EP3999800B1 - Underwater projectile, associated assembly and launch method - Google Patents
Underwater projectile, associated assembly and launch method Download PDFInfo
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- EP3999800B1 EP3999800B1 EP20743631.2A EP20743631A EP3999800B1 EP 3999800 B1 EP3999800 B1 EP 3999800B1 EP 20743631 A EP20743631 A EP 20743631A EP 3999800 B1 EP3999800 B1 EP 3999800B1
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- Prior art keywords
- projectile
- stop
- screw
- stress
- state
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- 230000006835 compression Effects 0.000 claims description 9
- 238000007906 compression Methods 0.000 claims description 9
- 238000011017 operating method Methods 0.000 claims 1
- 238000006073 displacement reaction Methods 0.000 description 2
- 230000002441 reversible effect Effects 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 235000005921 Cynara humilis Nutrition 0.000 description 1
- 240000002228 Cynara humilis Species 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000036316 preload Effects 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B19/00—Marine torpedoes, e.g. launched by surface vessels or submarines; Sea mines having self-propulsion means
- F42B19/12—Propulsion specially adapted for torpedoes
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/08—Rocket or torpedo launchers for marine torpedoes
- F41F3/10—Rocket or torpedo launchers for marine torpedoes from below the surface of the water
Definitions
- the present invention relates to a projectile, in particular underwater, of the type comprising a hull and a propulsion element, said propulsion element comprising: a first rotary shaft able to be rotated relative to the hull about an axis; and a first propeller capable of being driven in rotation by said first rotary shaft.
- torpedo-type underwater projectiles are launched while their propulsion system is stationary. It is necessary to apply a significant thrust force to them in order to eject them. It is in particular known to equip the launching devices with support plates driven by gas generators, as described in the document US7388145 , or pneumatic rammers, as described in the document WO2017162602 .
- Violent shocks may therefore be transferred to the rotating shafts and/or to the bearing systems carrying said rotating shafts, which may lead to damage to the propulsion mechanism.
- the object of the present invention is to provide a projectile capable of minimizing the impact of ejection on the state of the propulsion mechanism.
- the subject of the invention is a projectile of the aforementioned type, in which: the first propeller and the shell respectively comprise a first abutment and a first counter-abutment facing each other; the first propeller is adapted to slide axially along the first rotary shaft between a first position, in which a first non-zero clearance is provided between the first abutment and counter-abutment, and a second position, in which the first abutment and counter- stop are in contact; the propulsion element further comprises a first elastic return element, reversibly deformable along the axis between a first and a second stress state, said first and second states corresponding respectively to the first and second positions of the first propeller , the stress of the first state being lower than the stress of the second state.
- the invention further relates to a launch assembly comprising: a projectile as described above; and a launch tube comprising: an internal chamber capable of receiving the projectile; and an ejection device, capable of exerting a thrust on the thrust surface of the projectile, so as to eject said projectile from the internal chamber.
- the invention further relates to a method for launching a projectile as described above, comprising the following steps: application of an axial force against the thrust surface; transfer of said axial force to the first stop; so as to cause the sliding of the first propeller along the first rotary shaft, from the first position to the second position; and the transition of the first elastic return element from the first to the second stress state; Then transfer of the axial force from the first propeller to the hull, leading to the launch of the projectile; relaxation of the first elastic return element from the second to the first stress state.
- the transfer of the axial force to the first stop comprises the sliding of the second propeller along the second rotary shaft, from the third position to the fourth position; and the passage of the second elastic return element from the third to the fourth stress state; and simultaneously with the relaxation of the first elastic return element, the method comprises the relaxation of the second elastic return element from the fourth to the third stress state.
- the invention further relates to a method of operating a projectile as described above, in which: each of the first and second rotary shafts is driven in rotation relative to the shell around the axis; and the first and second helices are respectively in the first and in the third position.
- FIG. 1 shows a launch assembly 10 according to one embodiment of the invention.
- the launch assembly 10 is in particular intended to equip a ship, such as a surface vessel or a submarine.
- the launch assembly 10 is intended in particular for launching a projectile 12 in an underwater environment.
- the launch assembly 10 includes the projectile 12 and a launch tube 14.
- the projectile 12 for example a torpedo, is capable of moving in an underwater environment.
- the projectile 12 notably comprises a hull 16, one or more fins 18 and a propulsion element 20.
- the shell 16 has a longitudinal shape extending along a main axis 22.
- Said main axis 22 constitutes an axis of movement of the projectile 12.
- the propulsion element 20 is able to move the projectile 12 along said axis main 22, in a direction of movement.
- the propulsion element 20 is arranged at the rear of the hull 16 in said direction of movement.
- the propulsion element 20 comprises: an engine block 24 disposed inside the hull 16; at least one rotating shaft 26, 28; and at least one propeller 30, 32.
- the at least one rotary shaft 26, 28 is capable of being rotated relative to the shell 16, around the main axis 22, by the engine block 24.
- the at least one propeller 30, 32 is adapted to be driven in rotation by the at least one rotary shaft 26, 28 around the main axis 22.
- the propulsion element 20 further comprises at least one elastic return element 33, 34, associated with the at least one propeller 30, 32.
- the propulsion element 20 comprises a first 26 and a second 28 rotating shafts, coaxial and arranged along the main axis 22.
- the first rotating shaft 26 is of tubular shape, the second rotating shaft 28 being disposed within said first rotary shaft 26.
- a front part 35, 36 of each of the first 26 and second 28 rotary shafts is located inside the hull 16 and connected to the engine block 24.
- the first 26 and second 28 rotary shafts are free to rotate. one relative to the other.
- the motor unit 24 is capable of rotating the first 26 and second 28 rotary shafts in opposite directions of rotation.
- the engine block 24 comprises two separate motors, each of said motors being connected to one of the rotary shafts 26, 28.
- a rear portion 38, 40 of each of the first 26 and second 28 rotary shafts forms an axial projection out of the shell 16.
- the rear portion 40 of the second rotary shaft 28 forms an axial projection relative to the tubular first rotary shaft 26 .
- Each of the rear portions 38, 40 of the first 26 and second 28 rotary shafts has a threaded end 42, 44.
- First bearings 46 are interposed radially between the shell 16 and the first rotary shaft 26.
- second bearings 48 are interposed radially between the first 26 and the second 28 rotary shafts.
- the propulsion element 20 comprises a first 30 and a second 32 propeller, respectively assembled to the first 26 and to the second 28 rotary shafts.
- each of the first 30 and second 32 propellers is able to slide axially on the corresponding rotary shaft 26, 28.
- the propulsion element 20 comprises a first 33 and a second 34 elastic return elements, respectively associated with the first 30 and the second 32 propellers.
- each of the first 33 and second 34 elastic return elements is able to deform reversibly along the main axis 22, depending on the axial sliding of the propeller 30, 32 associated on the rotary shaft 26, 28 corresponding.
- the first 33 and/or the second 34 elastic return element is preferably a compression spring.
- Each of the first 30 and second 32 propellers comprises respectively a first 50 and a second 52 hubs, visible on the figure 2 .
- the first hub 50 of the first propeller 30 comprises a first mounting ring 54, in contact with the rear part 38 of the first rotary shaft 26.
- the first mounting ring 54 is locked in rotation with respect to said rear part 38.
- the first hub 50 is thus adapted to be driven in rotation by the first rotary shaft 26.
- the first hub 50 further comprises a front surface, forming a first abutment 56.
- Said first abutment 56 is a surface substantially perpendicular to the main axis 22 and oriented forwards.
- the shell 16 also comprises a rear surface, forming a first counter-stop 58.
- Said first counter-stop 58 is a surface substantially perpendicular to the main axis 22 and facing rearward.
- each of the first abutment 56 and counter-abutment 58 is substantially planar and crown-shaped, continuous or fragmented.
- the first elastic return element is a first spring washer 33, of the Belleville washer type, arranged around the rear part 38 of the first rotary shaft 26.
- the front of the first spring washer 33 is blocked axially by said rear part 38; the rear of said first spring washer 33 is in contact with the first mounting ring 54.
- the propulsion element 20 comprises a first nut 60, associated with the first propeller 30.
- the first nut 60 is mounted on the threaded end 42 of the first rotary shaft 26.
- the first mounting ring 54 is interposed axially between the first washer spring 33 and the first nut 60.
- the first nut 60 is in axial contact with the first mounting ring 54; the first spring washer 33 is compressed axially in a first stress state, between said first ring 54 and the first rotating shaft 26; moreover, a first non-zero axial clearance 62 is provided between the first stop 56, carried by the first propeller 30, and the first counter-stop 58 carried by the shell 16.
- the stress of the first spring washer 33 in the first state is non-zero, said first spring washer 33 therefore being prestressed in the first configuration of the projectile 12.
- the first hub 50 is able to slide on the first rotary shaft 26 between a first position, corresponding to the first configuration described above, and a second position (not shown) in which the first stops 56 and counter-stops 58 are at the contact with each other.
- the first spring washer 33 When the first hub 50 is in the second position, the first spring washer 33 is compressed axially in a second stress state, corresponding to a stress greater than the first state. The first spring washer 33 therefore tends to bring the first hub 50 back into the first position.
- the second hub 52 of the second propeller 32 includes a second mounting ring 64, in contact with the rear part 40 of the second rotary shaft 28.
- the second mounting ring 64 is locked in rotation with respect to said rear part 40.
- the second hub 52 is thus adapted to be driven in rotation by the second rotary shaft 28.
- the second hub 52 further comprises a front surface, forming a second abutment 66.
- Said second abutment 66 is a surface substantially perpendicular to the main axis 22 and oriented forwards.
- the first hub 50 also comprises a rear surface, forming a second counter-stop 68.
- Said second counter-stop 68 is a surface substantially perpendicular to the main axis 22 and facing rearward.
- each of the second abutment 66 and counter-abutment 68 is substantially planar and crown-shaped, continuous or fragmented.
- the second elastic return element is a second spring washer 34, of the Belleville washer type, arranged around the rear part 40 of the second rotary shaft 28.
- the front of the second spring washer 34 is blocked axially by said rear part 40; the rear of said second spring washer 34 is in contact with the second mounting ring 64.
- the propulsion element 20 comprises a second nut 70, associated with the second propeller 32.
- the second nut 70 is mounted on the threaded end 44 of the second rotary shaft 28.
- the second mounting ring 64 is interposed axially between the second washer spring 34 and the second nut 70.
- the second nut 70 is in axial contact with the second mounting ring 64; the second spring washer 34 is compressed axially in a third stress state, between said second ring 64 and the second rotary shaft 28; moreover, a second non-zero axial clearance 72 is provided between the second stop 66, carried by the second propeller 32, and the second counter-stop 68 carried by the first propeller 30.
- the stress of the second spring washer 34 in the third state is non-zero, said second spring washer 34 therefore being prestressed in the first configuration of the projectile 12.
- the second hub 52 is able to slide on the second rotary shaft 28 between a third position, corresponding to the first configuration of the projectile 12 described above, and a fourth position.
- the second abutments 66 and counter-abutments 68 are in contact with one another; and the first abutment 56 and counter-abutment 58, described above, are also in contact with each other.
- the first hub 50 is compressed axially between the shell 16 and the second hub 52.
- This fourth position of the second hub 52 corresponds to a second configuration of the projectile 12 , not shown.
- the second spring washer 34 When the second hub 52 is in the fourth position, the second spring washer 34 is compressed axially in a fourth stress state, corresponding to a stress greater than the third state. The second spring washer 34 therefore tends to bring the second hub 52 back into the third position, corresponding to the first configuration of the projectile 12.
- the first 62 and second 72 axial clearances are in particular adjusted during the manufacture of the projectile 12, by the screwing position of the first 60 and second 70 nuts on the corresponding threaded ends 42, 44 of the rotary shafts 26, 28.
- the constraint of each spring washer 33, 34 in the first configuration of the projectile 12 also depends on the screwing position of the corresponding nut 60, 70.
- the second hub 52 further comprises a rear surface, forming a thrust surface 74 of the projectile 12.
- Said thrust surface 74 is a surface substantially perpendicular to the main axis 22 and oriented rearward.
- thrust surface 74 is crown-shaped, continuous or fragmented, disposed radially from rotating shafts 26, 28.
- the propulsion element of the projectile only comprises a single rotary shaft 26 and a single propeller 30.
- the thrust surface of the projectile is thus formed by the rear surface 68 of the first hub 50, by analogy with the figure 2 .
- the launch tube 14 comprises an internal chamber 80 and a launching device 82.
- the internal chamber 80 capable of containing the projectile 12, has an elongated shape along an axis 84 and includes an opening 86 at one end.
- the launching device 82 arranged at the other end of the internal chamber 80, is capable of ejecting the projectile 12 from the launch tube through the opening 86.
- the launching device 82 comprises for example a pneumatic rammer, as described in the document WO2017162602 .
- Said pneumatic rammer comprises in particular a thrust head 88, movable axially with respect to the internal chamber 80.
- the thrust head 88 is in particular configured to exert a thrust along the axis 84 against the thrust surface 74 of the projectile 12.
- the pusher head 88 is configured to come into axial contact with the pusher surface 74 without coming into contact with the rotary shafts 26, 28.
- the pusher head 88 has, for example, a front surface in the form of a crown.
- the thrust surface 74 forms a rear projection relative to the second rotary shaft 28 and the thrust head 88 can then have a disc-shaped front surface.
- FIG. 1 represents the launch assembly 10 in an initial configuration, in which the projectile 12 is received in the internal chamber 80.
- the main axis 22 of the projectile 12 and the axis 84 of the internal chamber 80 are substantially coincident.
- the launch assembly 10 equipping for example a submarine, is in a submerged environment.
- the tube launching tube 14 is placed under water, the internal chamber 80 is filled with water and the opening 86 emerges for example under the surface of the sea.
- the projectile 12 is received in the launching tube 14, in the initial configuration previously described.
- the projectile 12 is then in the first configuration, described above and visible on the figure 2 .
- the launching device 82 is then activated, leading to the axial displacement of the thrust head 88.
- Said thrust head therefore exerts a force against the thrust surface 74 of the projectile 12, said force being oriented along the main axis 22 and directed forward.
- the thrust force is thus transmitted essentially to the second hub 52, which carries the thrust surface 74 of the projectile 12.
- the second hub 52 is therefore driven in axial sliding along the second rotary shaft 28, which compresses the second spring washer 34.
- the projectile 12 then reaches the second configuration, in which the first stop 56 carried by the first hub 50 comes into contact with the first counter-stop 58, carried by the shell 16.
- the second stop 66 and counter-stop 68 are always at contact with each other.
- the axial thrust force exerted by the thrust head 88 is therefore transmitted to the shell 16 of the projectile 12, via the second 52 and the first 50 hubs.
- the projectile 12 is thus ejected from the internal chamber 80 through the opening 86.
- the thrust force is transmitted essentially to the shell 16, with little impact on the rotating shafts 26, 28 and on the bearings 46, 48.
- the proportion of the thrust force transmitted to the bearings is in particular l order from 10% to 20%.
- the bearings 46, 48 only see the load of the preload of the spring washers 33, 34 and the stress exerted by the additional compression of the washers for a stroke equal to the functional clearance 62, 72. The risks of deterioration of the propulsion element 20 during the ejection of the projectile 12 are thus minimized.
- the first 33 and second 34 spring washers relax, bringing the projectile 12 back to the first configuration.
- the first 62 and second 72 axial clearances are restored between the shell 16, the first hub 50 and the second hub 52.
- the engine block 24 of the propulsion element 20 is started.
- Each of the first 30 and second 32 propellers is driven in rotation by the corresponding rotary shaft 26, 28, the first 62 and second 72 axial clearances allowing such rotational movements.
- the projectile 12 thus moves in an underwater environment.
- the propulsive force exerted by the propellers 30, 32 is much lower than the force exerted by the thrust head 88 at the stage of ejection of the projectile 12 from the tube. launch. This propulsion force is therefore applied to the spring washers 33, 34 without leading to the cancellation of the functional clearances 62, 72.
- a similar method makes it possible to implement a launch assembly comprising such a projectile associated with the launch tube 14.
- the thrust force of the launch tube is transferred to the hull of the projectile via the single helix, which is accompanied by the reversible compression of the elastic return element associated with said helix.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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- Ocean & Marine Engineering (AREA)
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Description
La présente invention concerne un projectile, notamment sous-marin, du type comportant une coque et un élément de propulsion, ledit élément de propulsion comprenant : un premier arbre rotatif apte à être mis en rotation par rapport à la coque autour d'un axe ; et une première hélice apte à être entraînée en rotation par ledit premier arbre rotatif.The present invention relates to a projectile, in particular underwater, of the type comprising a hull and a propulsion element, said propulsion element comprising: a first rotary shaft able to be rotated relative to the hull about an axis; and a first propeller capable of being driven in rotation by said first rotary shaft.
De manière classique, pour des raisons de sécurité, les projectiles sous-marins de type torpilles sont lancés alors que leur système de propulsion est à l'arrêt. Il est nécessaire de leur appliquer un effort de poussée important afin de les éjecter. Il est notamment connu d'équiper les dispositifs de lancement de plaques d'appui entraînées par des générateurs de gaz, comme décrit dans le document
L'effort d'éjection s'applique à la partie arrière de la torpille et est notamment reçu par l'hélice ou les hélices. Des chocs violents peuvent dont être transférés aux arbres rotatifs et/ou aux systèmes de roulements portant lesdits arbres rotatifs, ce qui peut entraîner des détériorations du mécanisme de propulsion.The ejection force applies to the rear part of the torpedo and is in particular received by the propeller or the propellers. Violent shocks may therefore be transferred to the rotating shafts and/or to the bearing systems carrying said rotating shafts, which may lead to damage to the propulsion mechanism.
La présente invention a pour but de fournir un projectile apte à minimiser l'impact de l'éjection sur l'état du mécanisme de propulsion.The object of the present invention is to provide a projectile capable of minimizing the impact of ejection on the state of the propulsion mechanism.
A cet effet, l'invention a pour objet un projectile du type précité, dans lequel : la première hélice et la coque comprennent respectivement une première butée et une première contre-butée en vis-à -vis l'une de l'autre ; la première hélice est apte à coulisser axialement le long du premier arbre rotatif entre une première position, dans laquelle un premier jeu non nul est ménagé entre les premières butée et contre-butée, et une deuxième position, dans laquelle les premières butée et contre-butée sont en contact ; l'élément de propulsion comporte en outre un premier élément de rappel élastique, réversiblement déformable selon l'axe entre un premier et un deuxième états de contrainte, lesdits premier et deuxième états correspondant respectivement à la première et à la deuxième positions de la première hélice, la contrainte du premier état étant inférieure à la contrainte du deuxième état.To this end, the subject of the invention is a projectile of the aforementioned type, in which: the first propeller and the shell respectively comprise a first abutment and a first counter-abutment facing each other; the first propeller is adapted to slide axially along the first rotary shaft between a first position, in which a first non-zero clearance is provided between the first abutment and counter-abutment, and a second position, in which the first abutment and counter- stop are in contact; the propulsion element further comprises a first elastic return element, reversibly deformable along the axis between a first and a second stress state, said first and second states corresponding respectively to the first and second positions of the first propeller , the stress of the first state being lower than the stress of the second state.
Suivant d'autres aspects avantageux de l'invention, le projectile comporte l'une ou plusieurs des caractéristiques suivantes, prises isolément ou suivant toutes les combinaisons techniquement possibles :
- le premier élément de rappel élastique est un ressort de compression, de préférence une rondelle ressort ;
- la première hélice comporte en outre une deuxième contre-butée, axialement opposée à la première butée ;
- l'élément de propulsion comporte en outre : un deuxième arbre rotatif apte à être mis en rotation par rapport à la coque autour de l'axe ; et une deuxième hélice apte à être entraînée en rotation par ledit deuxième arbre rotatif ; la deuxième hélice comprend une deuxième butée en vis-à -vis de la deuxième contre-butée ; la deuxième hélice est apte à coulisser axialement le long du deuxième arbre rotatif entre une troisième position, dans laquelle un deuxième jeu non nul est ménagé entre les deuxièmes butée et contre-butée, et une quatrième position, dans laquelle les deuxièmes butée et contre-butée sont en contact ; l'élément de propulsion comporte en outre un deuxième élément de rappel élastique, réversiblement déformable selon l'axe entre un troisième et un quatrième états de contrainte, lesdits troisième et quatrième états correspondant respectivement à la troisième et à la quatrième positions de la deuxième hélice, la contrainte du troisième état étant inférieure à la contrainte du quatrième état ;
- l'élément de propulsion est configuré de sorte que, lorsque la deuxième hélice est dans la quatrième position par rapport au deuxième arbre rotatif, la première hélice est dans la deuxième position par rapport au premier arbre rotatif ;
- le deuxième élément de rappel élastique est un ressort de compression, de préférence une rondelle ressort ;
- les premier et deuxième arbres rotatifs ont des sens de rotation opposés ;
- le projectile comprend une surface de poussée apte à transférer un effort axial à la première hélice ;
- la surface de poussée est portée par la deuxième hélice et axialement opposée à la deuxième butée.
- the first elastic return element is a compression spring, preferably a spring washer;
- the first propeller further comprises a second counter-stop, axially opposite to the first stop;
- the propulsion element further comprises: a second rotary shaft adapted to be rotated relative to the hull around the axis; and a second propeller capable of being driven in rotation by said second rotary shaft; the second propeller comprises a second abutment facing the second counter-abutment; the second propeller is adapted to slide axially along the second rotary shaft between a third position, in which a second non-zero play is provided between the second abutment and counter-abutment, and a fourth position, in which the second abutment and counter- stop are in contact; the propulsion element further comprises a second elastic return element, reversibly deformable along the axis between a third and a fourth states of stress, said third and fourth states corresponding respectively to the third and to the fourth positions of the second propeller , the stress of the third state being less than the stress of the fourth state;
- the propulsion element is configured such that when the second propeller is in the fourth position relative to the second rotating shaft, the first propeller is in the second position relative to the first rotating shaft;
- the second elastic return element is a compression spring, preferably a spring washer;
- the first and second rotating shafts have opposite directions of rotation;
- the projectile comprises a thrust surface able to transfer an axial force to the first propeller;
- the thrust surface is carried by the second propeller and axially opposite the second stop.
L'invention se rapporte en outre à un ensemble de lancement comprenant : un projectile tel que décrit ci-dessus ; et un tube de lancement comportant : une chambre interne apte à recevoir le projectile ; et un dispositif d'éjection, apte à exercer une poussée sur la surface de poussée du projectile, de sorte à éjecter ledit projectile hors de la chambre interne.The invention further relates to a launch assembly comprising: a projectile as described above; and a launch tube comprising: an internal chamber capable of receiving the projectile; and an ejection device, capable of exerting a thrust on the thrust surface of the projectile, so as to eject said projectile from the internal chamber.
L'invention se rapporte en outre à un procédé de lancement d'un projectile tel que décrit ci-dessus, comprenant les étapes suivantes : application d'un effort axial contre la surface de poussée ; transfert dudit effort axial à la première butée ; de sorte à entraîner le coulissement de la première hélice le long du premier arbre rotatif, de la première position à la deuxième position ; et le passage du premier élément de rappel élastique du premier au deuxième état de contrainte ; puis transfert de l'effort axial de la première hélice à la coque, conduisant au lancement du projectile ; détente du premier élément de rappel élastique du deuxième au premier état de contrainte.The invention further relates to a method for launching a projectile as described above, comprising the following steps: application of an axial force against the thrust surface; transfer of said axial force to the first stop; so as to cause the sliding of the first propeller along the first rotary shaft, from the first position to the second position; and the transition of the first elastic return element from the first to the second stress state; Then transfer of the axial force from the first propeller to the hull, leading to the launch of the projectile; relaxation of the first elastic return element from the second to the first stress state.
Selon un mode de réalisation préféré, le transfert de l'effort axial à la première butée comprend le coulissement de la deuxième hélice le long du deuxième arbre rotatif, de la troisième position à la quatrième position ; et le passage du deuxième élément de rappel élastique du troisième au quatrième état de contrainte ; et simultanément à la détente du premier élément de rappel élastique, le procédé comprend la détente du deuxième élément de rappel élastique du quatrième au troisième état de contrainte.According to a preferred embodiment, the transfer of the axial force to the first stop comprises the sliding of the second propeller along the second rotary shaft, from the third position to the fourth position; and the passage of the second elastic return element from the third to the fourth stress state; and simultaneously with the relaxation of the first elastic return element, the method comprises the relaxation of the second elastic return element from the fourth to the third stress state.
L'invention se rapporte en outre à un procédé de fonctionnement d'un projectile tel que décrit ci-dessus, dans lequel : chacun des premier et deuxième arbres rotatifs est entraîné en rotation par rapport à la coque autour de l'axe ; et les première et deuxième hélices sont respectivement dans la première et dans la troisième positions.The invention further relates to a method of operating a projectile as described above, in which: each of the first and second rotary shafts is driven in rotation relative to the shell around the axis; and the first and second helices are respectively in the first and in the third position.
L'invention sera mieux comprise à la lecture de la description qui va suivre, donnée uniquement à titre d'exemple non limitatif et faite en se référant aux dessins sur lesquels :
- [
Fig 1 ] lafigure 1 est une vue schématique, en coupe partielle, d'un ensemble de lancement comprenant un projectile selon un mode de réalisation de l'invention ; et - [
Fig 2 ] lafigure 2 est une vue schématique partielle, en coupe, du projectile de lafigure 1 .
- [
Fig 1 ] therefigure 1 is a schematic view, in partial section, of a launching assembly comprising a projectile according to one embodiment of the invention; And - [
Fig 2 ] therefigure 2 is a partial schematic view, in section, of the projectile of thefigure 1 .
La
L'ensemble de lancement 10 est notamment destiné au lancement d'un projectile 12 en milieu sous-marin. L'ensemble de lancement 10 comporte le projectile 12 et un tube 14 de lancement.The
Le projectile 12, par exemple une torpille, est apte à se déplacer en milieu sous-marin. Le projectile 12 comporte notamment une coque 16, un ou des ailerons 18 et un élément de propulsion 20.The
La coque 16 présente une forme longitudinale s'étendant selon un axe principal 22. Ledit axe principal 22 constitue un axe de déplacement du projectile 12. L'élément de propulsion 20 est apte à déplacer le projectile 12 le long dudit axe principal 22, selon un sens de déplacement. L'élément de propulsion 20 est disposé à l'arrière de la coque 16 selon ledit sens de déplacement.The
L'élément de propulsion 20 comprend : un bloc moteur 24 disposé à l'intérieur de la coque 16 ; au moins un arbre rotatif 26, 28 ; et au moins une hélice 30, 32.The
L'au moins un arbre rotatif 26, 28 est apte Ă ĂŞtre mis en rotation par rapport Ă la coque 16, autour de l'axe principal 22, par le bloc moteur 24.The at least one
L'au moins une hélice 30, 32 est apte à être entraînée en rotation par l'au moins un arbre rotatif 26, 28 autour de l'axe principal 22.The at least one
Comme il sera détaillé par la suite, l'élément de propulsion 20 comprend en outre au moins un élément 33, 34 de rappel élastique, associé à l'au moins une hélice 30, 32.As will be detailed below, the
Une vue de détail de l'élément de propulsion 20 est visible sur la
Une partie avant 35, 36 de chacun des premier 26 et deuxième 28 arbres rotatifs est située à l'intérieur de la coque 16 et reliée au bloc moteur 24. De préférence, les premier 26 et deuxième 28 arbres rotatifs sont libres en rotation l'un par rapport à l'autre. Selon un mode de réalisation préférentiel, le bloc moteur 24 est apte à faire tourner les premier 26 et deuxième 28 arbres rotatifs selon des sens de rotation opposés.A
De préférence, le bloc moteur 24 comporte deux moteurs distincts, chacun desdits moteurs étant relié à l'un des arbres rotatifs 26, 28.Preferably, the
Une partie arrière 38, 40 de chacun des premier 26 et deuxième 28 arbres rotatifs forme une saillie axiale hors de la coque 16. De plus, la partie arrière 40 du deuxième arbre rotatif 28 forme une saillie axiale par rapport au premier arbre rotatif 26 tubulaire.A
Chacune des parties arrière 38, 40 des premier 26 et deuxième 28 arbres rotatifs comporte une extrémité filetée 42, 44.Each of the
Des premiers roulements 46 sont interposés radialement entre la coque 16 et le premier arbre rotatif 26. De même, des deuxièmes roulements 48 sont interposés radialement entre le premier 26 et le deuxième 28 arbres rotatifs.
Dans le mode de réalisation représenté sur les
Comme visible sur la
Chacune des première 30 et deuxième 32 hélices comporte respectivement un premier 50 et un deuxième 52 moyeux, visibles sur la
Le premier moyeu 50 de la première hélice 30 comporte une première bague de montage 54, au contact de la partie arrière 38 du premier arbre rotatif 26. La première bague de montage 54 est bloquée en rotation par rapport à ladite partie arrière 38. Le premier moyeu 50 est ainsi apte à être entraîné en rotation par le premier arbre rotatif 26.The
Le premier moyeu 50 comporte en outre une surface avant, formant une première butée 56. Ladite première butée 56 est une surface sensiblement perpendiculaire à l'axe principal 22 et orientée vers l'avant.The
La coque 16 comporte par ailleurs une surface arrière, formant une première contre-butée 58. Ladite première contre-butée 58 est une surface sensiblement perpendiculaire à l'axe principal 22 et orientée vers l'arrière.The
De préférence, chacune des premières butée 56 et contre-butée 58 est sensiblement plane et en forme de couronne, continue ou fragmentée.Preferably, each of the
Dans le mode de réalisation représenté, le premier élément de rappel élastique est une première rondelle ressort 33, de type rondelle Belleville, disposée autour de la partie arrière 38 du premier arbre rotatif 26. L'avant de la première rondelle ressort 33 est bloqué axialement par ladite partie arrière 38 ; l'arrière de ladite première rondelle ressort 33 est au contact de la première bague de montage 54.In the embodiment shown, the first elastic return element is a
L'élément de propulsion 20 comporte un premier écrou 60, associé à la première hélice 30. Le premier écrou 60 est monté sur l'extrémité filetée 42 du premier arbre rotatif 26. La première bague de montage 54 est interposée axialement entre la première rondelle ressort 33 et le premier écrou 60.The
Dans une première configuration du projectile 12, visible sur la
De préférence, la contrainte de la première rondelle ressort 33 dans le premier état est non nulle, ladite première rondelle ressort 33 étant donc précontrainte dans la première configuration du projectile 12.Preferably, the stress of the
Le premier moyeu 50 est apte à coulisser sur le premier arbre rotatif 26 entre une première position, correspondant à la première configuration décrite ci-dessus, et une deuxième position (non représentée) dans laquelle les premières butée 56 et contre-butée 58 sont au contact l'une de l'autre.The
Lorsque le premier moyeu 50 est dans la deuxième position, la première rondelle ressort 33 est comprimée axialement dans un deuxième état de contrainte, correspondant à une contrainte supérieure au premier état. La première rondelle ressort 33 tend donc à ramener le premier moyeu 50 dans la première position.When the
Le deuxième moyeu 52 de la deuxième hélice 32 comporte une deuxième bague de montage 64, au contact de la partie arrière 40 du deuxième arbre rotatif 28. La deuxième bague de montage 64 est bloquée en rotation par rapport à ladite partie arrière 40. Le deuxième moyeu 52 est ainsi apte à être entraîné en rotation par le deuxième arbre rotatif 28.The
Le deuxième moyeu 52 comporte en outre une surface avant, formant une deuxième butée 66. Ladite deuxième butée 66 est une surface sensiblement perpendiculaire à l'axe principal 22 et orientée vers l'avant.The
Le premier moyeu 50 comporte par ailleurs une surface arrière, formant une deuxième contre-butée 68. Ladite deuxième contre-butée 68 est une surface sensiblement perpendiculaire à l'axe principal 22 et orientée vers l'arrière.The
De préférence, chacune des deuxièmes butée 66 et contre-butée 68 est sensiblement plane et en forme de couronne, continue ou fragmentée.Preferably, each of the
Dans le mode de réalisation représenté, le deuxième élément de rappel élastique est une deuxième rondelle ressort 34, de type rondelle Belleville, disposée autour de la partie arrière 40 du deuxième arbre rotatif 28. L'avant de la deuxième rondelle ressort 34 est bloqué axialement par ladite partie arrière 40 ; l'arrière de ladite deuxième rondelle ressort 34 est au contact de la deuxième bague de montage 64.In the embodiment shown, the second elastic return element is a
L'élément de propulsion 20 comporte un deuxième écrou 70, associé à la deuxième hélice 32. Le deuxième écrou 70 est monté sur l'extrémité filetée 44 du deuxième arbre rotatif 28. La deuxième bague de montage 64 est interposée axialement entre la deuxième rondelle ressort 34 et le deuxième écrou 70.The
Dans la première configuration du projectile 12, visible sur la
De préférence, la contrainte de la deuxième rondelle ressort 34 dans le troisième état est non nulle, ladite deuxième rondelle ressort 34 étant donc précontrainte dans la première configuration du projectile 12.Preferably, the stress of the
Le deuxième moyeu 52 est apte à coulisser sur le deuxième arbre rotatif 28 entre une troisième position, correspondant à la première configuration du projectile 12 décrite ci-dessus, et une quatrième position.The
Dans ladite quatrième position du deuxième moyeu 52, les deuxièmes butée 66 et contre-butée 68 sont au contact l'une de l'autre ; et les premières butée 56 et contre-butée 58, décrites ci-dessus, sont également au contact l'une de l'autre.In said fourth position of the
Plus précisément, dans la quatrième position du deuxième moyeu 52 sur le deuxième arbre rotatif 28, le premier moyeu 50 est comprimé axialement entre la coque 16 et le deuxième moyeu 52. Cette quatrième position du deuxième moyeu 52 correspond à une deuxième configuration du projectile 12, non représentée.More precisely, in the fourth position of the
Lorsque le deuxième moyeu 52 est dans la quatrième position, la deuxième rondelle ressort 34 est comprimée axialement dans un quatrième état de contrainte, correspondant à une contrainte supérieure au troisième état. La deuxième rondelle ressort 34 tend donc à ramener le deuxième moyeu 52 dans la troisième position, correspondant à la première configuration du projectile 12.When the
Les premier 62 et deuxième 72 jeux axiaux sont notamment réglés lors de la fabrication du projectile 12, par la position de vissage des premier 60 et deuxième 70 écrous sur les extrémités filetées 42, 44 correspondantes des arbres rotatifs 26, 28. La contrainte de chaque rondelle ressort 33, 34 dans la première configuration du projectile 12 dépend également de la position de vissage de l'écrou 60, 70 correspondant.The first 62 and second 72 axial clearances are in particular adjusted during the manufacture of the projectile 12, by the screwing position of the first 60 and second 70 nuts on the corresponding threaded ends 42, 44 of the
Le deuxième moyeu 52 comporte en outre une surface arrière, formant une surface de poussée 74 du projectile 12. Ladite surface de poussée 74 est une surface sensiblement perpendiculaire à l'axe principal 22 et orientée vers l'arrière.The
De préférence, la surface de poussée 74 est en forme de couronne, continue ou fragmentée, disposée à distance radiale des arbres rotatifs 26, 28.Preferably, thrust
Selon une variante de réalisation non représentée, l'élément de propulsion du projectile ne comporte qu'un seul arbre rotatif 26 et une seule hélice 30. La surface de poussée du projectile est ainsi formée par la surface arrière 68 du premier moyeu 50, par analogie avec la
Le tube de lancement 14 de l'ensemble de lancement 10 va à présent être décrit.
Le tube de lancement 14 comprend une chambre interne 80 et un dispositif de lancement 82. La chambre interne 80, apte à contenir le projectile 12, présente une forme allongée selon un axe 84 et comporte une ouverture 86 à une extrémité. Le dispositif de lancement 82, disposé à l'autre extrémité de la chambre interne 80, est apte à éjecter le projectile 12 hors du tube de lancement par l'ouverture 86.The
Le dispositif de lancement 82 comporte par exemple un refouloir pneumatique, comme décrit dans le document
En particulier, la tête de poussée 88 est configurée pour entrer en contact axial avec la surface de poussée 74 sans entrer en contact avec les arbres rotatifs 26, 28. La tête de poussée 88 présente par exemple une surface frontale en forme de couronne. En variante non représentée, la surface de poussée 74 forme une saillie arrière par rapport au deuxième arbre rotatif 28 et la tête de poussée 88 peut alors présenter une surface frontale en forme de disque.In particular, the
La
Un procédé de mise en oeuvre de l'ensemble de lancement 10 ci-dessus va maintenant être décrit.A method of implementing the
Dans un état initial du procédé, l'ensemble de lancement 10, équipant par exemple un sous-marin, est dans un environnement immergé. En particulier, le tube de lancement 14 est disposé sous l'eau, la chambre interne 80 est remplie d'eau et l'ouverture 86 débouche par exemple sous la surface de la mer. Par ailleurs, le projectile 12 est reçu dans le tube de lancement 14, dans la configuration initiale précédemment décrite. Le projectile 12 est alors dans la première configuration, décrite ci-dessus et visible sur la
Le dispositif de lancement 82 est alors activé, conduisant au déplacement axial de la tête de poussée 88. Ladite tête de poussée exerce donc un effort contre la surface de poussée 74 du projectile 12, ledit effort étant orienté selon l'axe principal 22 et dirigé vers l'avant.The launching
L'effort de poussée est ainsi transmis essentiellement au deuxième moyeu 52, qui porte la surface de poussée 74 du projectile 12. Le deuxième moyeu 52 est donc entraîné en coulissement axial le long du deuxième arbre rotatif 28, ce qui comprime la deuxième rondelle ressort 34.The thrust force is thus transmitted essentially to the
A partir d'une position intermédiaire du deuxième moyeu 52 le long du deuxième arbre rotatif 28, la deuxième butée 66 portée par ledit deuxième moyeu 52 vient au contact de la deuxième contre-butée 68, portée par le premier moyeu 50. Ledit premier moyeu 50 est alors également entraîné en coulissement axial par rapport au premier arbre rotatif 26, ce qui comprime la première rondelle ressort 33.From an intermediate position of the
Le projectile 12 atteint ensuite la deuxième configuration, dans laquelle la première butée 56 portée par le premier moyeu 50 vient au contact de la première contre-butée 58, portée par la coque 16. Les deuxièmes butée 66 et contre-butée 68 sont toujours au contact l'une de l'autre.The projectile 12 then reaches the second configuration, in which the
L'effort axial de poussée exercé par la tête de poussée 88 est donc transmis à la coque 16 du projectile 12, par l'intermédiaire du deuxième 52 et du premier 50 moyeux. Le projectile 12 est ainsi éjecté hors de la chambre interne 80 par l'ouverture 86.The axial thrust force exerted by the
En particulier, l'effort de poussée est transmis essentiellement à la coque 16, avec un faible impact sur les arbres rotatifs 26, 28 et sur les roulements 46, 48. La proportion de l'effort de poussée transmis aux roulements est notamment de l'ordre de 10% à 20%. En effet, les roulements 46, 48 ne voient que la charge de la précontrainte des rondelles ressort 33, 34 et la contrainte exercée par la compression supplémentaire des rondelles pour une course égale au jeu fonctionnel 62, 72. Les risques de détérioration de l'élément de propulsion 20 lors de l'éjection du projectile 12 sont ainsi minimisés.In particular, the thrust force is transmitted essentially to the
Lorsque la tête de poussée 88 n'est plus en contact avec la surface de poussée 74, les première 33 et deuxième 34 rondelles ressorts se détendent, ramenant le projectile 12 dans la première configuration. En particulier, les premier 62 et deuxième 72 jeux axiaux sont rétablis entre la coque 16, le premier moyeu 50 et le deuxième moyeu 52.When the
Lorsque le projectile 12 est hors du tube de lancement 14, le bloc moteur 24 de l'élément de propulsion 20 est mis en route. Chacune des première 30 et deuxième 32 hélices est entraînée en rotation par l'arbre rotatif 26, 28 correspondant, les premier 62 et deuxième 72 jeux axiaux autorisant de tels mouvements de rotation. Le projectile 12 se déplace ainsi en milieu sous-marin.When the projectile 12 is out of the
En particulier, lors du fonctionnement du bloc moteur 24, l'effort de propulsion exercé par les hélices 30, 32 est très inférieur à l'effort exercé par la tête de poussée 88 à l'étape d'éjection du projectile 12 hors du tube de lancement. Cet effort de propulsion s'applique donc sur les rondelles ressort 33, 34 sans entrainer l'annulation des jeux fonctionnels 62, 72.In particular, during operation of the
Le déplacement axial des premier 50 et deuxième 52 moyeux étant réversible grâce aux éléments 33, 34 de rappel élastique associés, le projectile 12 peut être éjecté plusieurs fois selon le procédé ci-dessus, sans détérioration de l'élément de propulsion 20.The axial displacement of the first 50 and second 52 hubs being reversible thanks to the associated
Dans la variante de réalisation évoquée ci-dessus, selon laquelle le projectile ne comporte qu'un arbre rotatif et une hélice, un procédé similaire permet de mettre en oeuvre un ensemble de lancement comprenant un tel projectile associé au tube de lancement 14. En particulier, l'effort de poussée du tube de lancement est transféré à la coque du projectile par l'intermédiaire de l'unique hélice, ce qui s'accompagne de la compression réversible de l'élément de rappel élastique associé à ladite hélice.In the variant embodiment mentioned above, according to which the projectile comprises only a rotating shaft and a propeller, a similar method makes it possible to implement a launch assembly comprising such a projectile associated with the
Claims (13)
- A projectile (12) comprising a shell (16) and a propulsion element (20), said propulsion element comprising: a first rotating shaft (26) able to be set in rotation relative to the shell about an axis (22); and a first screw (30, 50) able to be driven in rotation by said first rotating shaft;
characterized in that:- the first screw and the shell respectively comprise a first stop (56) and a first counter-stop (58) opposite one another;- the first screw is able to slide axially along the first rotating shaft between a first position, in which a first non-zero clearance (62) is provided between the first stop and counter-stop, and a second position, in which the first stop (56) and counter-stop (58) are in contact;- the propulsion element further includes a first elastic return element (33), which is reversibly deformable along the axis (22) between a first and a second state of stress, which first and second states correspond respectively to the first and second positions of the first screw (30, 50), the stress of the first state being lower than the stress of the second state. - The projectile according to claim 1, wherein the first elastic return element (33) is a compression spring, preferably a lock washer.
- The projectile according to claim 1 or claim 2, wherein the first screw further includes a second counter-stop (68), axially opposite the first stop.
- The projectile according to claim 3, wherein:- the propulsion element further includes: a second rotating shaft (28) able to be set in rotation relative to the shell about the axis; and a second screw (32, 52) able to be rotated by said second rotating shaft;- the second screw comprises a second stop (66) opposite the second counter-stop (68);- the second screw is able to slide axially along the second rotating shaft between a third position, in which a second non-zero clearance (72) is provided between the second stop and counter-stop, and a fourth position, in which the second stop (66) and counter-stop (68) are in contact;- the propulsion element further includes a second elastic return element (34), which is reversibly deformable along the axis (22) between a third and a fourth state of stress respectively corresponding to the third and the fourth positions of the second screw (32, 52), the stress of the third state being lower than the stress of the fourth state.
- The projectile according to claim 4, wherein the propulsion element (20) is configured such that, when the second screw (32, 52) is in the fourth position relative to the second rotating shaft (28), the first screw (30) is in the second position relative to the first rotating shaft (26).
- The projectile according to one of claims 4 or 5, wherein the second elastic return element (34) is a compression spring, preferably a lock washer.
- The projectile according to one of claims 4 to 6, wherein the first (26) and second (28) rotating shafts have opposite directions of rotation.
- The projectile according to one of the preceding claims, comprising a thrust surface (74) able to transfer an axial force to the first screw (30, 50).
- The projectile according to claim 8 combined with one of claims 4 to 7, wherein the thrust surface (74) is borne by the second screw (32) and axially opposite the second stop (66).
- A launching assembly (10) comprising:- un projectile (12) according to one of claims 8 or 9; and
a launching tube (14) including: an inner chamber (80) able to receive the projectile; and an ejection device (82, 88), able to exert thrust on the thrust surface (74) of the projectile, so as to eject said projectile from the inner chamber. - A method for launching a projectile (12) according to one of claims 8 or 9, comprising the following steps:- applying an axial force against the thrust surface (74);- transferring said axial force to the first stop (56), so as to cause the first screw (30, 50) to slide along the first rotating shaft (26), from the first position to the second position; and the passage of the first elastic return element (33) from the first to the second state of stress; then- transferring the axial force from the first screw (30, 50) to the shell (16), leading to launching of the projectile (12);- releasing the first elastic return element (33) from the second to the first state of stress.
- The method according to claim 11, for launching a projectile (12) according to claim 9, wherein:- the transfer of the axial force to the first stop (56) comprises the sliding of the second screw (32, 52) along the second rotating shaft (28), from the third position to the fourth position; and the passage of the second elastic return element (34) from the third to the fourth state of stress; and- simultaneously with the release of the first elastic return element (33), the method comprises the release of the second elastic return element (34) from the fourth to the third state of stress.
- An operating method of a projectile (12) according to one of claims 4 to 9, wherein:- each of the first (26) and second (28) rotating shafts is driven in rotation relative to the shell about the axis; and- the first (30) and second (32) screws are respectively in the first and in the third positions.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1908105A FR3098896B1 (en) | 2019-07-18 | 2019-07-18 | UNDERWATER PROJECTILE, ASSOCIATED ASSEMBLY AND LAUNCHING PROCEDURE |
PCT/EP2020/070110 WO2021009277A1 (en) | 2019-07-18 | 2020-07-16 | Underwater projectile, associated assembly and launch method |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3999800A1 EP3999800A1 (en) | 2022-05-25 |
EP3999800B1 true EP3999800B1 (en) | 2023-06-28 |
Family
ID=69157926
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20743631.2A Active EP3999800B1 (en) | 2019-07-18 | 2020-07-16 | Underwater projectile, associated assembly and launch method |
Country Status (4)
Country | Link |
---|---|
US (1) | US11761741B2 (en) |
EP (1) | EP3999800B1 (en) |
FR (1) | FR3098896B1 (en) |
WO (1) | WO2021009277A1 (en) |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1372295A (en) * | 1917-03-31 | 1921-03-22 | Westing House Electric & Mfg C | Propeller |
US3301210A (en) * | 1966-01-17 | 1967-01-31 | Jr Ernest N Oeland | Propeller assembly drive |
US4007505A (en) * | 1975-11-10 | 1977-02-15 | The United States Of America As Represented By The Secretary Of The Navy | Flexible stabilizer for underwater vehicle |
US4690085A (en) * | 1986-07-09 | 1987-09-01 | Sundstrand Corporation | Propulsion system for a torpedo with thrust compensation |
DE10106388C2 (en) | 2001-02-12 | 2002-12-12 | Infineon Technologies Ag | Circuit arrangement for providing exponential predistortion for an adjustable amplifier |
US7388145B1 (en) * | 2005-04-04 | 2008-06-17 | The United States Of America As Represented By The Secretary Of The Navy | Unmanned underwater vehicle tailcone assembly |
FR3002763B1 (en) * | 2013-03-04 | 2015-04-10 | Dcns | SHOCK ABSORPTION ELEMENT FOR A PNEUMATIC REPLACEMENT DEVICE OF A LAUNCHING DEVICE OF A VEHICLE UNDERWATER |
FR3049054B1 (en) | 2016-03-21 | 2018-04-13 | Dcns | LAUNCHER TUBE REFOULOIR FOR SHIP |
-
2019
- 2019-07-18 FR FR1908105A patent/FR3098896B1/en active Active
-
2020
- 2020-07-16 US US17/627,561 patent/US11761741B2/en active Active
- 2020-07-16 EP EP20743631.2A patent/EP3999800B1/en active Active
- 2020-07-16 WO PCT/EP2020/070110 patent/WO2021009277A1/en unknown
Also Published As
Publication number | Publication date |
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FR3098896A1 (en) | 2021-01-22 |
US20220260352A1 (en) | 2022-08-18 |
FR3098896B1 (en) | 2021-07-30 |
WO2021009277A1 (en) | 2021-01-21 |
US11761741B2 (en) | 2023-09-19 |
EP3999800A1 (en) | 2022-05-25 |
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