferably, said flat jet is delimited by two straight lines which intersect at the level of the nozzle and which define an opening angle of the predefined flat jet.

De préférence, la valeur dudit angle d'ouverture du jet plat est de degrés.Preferably, the value of said angle of opening of the flat jet is degrees.

De préférence, ladite au moins une buse est portée par un bras de support permettant de réaliser un ajustement de la position et de l'orientation de la buse par rapport à la perche de support, et qui réalise une communication fluidique entre la buse et la perche de support.Preferably, said at least one nozzle is carried by a support arm making it possible to carry out an adjustment of the position and the orientation of the nozzle relative to the support pole, and which provides fluid communication between the nozzle and the nozzle. support pole.

De préférence, l'installation comporte une pluralité de bras de support interchangeables qui sont aptes à être intervertis entre deux phases du procédé, pour modifier la position de ladite buse par rapport à la perche de support.Preferably, the installation comprises a plurality of interchangeable support arms which are able to be interchanged between two phases of the process, in order to modify the position of said nozzle with respect to the support pole.

De préférence, chaque bras de support est apte à pivoter par rapport à la perche de support autour d'un axe orthogonal à l'axe principal A au cours d'une phase du procédé.Preferably, each support arm is able to pivot relative to the support pole about an axis orthogonal to the main axis A during a phase of the method.

BRÈVE DESCRIPTION DES DESSINSBRIEF DESCRIPTION OF THE DRAWINGS

  • La figure 1 est une représentation schématique d'une installation d'extraction de propergol selon l'inventionThe figure 1 is a schematic representation of a propellant extraction installation according to the invention
  • La figure 2 est une représentation schématique montrant une phase de chariotage pour l'extraction du propergol.The figure 2 is a schematic representation showing a turning phase for the extraction of the propellant.
  • La figure 3 est une représentation schématique d'une perche de support qui porte plusieurs buses de projection de liquide.The figure 3 is a schematic representation of a support pole which carries several liquid projection nozzles.
  • La figure 4 est une représentation schématique d'une perche de support montrant les déplacements possibles d'un bras de support.The figure 4 is a schematic representation of a support pole showing the possible displacements of a support arm.
EXPOSÉ DÉTAILLÉ DE MODES DE RÉALISATION PARTICULIERSDETAILED PRESENTATION OF PARTICULAR EMBODIMENTS

On a représenté à la figure 1 une installation 10 pour l'extraction du propergol contenu dans un corps de propulseur chargé 12.We have represented at the figure 1 an installation 10 for extracting the propellant contained in a loaded propellant body 12.

Le corps de propulseur chargé 12 comporte une structure 14 de forme principale tubulaire de révolution et possédant un axe principal A.The loaded thruster body 12 comprises a structure 14 of tubular main shape of revolution and having a main axis A.

Cette structure est ouverte à une de ses extrémités axiales 16, l'autre extrémité axiale peut être ouverte ou fermée.This structure is open at one of its axial ends 16, the other axial end can be open or closed.

Du propergol 18 est présent à l'intérieur de la structure 14 et est fixée à sa face interne.Propellant 18 is present inside the structure 14 and is fixed to its internal face.

L'installation 10 fonctionne par l'utilisation d'un ou plusieurs jets 28 de liquide sous pression, réalisant une abrasion du propergol 18.The installation 10 operates by the use of one or more jets 28 of pressurized liquid, causing abrasion of the propellant 18.

De préférence, le liquide sous pression est de l'eau. Ainsi, dans la description qui va suivre on fera référence à de l'eau pour former les jets. Il sera compris que d'autres liquides peuvent être envisagés et que l'utilisation d'un tel autre liquide se déduira de la description par analogie.Preferably, the pressurized liquid is water. Thus, in the description which follows, reference will be made to water to form the jets. It will be understood that other liquids can be considered and that the use of such another liquid will be deduced from the description by analogy.

L'installation 10 comporte une perche de support 22 qui s'étend coaxialement à l'axe principal A de la structure 14 et qui est mobile en rotation autour de cet axe principal A et en translation le long de l'axe principal A.The installation 10 comprises a support pole 22 which extends coaxially with the main axis A of the structure 14 and which is movable in rotation around this main axis A and in translation along the main axis A.

La perche de support 22 porte au moins une buse 24 de projection d'eau sous pression en direction du propergol 18 sous la forme d'un jet 28.The support pole 22 carries at least one nozzle 24 for spraying pressurized water in the direction of the propellant 18 in the form of a jet 28.

Selon le mode de réalisation représenté à la figure 1, la perche de support 22 porte deux buses 24 de projection qui sont réparties sur une extrémité axiale 22A de la perche de support 22.According to the embodiment shown in figure 1 , the support pole 22 carries two projection nozzles 24 which are distributed over an axial end 22A of the support pole 22.

Il sera compris que l'installation 10 n'est pas limitée à ces modes de réalisation comportant deux buses de projection et que l'installation 10 peut comporter une seule buse 24 de projection ou plusieurs buses 24 réparties de façon stratégique sur la perche de support 22.It will be understood that the installation 10 is not limited to those embodiments comprising two projection nozzles and that the installation 10 may include a single projection nozzle 24 or several nozzles 24 strategically distributed on the support pole. 22.

Dans la description qui va suivre, on fera référence à une seule buse 24 de projection. Il sera compris que la description pour un mode de réalisation comportant plusieurs buses 24 de projection pourra se déduire par similitude.In the description which follows, reference will be made to a single projection nozzle 24. It will be understood that the description for an embodiment comprising several spray nozzles 24 can be deduced by similarity.

L'installation 10 comporte aussi un bras de support 26 de la buse 24, qui relie la buse 24 à la perche de support 22.The installation 10 also comprises a support arm 26 for the nozzle 24, which connects the nozzle 24 to the support pole 22.

Le bras de support 26 permet de réaliser un positionnement précis de la buse 24 par rapport à la structure 14 et au propergol 18 à extraire, c'est-à-dire notamment la position par rapport à l'axe principal A et l'orientation de la buse 24.The support arm 26 makes it possible to achieve precise positioning of the nozzle 24 relative to the structure 14 and to the propellant 18 to be extracted, that is to say in particular the position relative to the main axis A and the orientation nozzle 24.

L'alimentation de la buse 24 en eau sous pression est réalisée par l'intermédiaire de la perche de support 22 et du bras de support 26.The pressurized water nozzle 24 is supplied by means of the support pole 22 and the support arm 26.

La perche de support 22 comporte ainsi des conduits internes de circulation de l'eau sous pression (non représentés) qui débouchent dans des orifices formés dans la paroi externe de la perche de support 22.The support pole 22 thus comprises internal conduits for circulating pressurized water (not shown) which open into orifices formed in the external wall of the support pole 22.

Le bras de support 26 consiste en un élément tubulaire dont une extrémité est raccordée à la buse 24 qu'il porte et l'autre extrémité du bras de support est en communication fluidique avec les conduits internes de la perche de support 22, par un orifice de la perche de support 22, au niveau duquel le bras de support 26 est monté sur la perche de support 22.The support arm 26 consists of a tubular element, one end of which is connected to the nozzle 24 which it carries and the other end of the support arm is in fluid communication with the internal conduits of the support pole 22, via an orifice of the support pole 22, at which the support arm 26 is mounted on the support pole 22.

La buse 24 est conçue pour que le jet d'eau 28 soit évasé et plan. Le jet d'eau 28 sortant de la buse 24 est ainsi un jet plat.The nozzle 24 is designed so that the water jet 28 is flared and flat. The water jet 28 leaving the nozzle 24 is thus a flat jet.

Plus précisément, le jet d'eau 28 est de forme principale triangulaire, et il est délimité par deux droites 30 qui sont sécantes en un point localisé dans la buse 24 et ces deux droites délimitent un angle 32, qui est l'angle d'ouverture du jet d'eau 28.More precisely, the water jet 28 is of triangular main shape, and it is delimited by two straight lines 30 which intersect at a point located in the nozzle 24 and these two straight lines define an angle 32, which is the angle of opening of the water jet 28.

De préférence, la valeur de l'angle d'ouverture 32 est de 10 degrés. Il sera compris que l'invention n'est pas limitée à cette valeur unique et qu'elle peut aussi concerner une buse 24 produisant un jet d'eau 28 pour lequel la valeur de l'angle d'ouverture 32 est comprise entre 10 et 40 degrés.Preferably, the value of the opening angle 32 is 10 degrees. It will be understood that the invention is not limited to this single value and that it can also relate to a nozzle 24 producing a water jet 28 for which the value of the opening angle 32 is between 10 and 40 degrees.

Le jet d'eau 28 s'étend dans un plan défini par ces deux droites 30.The water jet 28 extends in a plane defined by these two straight lines 30.

Lors de l'extraction du propergol 18, la perche de support 22 tourne autour de l'axe principal A et translate le long de cet axe principal A. La buse 24 effectue ainsi une trajectoire hélicoïdale coaxiale à l'axe principal A.During the extraction of the propellant 18, the support pole 22 rotates around the main axis A and translates along this main axis A. The nozzle 24 thus performs a helical path coaxial with the main axis A.

De préférence, le bras de support 26 de la buse 24 est conçu pour que le plan dans lequel le jet d'eau 28 sortant de la buse s'étend, soit perpendiculaire à une direction tangentielle à cette trajectoire hélicoïdale.Preferably, the support arm 26 of the nozzle 24 is designed so that the plane in which the water jet 28 exiting the nozzle extends, is perpendicular to a direction tangential to this helical path.

Aussi, selon le mode de réalisation représenté à la figure 2, l'axe médian B du jet d'eau 28 est incliné par rapport à une direction radiale par rapport à l'axe principal A, en direction du sens d'avance de la perche de support 22 lors de l'extraction du propergol 18.Also, according to the embodiment shown in figure 2 , the median axis B of the water jet 28 is inclined relative to a radial direction relative to the main axis A, in the direction of the direction of advance of the support pole 22 during the extraction of the propellant 18 .

Il sera compris que l'invention n'est pas limitée à cette orientation radiale de l'axe médian B et que l'axe médian B peut être incliné différemment, notamment, l'axe médian B peut être radial par rapport à l'axe principal A.It will be understood that the invention is not limited to this radial orientation of the median axis B and that the median axis B can be inclined differently, in particular, the median axis B can be radial with respect to the axis principal A.

C'est notamment le cas lorsque l'installation comporte plusieurs buses 24, qui sont portées par plusieurs bras de support 26, voire lorsque plusieurs buses 24 sont portées par un même bras de support 26.This is particularly the case when the installation comprises several nozzles 24, which are carried by several support arms 26, or even when several nozzles 24 are carried by the same support arm 26.

Un procédé d'extraction du propergol 18 du corps de propulseur chargé 12 utilisant une telle installation 10 consiste à utiliser une buse 24 produisant un jet d'eau 28 plat et à lui faire parcourir une trajectoire hélicoïdale coaxiale à l'axe principal du corps de propulseur chargé 12.A method of extracting the propellant 18 from the charged propellant body 12 using such a plant 10 is to use a nozzle 24 producing a flat water jet 28 and to cause it to travel a helical path coaxial with the main axis of the propellant body. thruster loaded 12.

En effectuant cette trajectoire, le jet d'eau 28 plat érode une partie du propergol 18, sur une épaisseur 34 donnée et sur toute la longueur axiale du corps de propulseur chargé 12.By carrying out this trajectory, the flat water jet 28 erodes part of the propellant 18, over a given thickness 34 and over the entire axial length of the loaded propellant body 12.

La trajectoire hélicoïdale de la buse 24 possède un pas axial qui est défini en fonction de l'étendue axiale 36 selon laquelle du propergol est érodée par le jet d'eau 28.The helical path of the nozzle 24 has an axial pitch which is defined as a function of the axial extent 36 that propellant is eroded by the water jet 28.

De préférence, lorsque l'installation comporte une buse 24, la valeur du pas axial est égale à cette étendue axiale 36.Preferably, when the installation comprises a nozzle 24, the value of the axial pitch is equal to this axial extent 36.

Selon une variante, la valeur du pas axial est inférieure à cette étendue axiale 36, pour avoir un recouvrement des passes du jet d'eau 28 sur le propergol 18.According to one variant, the value of the axial pitch is less than this axial extent 36, in order to have an overlap of the passes of the water jet 28 on the propellant 18.

Lorsque l'installation comporte plusieurs buses 24, la valeur du pas axial peut être inférieure à cette étendue axiale 36.When the installation comprises several nozzles 24, the value of the axial pitch may be less than this axial extent 36.

Le procédé consiste à mettre en œuvre successivement plusieurs phases au cours de chacune desquelles une partie du propergol 18 est érodé selon ladite épaisseur 34, le nombre de ces phases est défini selon l'épaisseur totale de propergol 18.The method consists in successively implementing several phases during each of which a part of the propellant 18 is eroded along said thickness 34, the number of these phases is defined according to the total thickness of the propellant 18.

Comme on l'a dit précédemment, puisque le jet d'eau 28 est évasé et plat, lorsqu'il impacte la structure 14, sa puissance permet de ne pas endommager celle-ci, même une structure 14 réalisée en matériau composite.As stated previously, since the water jet 28 is flared and flat, when it impacts the structure 14, its power makes it possible not to damage the latter, even a structure 14 made of a composite material.

Au début d'une phase, la buse 24 est positionnée au plus près du propergol 18 à extraire, afin d'assurer une efficacité optimale du jet d'eau 28. Cette mise en place est réalisée par le choix d'un bras de support 26 présentant les dimensions adaptées.At the start of a phase, the nozzle 24 is positioned as close as possible to the propellant 18 to be extracted, in order to ensure optimum efficiency of the water jet 28. This positioning is carried out by choosing a support arm. 26 with the correct dimensions.

Pendant chaque phase, l'eau sous pression est conduite jusqu'à la buse 24 pour former le jet d'eau 28 plat.During each phase, the pressurized water is conducted to the nozzle 24 to form the flat water jet 28.

Dans le même temps, la perche de support est mise en mouvement, c'est-à-dire en rotation autour de l'axe principal A et en translation le long de l'axe principal A, comme on l'a représenté par les flèches 38 à la figure 2, pour conférer à la buse 24 et au jet d'eau 28 plat une trajectoire hélicoïdale, sur toute la longueur axiale du corps de propulseur chargé 12.At the same time, the support pole is set in motion, that is to say in rotation around the main axis A and in translation along the main axis A, as represented by the arrows 38 at the figure 2 , to give the nozzle 24 and the flat water jet 28 a helical path, over the entire axial length of the loaded propellant body 12.

A l'issue d'une phase, une partie du propergol 18 a été rognée selon l'épaisseur 34 d'érosion définie précédemment.At the end of a phase, part of the propellant 18 was trimmed according to the erosion thickness 34 defined above.

Un ajustement de la position de la buse 24 est effectué entre deux phases successives, pour que la buse 24 soit de nouveau à la meilleure distance possible du propergol 18 à extraire pour la phase qui va être mise en œuvre.An adjustment of the position of the nozzle 24 is carried out between two successive phases, so that the nozzle 24 is again at the best possible distance from the propellant 18 to be extracted for the phase which will be implemented.

Cet ajustement de la position consiste à remplacer le bras de support 26 utilisé au cours d'une phase par un autre bras de support adapté à positionner la buse 24 pour la phase suivante.This adjustment of the position consists in replacing the support arm 26 used during one phase with another support arm suitable for positioning the nozzle 24 for the following phase.

Par exemple, le bras de support 26 utilisé dans la phase ultérieure a une longueur supérieure de celle du bras de support 26 utilisé dans la phase antérieure.For example, the support arm 26 used in the later phase has a length greater than that of the support arm 26 used in the earlier phase.

Selon une variante de réalisation basée sur la figure 4, le bras de support 26 est monté articulé par rapport à l'extrémité axiale 22A de la perche de support 22 autour d'un axe transversal perpendiculaire à l'axe principal A.According to an alternative embodiment based on the figure 4 , the support arm 26 is mounted articulated relative to the axial end 22A of the support pole 22 about a transverse axis perpendicular to the main axis A.

Le bras de support 26 est apte à pivoter autour de cet axe transversal entre deux positions extrêmes représentées à la figure 4 par des traits en pointillés.The support arm 26 is able to pivot about this transverse axis between two extreme positions shown in figure 4 by dotted lines.

Une première position extrême 26A située dans le prolongement de l'extrémité axiale 22A de la perche de support 22 est inclinée de 20 degrés sous l'axe principal A, la deuxième position extrême 26B est inclinée de 155 degrés au-dessus de l'axe principal A, soit un débattement angulaire total de 175 degrés.A first extreme position 26A located in the extension of the axial end 22A of the support pole 22 is inclined 20 degrees below the main axis A, the second extreme position 26B is inclined 155 degrees above the axis main A, for a total angular travel of 175 degrees.

De préférence, le bras 26 oscille par rapport à l'extrémité axiale 22A de la perche de support 22 pendant chaque phase d'extraction, en plus de la rotation de la perche de support 22 autour de l'axe principal A et de la translation axiale de la perche de support 22.Preferably, the arm 26 oscillates relative to the axial end 22A of the support pole 22 during each extraction phase, in addition to the rotation of the support pole 22 around the main axis A and the translation. axial direction of the support pole 22.

De préférence, pour la dernière phase du procédé, l'épaisseur de propergol 18 présente sur la structure 14 est inférieure à l'épaisseur 34 que le jet d'eau 28 plat peut éroder. Cela permet d'extraire la totalité du propergol restant.Preferably, for the last phase of the process, the thickness of propellant 18 present on the structure 14 is less than the thickness 34 that the flat water jet 28 can erode. This allows all of the remaining propellant to be extracted.

Aussi, même si le jet d'eau 28 plat atteint la paroi de la structure 14, celui-ci ne peut l'endommager, comme on l'a dit précédemment. La structure 14 peut alors, selon les cas de figure, être réutilisée ou retraitée.Also, even if the flat water jet 28 reaches the wall of the structure 14, it cannot damage it, as has been said previously. The structure 14 can then, depending on the case, be reused or reprocessed.

Aussi, pendant toutes les phases du procédé d'extraction, seul un mélange d'eau et de propergol est récupéré, ce qui facilite le retraitement ultérieur du propergol.Also, during all the phases of the extraction process, only a mixture of water and propellant is recovered, which facilitates the subsequent reprocessing of the propellant.

Claims (10)

Procédé d'extraction de propergol (18) depuis un corps de propulseur chargé (12),
ledit corps de propulseur chargé (12) comprenant une structure (14) allongée d'axe principal A qui est un élément de révolution autour dudit axe principal (A), et à l'intérieur de laquelle dite structure, le propergol (18) est situé,
le procédé d'extraction consistant à utiliser au moins une buse (24) produisant un jet (28) de liquide qui érode le propergol (18),
caractérisé en ce que le jet (28) de liquide est un jet plat
et en ce que la buse (24) parcourt une trajectoire hélicoïdale coaxiale à l'axe principal A lors de l'extraction du propergol (18).Method of extracting propellant (18) from a charged propellant body (12),
said loaded propellant body (12) comprising an elongated structure (14) of main axis A which is an element of revolution about said main axis (A), and inside which said structure, the propellant (18) is located,
the extraction process comprising using at least one nozzle (24) producing a jet (28) of liquid which erodes the propellant (18),
characterized in that the jet (28) of liquid is a flat jet
and in that the nozzle (24) follows a helical path coaxial with the main axis A during the extraction of the propellant (18). Procédé selon la revendication précédente, caractérisé en ce qu'il est mis en œuvre en plusieurs phases consistant chacune à éroder le propergol (18) par le jet plat (28), sur une épaisseur (34) prédéfinie.Method according to the preceding claim, characterized in that it is implemented in several phases each consisting in eroding the propellant (18) by the flat jet (28), over a predefined thickness (34). Procédé selon la revendication précédente, caractérisé en ce qu'un ajustement de la position de la buse 24 est effectué entre deux phases successives, pour rapprocher la buse (24) du propergol (18) selon un pas prédéfini.Method according to the preceding claim, characterized in that an adjustment of the position of the nozzle 24 is carried out between two successive phases, in order to bring the nozzle (24) closer to the propellant (18) according to a predefined pitch. Procédé selon l'une quelconque des revendications précédentes, caractérisé en ce que la trajectoire parcourue par la buse (24) possède un pas sensiblement égal à une étendue axiale (36) selon laquelle du propergol est érodée par le jet plat (28).Method according to any one of the preceding claims, characterized in that the path traversed by the nozzle (24) has a pitch substantially equal to an axial extent (36) according to which propellant is eroded by the flat jet (28). Installation (10) de mise en œuvre d'un procédé d'extraction de propergol (18) depuis un corps de propulseur chargé (12) selon l'une quelconque des revendications précédentes, qui comporte une perche de support (22) qui est alimentée en liquide sous pression et qui est mobile en translation et rotation selon son axe principal qui est confondu avec un axe principal A du corps de propulseur chargé (12),
au moins une buse (24) de projection d'un jet de liquide qui est portée par la perche de support (22),
des moyens (26) d'alimentation de ladite au moins une buse (24) en liquide sous pression par l'intermédiaire de la perche de support (22),
caractérisée en ce que ladite au moins une buse (24) est conçue pour projeter le liquide en un jet plat (28).Installation (10) for carrying out a method of extracting propellant (18) from a charged propellant body (12) according to any one of the preceding claims, which comprises a support pole (22) which is supplied in liquid under pressure and which is mobile in translation and rotation along its main axis which coincides with a main axis A of the loaded propellant body (12),
at least one nozzle (24) for projecting a jet of liquid which is carried by the support pole (22),
means (26) for supplying said at least one nozzle (24) with liquid under pressure via the support pole (22),
characterized in that said at least one nozzle (24) is adapted to project the liquid in a flat jet (28). Installation (10) selon la revendication précédente, caractérisée en ce que ledit jet plat (28) est délimité par deux droites (30) qui sont sécantes au niveau de la buse (24) et qui délimitent un angle (32) d'ouverture du jet plat (28) prédéfini.Installation (10) according to the preceding claim, characterized in that said flat jet (28) is delimited by two straight lines (30) which intersect at the level of the nozzle (24) and which define an angle (32) of opening of the predefined flat jet (28). Installation (10) selon la revendication précédente, caractérisée en ce que la valeur dudit angle (32) d'ouverture du jet plat (28) est de 10 degrés.Installation (10) according to the preceding claim, characterized in that the value of said angle (32) of opening of the flat jet (28) is 10 degrees. Installation (10) selon l'une quelconque des revendications 5 à 7, caractérisée en ce que ladite au moins une buse (24) est portée par un bras de support (26) permettant de réaliser un ajustement de la position et de l'orientation de la buse (24) par rapport à la perche de support (22), et qui réalise une communication fluidique entre la buse (24) et la perche de support (22).Installation (10) according to any one of claims 5 to 7, characterized in that said at least one nozzle (24) is carried by a support arm (26) making it possible to carry out an adjustment of the position and the orientation. of the nozzle (24) relative to the support pole (22), and which provides fluid communication between the nozzle (24) and the support pole (22). Installation (10) selon la revendication précédente, pour la mise en œuvre d'un procédé selon la revendication 3, caractérisée en ce qu'elle comporte une pluralité de bras de support (26) interchangeables qui sont aptes à être intervertis entre deux phases du procédé, pour modifier la position de ladite buse (24) par rapport à la perche de support (22).Installation (10) according to the preceding claim, for the implementation of a method according to claim 3, characterized in that it comprises a plurality of interchangeable support arms (26) which are able to be interchanged between two phases of the method, for changing the position of said nozzle (24) relative to the support pole (22). Installation (10) selon la revendication 8 ou 9, caractérisée en ce que chaque bras de support (26) est apte à pivoter par rapport à la perche de support (22) autour d'un axe orthogonal à l'axe principal (A) au cours d'une phase du procédé.Installation (10) according to claim 8 or 9, characterized in that each support arm (26) is able to pivot relative to the support pole (22) about an axis orthogonal to the main axis (A) during a phase of the process.
EP21159491.6A 2020-02-27 2021-02-26 Method and facility for extracting propellant from a propeller Active EP3872441B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR2001925A FR3107761A1 (en) 2020-02-27 2020-02-27 PROCESS AND INSTALLATION FOR EXTRACTING PROPERGOL FROM A PROPELLER

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EP3872441A1 true EP3872441A1 (en) 2021-09-01
EP3872441B1 EP3872441B1 (en) 2024-09-04
EP3872441C0 EP3872441C0 (en) 2024-09-04

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FR (1) FR3107761A1 (en)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3312231A (en) * 1962-10-29 1967-04-04 Thiokol Chemical Corp Apparatus for the reclamation of solid propellant rocket motor cases
US4793866A (en) * 1985-12-13 1988-12-27 Morton Thiokol, Inc. Method and apparatus for removing solid propellant from rocket motor cases
US5052624A (en) * 1988-03-11 1991-10-01 Possis Corporation Ultra high pressure water cleaning tool
WO1996021136A1 (en) * 1994-12-29 1996-07-11 Getty Heather L High pressure washout of explosive agents
DE10122433A1 (en) * 2000-05-09 2002-03-21 Waterkracht Bv Cleaning objects with water involves moving water at high pressure through heated high pressure line to spray nozzle; water is outputted from nozzle almost boiling and sprayed against object

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3312231A (en) * 1962-10-29 1967-04-04 Thiokol Chemical Corp Apparatus for the reclamation of solid propellant rocket motor cases
US4793866A (en) * 1985-12-13 1988-12-27 Morton Thiokol, Inc. Method and apparatus for removing solid propellant from rocket motor cases
US5052624A (en) * 1988-03-11 1991-10-01 Possis Corporation Ultra high pressure water cleaning tool
WO1996021136A1 (en) * 1994-12-29 1996-07-11 Getty Heather L High pressure washout of explosive agents
DE10122433A1 (en) * 2000-05-09 2002-03-21 Waterkracht Bv Cleaning objects with water involves moving water at high pressure through heated high pressure line to spray nozzle; water is outputted from nozzle almost boiling and sprayed against object

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EP3872441C0 (en) 2024-09-04
FR3107761A1 (en) 2021-09-03

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