EP2939917A1 - Modulare foil-vorrichtung - Google Patents

Modulare foil-vorrichtung Download PDF

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Publication number
EP2939917A1
EP2939917A1 EP15001324.1A EP15001324A EP2939917A1 EP 2939917 A1 EP2939917 A1 EP 2939917A1 EP 15001324 A EP15001324 A EP 15001324A EP 2939917 A1 EP2939917 A1 EP 2939917A1
Authority
EP
European Patent Office
Prior art keywords
segment
foil
fuselage
central
rod
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
EP15001324.1A
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English (en)
French (fr)
Other versions
EP2939917B1 (de
Inventor
Raphaël SALLES
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F One
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F One
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Filing date
Publication date
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Publication of EP2939917A1 publication Critical patent/EP2939917A1/de
Application granted granted Critical
Publication of EP2939917B1 publication Critical patent/EP2939917B1/de
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B32/00—Water sports boards; Accessories therefor
    • B63B32/60—Board appendages, e.g. fins, hydrofoils or centre boards
    • B63B32/64—Adjustable, e.g. by adding sections, by removing sections or by changing orientation or profile
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B34/00—Vessels specially adapted for water sports or leisure; Body-supporting devices specially adapted for water sports or leisure
    • B63B34/26—Accessories for canoes, kayaks or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING 
    • B63B34/00—Vessels specially adapted for water sports or leisure; Body-supporting devices specially adapted for water sports or leisure
    • B63B34/40—Body-supporting structures dynamically supported by foils under water

Definitions

  • the present invention is in the field of water sports which the practitioner uses a traction force for his movements, such as the muscle energy of a human or wind energy or a vehicle or engine, namely the so-called sports " gliding ", in particular using a boat or a draft sail, preferably kitesurfing.
  • a traction force for his movements such as the muscle energy of a human or wind energy or a vehicle or engine, namely the so-called sports " gliding ", in particular using a boat or a draft sail, preferably kitesurfing.
  • the present invention will find a preferential application, but not limited to kitesurfing, but may be adapted for the practice of wakeboarding, windsurfing, windsurfing and surfing, or even kayaking.
  • the invention specifically relates to a foil device, intended to be secured and extend under the underside of a boat or a board for the practice of such a water sport.
  • foil is derived from the Anglo-Saxon term “hydrofoil”, hereinafter referred to as "foil”.
  • a foil is a wing that moves in and in contact with water, whose hydrodynamic profile transmits to its support a lift force orthogonal to the direction of movement of the board.
  • Such foil is generally provided with at least one vertically extending mast, removably attached at its upper end to the underside of the board and connected at its lower end to a wing.
  • the latter extends laterally, generally symmetrically on either side of a fuselage, relative to the plane of the mast, aligned with the longitudinal median plane of the board.
  • the wing may consist of a single element but it generally consists of at least two separate portions, anterior and posterior, to obtain lever arms and moments necessary for longitudinal stability for pitching and lateral for the roll.
  • such a foil comprises a mast at the lower end of which extends a fuselage, the assembly being shaped T inverted.
  • a front segment of the fuselage receives an anterior portion of a wing by screw-fastening from above, while a rear segment receives a rear wing portion by fastening by screwing from below.
  • An existing solution consists of a dismountable foil having a mast to which is attached a fuselage which comprises removable front and rear wings.
  • the fuselage has two ends, in the form of a half-cylinder, front and rear, respectively complementary to a front half-cylinder comprising a front wing portion and a rear half-cylinder comprising a rear wing portion.
  • the fuselage also comprises a rod ensuring longitudinal locking of the fuselage with the front and rear wing portions through each of these parts.
  • the stem comprises at each of its front and rear ends a muzzle of the fuselage.
  • the rear snout of the fuselage is fixed rigidly to the rod and the front muzzle comprises a tapping complementary to the front end of the rod itself having a thread.
  • the assembly of such a foil has a weakness mechanical maintenance of the various parts that compose it (the fuselage, the front and rear fuselage nose and the front and rear wing portions), in particular face lateral or vertical forces relative to the foil displacement vector.
  • the rod provides longitudinal locking of the foil parts but is also the only holding force of the foil assembled against the multidirectional constraints exerted by the water on the foil as a function of its displacement.
  • the fact that the fuselage is fixed to the mast over almost its entire length (except the front and rear muzzle) has the disadvantage, once dismantled, to present a bulky piece T-shaped posing problems of storage and transport.
  • the present invention aims to overcome the disadvantages of the state of the art, by proposing a modular foil, consisting of several removable elements, assembled and fixed together.
  • a feature of the invention lies in the fact that the elements, once assembled, are locked along the longitudinal axis of the fuselage of the foil, namely substantially in the direction of movement of the foil.
  • the invention provides for improving the assembly between the abutting segments, by providing interlocking by means of male and female connectors having inclined walls intended to cooperate together by sliding, imparting a guide and a centering improved thus assembled segments, limiting the game once locked.
  • the male and female connectors also allow an optimal interlocking of the segments and constitute a key to ensure that the segments are correctly positioned relative to each other.
  • the fuselage comprises a second segment carrying a second wing and being removable from the central segment, and assembly means for connecting in the longitudinal direction the central segment to the second segment, the central segment and the second segment are connected end to end by the assembly means which comprise a pair formed of a male connector and a female connector cooperating by specific interlocking, each connector being formed at the ends of the central segment. and the second segment, the male connector comprising at least one inclined wall which is complementary and adapted to cooperate with an inclined wall carried by the female connector, the inclined walls ensuring a perfect interlocking of the central segment and the second segment.
  • the contact, on the one hand, between the central segment and the first segment, and on the other hand, between the central segment and the second segment, are not realized only by the contact between the male connector and the female connector.
  • the two connected ends of the first and second segments may have their respective male connectors, while the first end and the second opposite end of the central segment may include the corresponding female connectors.
  • the locking means may comprise at least one rod extending at least in part along at least the first segment and cooperating in locking with the central segment.
  • the locking means may comprise at least one rod cooperating in insertion within a first housing formed along the first segment from a free end of the first segment opposite its connected end and to said connected end of the first segment, the rod cooperating in locking at least through the first end of said central segment with another segment of said fuselage.
  • Said locking means may comprise a single rod cooperating in insertion within a first housing formed along the first segment from a free end of the first segment opposite its connected end and to said connected end of the first segment, since its first end to its second end, said rod cooperating in lock within the connected end of said second segment.
  • the rod may have a distal end cooperating in abutment against the opposite free end of the first segment.
  • the rod may comprise at least one end thread so as to cooperate with a complementary tapping formed within the connected end of the central segment or the second segment.
  • a light of diameter slightly greater than that of the rod is formed in the center of each male and female connector, allowing the rod to cross each butted segment.
  • the male connector comprises two complementary inclined walls adapted to cooperate with two inclined walls formed at the female connector.
  • the male connector comprises four complementary inclined walls adapted to cooperate with four inclined walls formed at the female connector.
  • the present invention relates to a device 1 foil.
  • Such a foil 1 comprises at least one wing, preferentially but not limitatively at least one front wing 2 and at least one rear wing 3.
  • Each wing 2 and 3 may comprise several portions, preferably two, extending symmetrically from both sides. other, to the right and to the left, of the vertical median plane of the foil 1.
  • Each wing 2 and 3 has an aerodynamic or hydrodynamic profile, the shape of which provides lift during the displacement of the device 1.
  • the foil 1 also comprises at least one mast 4.
  • the latter extends vertically or substantially vertically.
  • said mast 4 may extend in or parallel to the longitudinal vertical median plane of said foil 1.
  • Such mast 4 may comprise several distinct branches, grouped together or separated, over all or part of its length. These branches may be straight or inclined, extending in said longitudinal vertical median plane of said foil 1.
  • Said mast 4 may be in any form, preferably a shape having an aerodynamic or hydrodynamic profile.
  • the mast 4 has an elongated shape and flattened along its width, or tapered, with a section generally spindle in section along a horizontal or substantially horizontal transverse plane.
  • This mast 4 is intended to cooperate in fixing, removably, from the underside of a watercraft, preferably a board for the practice of a water sport, as defined previously. To do this, the mast 4 is equipped in the upper part with fastening means (not shown). These means ensure the maintenance and solidarity of the foil 1 with the board, but also the transmission of the lift to lift the board during movements of the foil assembly 1 attached to the board in contact with and over the water .
  • the mast 4 is provided in the lower part of a fuselage 5.
  • the latter constitutes the fuselage of the foil 1. It extends along an axis in or parallel to the longitudinal vertical median plane of the foil 1, from the front to the rear. It generally has an elongated spindle shape, with preferentially but not limitatively a circular or ovoidal cross section.
  • the mast 4 has a length of between 600 mm and 1200 mm, preferably between 750 mm and 950 mm, preferably 880 mm.
  • the width of the mast 4 is scalable vertically, and between 70 mm and 200 mm, preferably between 80 mm and 150 mm, and preferably the width of the mast changes from 100 mm to 120 mm.
  • the width of the mast 4 in the lower part, at its attachment to the fuselage 5, is 100 mm.
  • the thickness of the mast 4 in the lower part, at its attachment with the fuselage 5, is 12 mm.
  • the fuselage 5 serves as support for the wing, from which it extends.
  • each wing 2 and 3 extends laterally, projecting, symmetrically on either side, right and left. left, relative to the longitudinal vertical median plane of the fuselage 5.
  • the fuselage 5 is divided into several segments, at least two.
  • each wing 2 and 3 is integral with a segment of the fuselage 5.
  • the fuselage segment 5 supporting each wing portion 2 and 3 consists of a single and same room.
  • the fuselage 5 comprises a central segment 6 connected to the lower part of the mast 4.
  • the mast 4 can be connected to the fuselage 5 at the central segment 6 permanently or removably.
  • the lower end of the mast 4 may be shaped and dimensioned so as to cooperate in a complementary manner with the central segment 6 of the fuselage 5. This cooperation is effected in particular by interlocking, the mast 4 forming a male part coming from insert within a female portion formed within the central segment 6, or vice versa. A specific attachment can then maintain the interlocking of these two parts.
  • the length of the central segment 6 which extends longitudinally along the fuselage 5 is between 70 mm and 360 mm and preferably between 100 mm and 200 mm.
  • the central segment 6 is not longer than twice the width of the mast 4. This feature makes it possible to reduce the space requirement and to avoid that once disassembled, the central segment 6 does not exceed the width of the mast 4 excessively.
  • the part does not have a T-shape or an L-shape which forms difficult to store or transport.
  • the length of the central segment 6 is preferably between 150 mm and 190 mm, and preferably 175 mm.
  • the section of the fuselage 5 has an ovoid section shape between 20x20 mm and 30x50 mm, and preferably 23x30 mm.
  • the segments are assembled end to end, that is to say connected together by a specific connection located at one of their ends, the end of a segment connected to another segment is called butted end.
  • the specific connection area is the only contact area between the different segments that support the wing.
  • the distal ends located opposite the segments are contiguous to each other.
  • the fuselage 5 comprises at least a first removable segment 7 secured to at least a first portion of the wing.
  • the fuselage 5 comprises a single first removable segment 7 integral with at least a first portion of the wing.
  • the fuselage 5 is divided into only two segments, for example the central segment 6 connected to the mast 4 and another segment abutting the front or rear of the central segment 6. Therefore, if the first segment removable 7 is at the front, it supports the front wing 2 and the rear wing 3 is secured to the central segment 6 which extends to the rear end of the foil 1. Conversely if the first removable segment 7 is located at the rear, then it is the rear wing 3 which is removable while the front wing 2 is fixed, secured to the central segment 6 which extends to the front end of the foil 1.
  • the latter comprises assembly means 8 at least at one end of the central segment 6 with an abutting end of the first segment 7.
  • the fuselage 5 merges with the lower part of the mast 4 on which a wing 2 is engaged by means of the assembly means 8.
  • the fuselage 5 merges with the wing 2 which is engaged by means of the assembly means 8 at the lower part of the mast 4.
  • the assembly means 8 ensure the connection of the segments 6 and 7 between them at their butted end, and their maintenance. This maintenance results in the blocking displacement of each removable segment when assembled on the central segment 6, outside the direction of nesting to assemble and disassemble the segments.
  • This interlocking direction extends along the longitudinal median axis of the fuselage 5. In other words, once assembled, the segments can not move laterally or turn relative to each other, relative to each other. at the longitudinal center line of the fuselage 5.
  • the assembly means 8 may be in the form of at least one pair consisting of a male connector 80 and a female connector 81 cooperating by interlocking. Each pair is formed at the abutting ends of the segments.
  • the interlocking connection between the male connector 80 and the female connector 81 is the only contact zone between each butted segment.
  • the specific connection between the male connector 80 and the female connector 81 contributes to maintaining the assembly of the foil 1 against the multidirectional stresses exerted by the water during the movements of the foil 1, apart from the translation stress along the longitudinal axis. of the fuselage 5, the segments of which are held by the locking means 9.
  • the male end 80 is provided projecting at the end of the removable segment, namely the first segment 7, while the female connector 81, recessed, is formed at within the adjacent end of the central segment 6.
  • the female connector 81 recessed
  • Male connectors 80 and 81 female have dimensions and complementary shapes, with the game, allowing their interlocking.
  • the male connector 80 may have a polyhedral shape, in particular pyramidal truncated, triangular, rectangular, square or polygonal, or even such a star.
  • the polygon section, with edges, ensures the locking, in particular in rotation, segments between them.
  • Two examples are schematized on the Figures 5 and 6 .
  • the male connector 80 comprises at least one inclined wall designed to cooperate with a complementary inclined wall formed at the female connector 81.
  • the male connector 80 has at least one inclined outer wall 86, decreasing from the inside to the outside of the segment.
  • This inclined outer wall 86 is intended to cooperate with an inner wall also inclined, formed in the female connector 81 of the abutting end, convergently from the outside to the inside of the adjacent segment.
  • the inclined walls slide against each other, providing improved guidance, centering and positioning of the interlocking segments, once the abutting ends assembled.
  • the interlocking of these inclined walls ensures a perfect connection between the segments.
  • the male connector 80 may have a frustoconical shape and the inclined outer wall 86 is constituted by the outer wall.
  • the female connector 81 then comprises a reverse cone frustum, of complementary dimensions, whose peripheral inner wall then forms the inclined inner wall.
  • the locking in rotation can then be effected by at least one lug 82, preferably two, projecting outwardly, at the end of the male connector 80 or at least one side, and cooperating within a hole or blind hole, arranged vis-à-vis the breast or one side of the female connector 81.
  • the male connector 80 has a truncated pyramidal shape with a rectangular base.
  • the outer faces of the truncated pyramid then each constitute an inclined outer wall 86, preferably the outer walls 86 are inclined at an angle of at least 2 ° and preferably 3 ° with respect to a vertical projection of a defined plane by a baseline of an outer face of the truncated pyramid.
  • the section of the rectangular base of the truncated pyramid has dimensions of between 12x12 mm and 25x40 mm, preferably between 15x15 mm and 25x30 mm, and preferably 18x19 mm.
  • the connection area between each segment of the fuselage 5 varies between 114 mm 2 and 1000 mm 2 , preferably between 225 mm 2 and 750 mm 2 , and preferably 340 mm 2 .
  • the preferred height of the truncated pyramid is between 30 mm and 100 mm, preferably between 40 mm and 60 mm, and preferably 50 mm.
  • edges of the truncated pyramid of the previous embodiment are rounded. These edges with the outer faces then together constitute the inclined outer walls 86.
  • the male connector 80 can be made on a hollow or tubular body of the fuselage 5. Therefore, it is in the form arches, projecting over a portion of the perimeter of the end of a segment.
  • the female connector 81 then consists of complementary notches.
  • each arc may have an inner wall 85 inclined, in a frustoconical type of curvature, intended to cooperate against a complementary outer wall provided to the corresponding female connector level 81.
  • an essential feature of the present invention lies in the locking of the assembly of the segments of the fuselage 5.
  • This interlocking interlocking segments assembled is carried out according to a component oriented along the longitudinal axis of the fuselage 5. In d In other words, the locking does not take place transversely or orthogonally, but longitudinally with respect to the fuselage 5.
  • the foil device 1 comprises locking means 9 of the first segment 7 with at least the central segment 6.
  • the locking means 9 extend along the longitudinal axis of the fuselage 5 and provide locking in at least one direction of the longitudinal axis of the fuselage 5.
  • the locking means 9 cooperate with each segment, to block their interlocking.
  • the inclined wall or walls of the connectors 80 and 81 cooperate with the locking means 9.
  • the connectors 80 and 81 participate in clamping, centering, wedging and locking the segments so as to eliminate the clearance between the segments of the fuselage 5.
  • These means 9 have a component substantially orthogonal to the median axis of the mast 4, that is to say that their horizontal or substantially horizontal component (along the longitudinal median axis of the fuselage 5) is greater than the vertical component or substantially vertical (along the longitudinal median axis of said mast 4).
  • the locking means 9 have a single and only horizontal component or substantially horizontal.
  • the fuselage 5 can be divided into three segments. According to a specific embodiment, not shown, an intermediate segment may be interposed between the central segment 6 and the first segment 7. In other words, the first segment 7 is subdivided into two.
  • the fuselage 5 comprises at least one second removable segment 10 secured to at least a second portion of the wing.
  • the fuselage 5 comprises three segments. These three segments are the front segment 7, central 6 and rear 10.
  • the second segment 10 can receive the rear wing 3 while the first segment 7 receives the front wing 2, as visible on the Figures 1 to 3 (Or vice versa).
  • the abutment of the central segment 6 and the second segment 10 is also performed by means of assembly. These are similar to the means previously described.
  • the abutting ends of the first 6 and second 10 segments have their respective male connector 80, while the first end and the second end opposite end of the central segment 6 has the corresponding female connectors 81.
  • the opposite is also possible, namely that the central segment 6 has the male connectors 80 at each end, while the segments 7 and 10 have the female connectors 81 on one of their end intended to be abutted with the central segment 6.
  • the locking means 9 allow to fix between them two segments. This locking is always performed along the longitudinal median axis of the fuselage 5.
  • the locking means 9 comprise at least one rod 11 extending at least in part along at least the first segment 7 and cooperating in lock with the central segment 6.
  • the rod 11 passes through the assembled ends of the abutting segments, to apply a clamping force in the longitudinal interlocking direction.
  • a light 87 of diameter slightly greater than that of the rod 11, is formed in the center of each male connector 80 and female 81 allowing the rod 11 to pass through each butted segment.
  • the rod has a length of between 50 mm and 400 mm, preferably between 100 mm and 350 mm, preferably 295 mm.
  • the diameter of the rod is between 5 mm and 10 mm, and preferably 6 mm.
  • this lock through the central segment 6 in its entirety, from one end to the opposite opposite.
  • the locking means 9 comprise at least one rod 11 extending from the first segment 7 to integrally cross the central segment 6, through a central housing 12, and to be inserted in the second segment 10.
  • This configuration may include two rods 11, housed at each end, on either side within the central segment 6, through one or more central housing 12, and at the level of the opposite end within housing specific to each segment, before 7 and rear 10.
  • this rod 11 can extend from the front segment 7 to the rear segment 10, or vice versa.
  • each rod 11 comprises at least one end thread so as to cooperate with a complementary tapping formed within the abutting end of the central segment 6 or the second segment 10.
  • the locking means 9 comprise at least one rod 11 cooperating in insertion within a first housing 13 formed along the first segment 7 from an opposite free end to the end abutment.
  • the rod 11 cooperates in locking at least through the first end of the central segment 6 with another of the fuselage segments 5, as the second segment 10.
  • the rod 11 is inserted and locked to the inside the first housing 13, in the form of a blind hole. It protrudes from this hole to cross the central segment inside and along its central housing 12, to open at the opposite end and lock inside the second segment 10.
  • the locking means 9 comprise a single rod 11 cooperating in insertion within a first housing 13 formed along the first segment 7 from an opposite free end to the end abutment and within a central housing 12 formed along the central segment 6 from its first end to its second end, the rod 11 cooperating in lock within the abutting end of said second segment 10.
  • the first housing 13 is through and the rod 11 is slidably introduced from one end of the first segment 7 to pass through it integrally, exit and cross integrally the central segment 6, to open and be inserted in lock in the second segment 10.
  • the rod 11 has a distal end cooperating abutting against the opposite free end of the first segment 7.
  • the first housing 13 may comprise, at its free end, an annular hook 16 intended to receive the distal end of the rod 11 at which is formed an annular ring 14. The latter then cooperates interlocking within the hook 16, limiting its travel along and inside the segments through which it passes.
  • the distal end may include a removable end tip.
  • the latter can be fixed by screwing on the annular ring 14, which then has a complementary internal thread.
  • the rod 11 may have a thread intended to cooperate with a complementary tapping formed in the farthest segment, namely the central segment 6 in the case of only two fixed segments. sets, or the second segment 10 in the case of three butted segments.
  • the rod 11 can pass through the male connectors 80 and the female connector 81, as illustrated in FIGS. Figures 5 to 8 .
  • the longitudinal housings of each segment then pass through the male connectors 80 and female 81 corresponding.
  • the various elements constituting the foil 1, namely the mast 4 and the fuselage segments 5, can be made of any type of material, preferably carbon fiber.
  • the rod 11 and its tip 15 may be made of metal, preferably stainless.
  • metal or composite inserts may be introduced into the segments, in their housing, so as to cooperate by screwing with the rod 11.
  • Disassembly of such a foil 1 is done by repeating the previous steps inversely.
  • the foil device 1 makes it possible to quickly and simply assemble the segments to form the fuselage 5, free of any adjustment or mounting error.
  • the longitudinal locking provides improved blocking of the segments between them, limiting the wear of fasteners and interlocking parts. Maintaining longitudinally locking provides a better distribution of the torques applied during use of the foil 1, offering better resistance to the mechanical stresses it undergoes and increasing its life.
  • the inclination of the pieces interlocking ensures perfect junction between segments.
  • the inner and outer wall inclination of the male 80 and female 81 connectors for assembly and interlocking, combined with longitudinal locking, ensures better connection of the segments together, improving rigidity, strength and accuracy. foil 1 according to the invention.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mutual Connection Of Rods And Tubes (AREA)
  • Toys (AREA)
  • Connection Of Plates (AREA)
EP15001324.1A 2014-04-30 2015-04-30 Modulare foil-vorrichtung Not-in-force EP2939917B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1453937A FR3020619B1 (fr) 2014-04-30 2014-04-30 Dispositif de foil modulaire

Publications (2)

Publication Number Publication Date
EP2939917A1 true EP2939917A1 (de) 2015-11-04
EP2939917B1 EP2939917B1 (de) 2017-03-01

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP15001324.1A Not-in-force EP2939917B1 (de) 2014-04-30 2015-04-30 Modulare foil-vorrichtung

Country Status (3)

Country Link
US (1) US9278739B2 (de)
EP (1) EP2939917B1 (de)
FR (1) FR3020619B1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3051433A1 (fr) * 2016-05-20 2017-11-24 Seair Dispositif de precision de calage angulaire d'aile de derive sur une coque de bateau
CN109415105A (zh) * 2016-05-17 2019-03-01 转翼有限公司 基于水翼的装置
DE202019103496U1 (de) 2019-06-25 2019-09-12 North Kiteboarding Australasia Hydrofoil zur Befestigung an einem Wassersportbrett

Families Citing this family (9)

* Cited by examiner, † Cited by third party
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US10160525B2 (en) 2016-05-17 2018-12-25 Go Foil, Inc Hydrofoil-based apparatus
US10358193B2 (en) * 2016-06-09 2019-07-23 Adherend Innovations, LLC Hydrofoil assembly for watersports and associated methods of manufacture
ES2740976B2 (es) * 2018-07-24 2021-03-29 Kookite S L Sistema de fijación rápida para componentes de hidroalas de kitesurf
DE102018124323A1 (de) * 2018-10-02 2020-04-02 Ellergon Antriebstechnik Gesellschaft M.B.H. Hydrofoil
CN109263823B (zh) * 2018-11-29 2024-05-17 深圳市苇渡智能科技有限公司 一种冲浪装置
WO2020222206A1 (en) * 2019-05-02 2020-11-05 You Tiesda Locking mechanism for modular components
SE544743C2 (en) * 2021-04-16 2022-11-01 Consat Ab Hydrofoil for windsurfing
DE202021104080U1 (de) 2021-07-30 2021-08-09 Fürstenberg Fittings UG (haftungsbeschränkt) Hydrofoil für ein Wassersportbrett
EP4276011A1 (de) 2022-05-13 2023-11-15 Scubajet GmbH Modulares unterwasser-erweiterungssystem

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4304158A1 (de) * 1993-02-12 1994-08-25 Adalbert Kefer Auftriebsfinne
US20020115363A1 (en) * 2001-02-20 2002-08-22 Michael Murphy Adjustable angled rear wing
US20050090166A1 (en) * 1999-09-23 2005-04-28 Woolley Robert C. Flying ski
US20050255764A1 (en) 2004-05-17 2005-11-17 Woolley Robert C Flying ski

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5975464A (en) * 1998-09-22 1999-11-02 Scaled Composites, Inc. Aircraft with removable structural payload module
US7497752B2 (en) * 2004-12-13 2009-03-03 John Field Fin attachment system and method
US9085343B2 (en) * 2013-03-14 2015-07-21 Hydrofoiled, Inc. Universal hydrofoil connector system and method of attachment
JP5984976B2 (ja) * 2014-02-07 2016-09-06 エレルゴン・アントリーブステヒニク・ゲゼルシヤフト・ミツト・ベシユレンクテル・ハフツングＥＬＬＥＲＧＯＮ Ａｎｔｒｉｅｂｓｔｅｃｈｎｉｋ ＧｍｂＨ ハイドロフォイル
FR3017363B1 (fr) * 2014-02-11 2017-06-23 Socarbon Aile portante pour sport nautique

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4304158A1 (de) * 1993-02-12 1994-08-25 Adalbert Kefer Auftriebsfinne
US20050090166A1 (en) * 1999-09-23 2005-04-28 Woolley Robert C. Flying ski
US20020115363A1 (en) * 2001-02-20 2002-08-22 Michael Murphy Adjustable angled rear wing
US20050255764A1 (en) 2004-05-17 2005-11-17 Woolley Robert C Flying ski

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
AHD BOARDS TV: "Hydrofoil: AFS-1 session ENG.mov", 6 April 2012 (2012-04-06), XP054975682, Retrieved from the Internet <URL:https://www.youtube.com/watch?v=aihqiBahXsU> [retrieved on 20150120] *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109415105A (zh) * 2016-05-17 2019-03-01 转翼有限公司 基于水翼的装置
FR3051433A1 (fr) * 2016-05-20 2017-11-24 Seair Dispositif de precision de calage angulaire d'aile de derive sur une coque de bateau
DE202019103496U1 (de) 2019-06-25 2019-09-12 North Kiteboarding Australasia Hydrofoil zur Befestigung an einem Wassersportbrett

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US20150314837A1 (en) 2015-11-05
US9278739B2 (en) 2016-03-08
FR3020619A1 (fr) 2015-11-06
FR3020619B1 (fr) 2018-03-16
EP2939917B1 (de) 2017-03-01

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