EP0511050B1 - Dispositif comprenant au moins un élément de forme aérodynamique à géométrie modifiable, intégrant un système de contrÔle de la couche limite - Google Patents

Dispositif comprenant au moins un élément de forme aérodynamique à géométrie modifiable, intégrant un système de contrÔle de la couche limite Download PDF

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Publication number
EP0511050B1
EP0511050B1 EP92401041A EP92401041A EP0511050B1 EP 0511050 B1 EP0511050 B1 EP 0511050B1 EP 92401041 A EP92401041 A EP 92401041A EP 92401041 A EP92401041 A EP 92401041A EP 0511050 B1 EP0511050 B1 EP 0511050B1
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EP
European Patent Office
Prior art keywords
opening
geometry
flap
aerodynamic
zone
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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.)
Expired - Lifetime
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EP92401041A
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German (de)
English (en)
French (fr)
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EP0511050A1 (fr
Inventor
Pierre Julien
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Individual
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Individual
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Publication date
Priority claimed from FR9104719A external-priority patent/FR2675461A1/fr
Priority claimed from FR9105445A external-priority patent/FR2676032A1/fr
Priority claimed from FR9108750A external-priority patent/FR2678892B1/fr
Application filed by Individual filed Critical Individual
Priority to US08/137,085 priority Critical patent/US5485799A/en
Publication of EP0511050A1 publication Critical patent/EP0511050A1/fr
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Publication of EP0511050B1 publication Critical patent/EP0511050B1/fr
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H9/00—Marine propulsion provided directly by wind power
    • B63H9/04—Marine propulsion provided directly by wind power using sails or like wind-catching surfaces
    • B63H9/06—Types of sail; Constructional features of sails; Arrangements thereof on vessels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H9/00—Marine propulsion provided directly by wind power
    • B63H9/04—Marine propulsion provided directly by wind power using sails or like wind-catching surfaces
    • B63H9/06—Types of sail; Constructional features of sails; Arrangements thereof on vessels
    • B63H9/061—Rigid sails; Aerofoil sails
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H8/00—Sail or rigging arrangements specially adapted for water sports boards, e.g. for windsurfing or kitesurfing
    • B63H8/20—Rigging arrangements involving masts, e.g. for windsurfing

Definitions

  • Device comprising at least one element of aerodynamic shape with modifiable geometry, integrating a control system of the boundary layer.
  • the present invention relates to a device comprising at least one element of aerodynamic shape, at least part or area of which is foldable, for propulsion and / or lift by the effect of the relative wind.
  • a device of this type is known in particular from WO 86/00591 GRAVELINE.
  • the invention relates to a device of the aforementioned type with large adjustable lift, which is intended for any machine which can be set in motion in the air, on water or on land, such as a boat, windsurfing board, aircraft. , flying wing, kite, sand yachting, etc.
  • the invention is also applicable to the production of models of these locomotion or sports machines.
  • LEMOIGNE proposes to provide them with nozzles which protrude strongly, on the upper surface, by harming the profile of the wing, in terms of aerodynamics.
  • MAGNI For its part US-A-1,567,531 MAGNI describes a thick wing comprising a first part in the form of a partially adjustable camber and a second part in the form of an immutable camber, pivotally mounted relative to said first part, an air passage which can be open between the two parts, the opening / closing of said passage being a function of the hollow of the wing (the importance of said pivoting) and the passage being delimited by two walls of immutable configuration belonging respectively to each of the two parts.
  • the geometry of the air passage of this device is not adjustable: it always forms a divergent, which slows the air.
  • said opening and said means for guiding said air passage are adjusted in geometry and opening / closing by means capable of acting both on the position and on the geometry of at least part and / or zone of said device and said device further comprises means adapted to adjust the geometry of said element, including at least the camber in shape and in hollow.
  • the invention differs from the prior art represented by MAGNI in that the means used by MAGNI to vary the position of the parts of its thick wing having an impact on the air passages are themselves , unable to further vary the geometry of said parts, or to vary only this geometry, while the present invention offers all these possibilities regardless of the shape of the camber of said element and its hollow.
  • US-A-2 984 199 GIEWALD describes a flexible wing with thin profile in three parts forming a sail plan whatever its orientation relative to the craft which it equips.
  • the three parts are positioned immutable by the spacing and alignment of the region of their leading edge.
  • the three parts of the GIEWALD canopy cannot participate in the adjustment of the shape of the camber because the leading edges do not have their own mobility which allows them to position themselves in an adjustable manner. one to another.
  • the air passage opening according to the invention can be both continuous and discontinuous (it is understood that this is a continuity or a discontinuity in space, not in time) .
  • the invention therefore relates to a device which comprises the element of aerodynamic shape and the means which give it its geometry, to vary its lift and its drag and, in certain cases, its orientation relative to the machine that the device team.
  • these means can act on the shape and / or on the size of its camber, of its twist, of its span, of its surface, etc.
  • the element of aerodynamic shape can be partially collapsible and / or totally.
  • the thickness can be fixed by construction and / or be given by adjustment using the positioning means.
  • the skeleton of the profile of the element of aerodynamic shape it can form a line with variable curvature and this curvature can never be zero.
  • the skeleton may have a curvature having only one concavity.
  • the creation and / or adjustment of the air passage opening (s) and the air flow guiding means are independent of the general geometry of the aerodynamically shaped element, in particular of the length of the skeleton, of its profile.
  • the aerodynamically shaped element can be in one or more parts and / or zones, integral or dissociated. mobile and / or stationary with respect to each other. It can include at least one expandable zone.
  • the position of the aerodynamically shaped element and / or of its different parts and / or zones can be adjustable relative to the machine fitted to the device to which the element belongs.
  • the aerodynamically shaped element and / or its various parts and / or zones may be of reversible concavity.
  • the shape of the skeleton of the profiles of said shape is a choice of adjustment. Deformations of the shape are possible without necessarily causing a break in curve other than that created by the open air passages, the external surface of the element retaining, depending on the setting, continuous curved lines favoring the flow of the air.
  • the positioning means act by positioning, in an adjustable manner, between themselves and / or between themselves and the machine, certain points and areas of connection between the aerodynamically shaped element and the positioning means.
  • These means can be chosen, for example, from the following elements, fixed or movable with respect to one another, the geometry of which can be variable: beam, torque, truss beam, mast, pivoting wing mast, bipod mast, tripod mast or shaped mast of L, arch, pylon, wishbone, boom, boom boom, articulated arm, outrigger, balestron, spacer, batten, rail, carriage, hoist, jack, and all the hardware, rigging part and mechanical, pneumatic control means, electro-mechanical and hydraulic known in the fields considered.
  • boom-shaped boom is meant a boom having first and second branches substantially at right angles, the first branch acting as a boom itself and the second branch, pivotally mounted on the machine fitted to the device, making support office for the first branch.
  • the positioning means can be located outside, partially inside or entirely inside the aerodynamically shaped element, or even be integrated therein.
  • These positioning means can act on the orientation of the aerodynamically shaped element by rotating it around an axis, for example around a mast.
  • the positioning means may comprise a structure comprising one or more elements comparable to a conventional boom or in the form of a gallows, to a balestron or to a wishbone, the said element or elements comprising itself or themselves at least part of variable geometric.
  • variable geometry part is meant articulated and / or sliding and / or flexible and / or extensible.
  • the aerodynamically shaped element may include pull points.
  • the pull points are connected to a spar (boom, beam, etc.), or to a mobile structure, itself connected to the machine fitted to the device according to the invention and / or itself maintained at bar l 'operator.
  • the pull points can be connected directly to said machine.
  • the connections allow the adjustments by fixing the lengths between the pulling points and the anchoring points, which can themselves be on the machine, on the spar, on an intermediate structure, with adjustable position.
  • the device is designed to adapt, among other things, to existing sailing machines by modifying them to a minimum.
  • the device comprises stays, shrouds, sheets, low haul or other elements of the positioning means and of the rigging transmitting forces, at least a part of them, of which preferably the stays and the stays, will be directly connected to the vehicle equipped with this device.
  • said leading edge can be positioned outside the longitudinal and movement axis of the machine fitted on the device according to the invention.
  • At least one pulling point is provided between the two ends of said leading edge and, a stiffening element with variable geometry, continuous or discontinuous, can preferably be fitted to said leading edge. over all or part of its length, which makes it possible to impart specific mobility to the leading edge.
  • the aforementioned stiffening element can, for example, be flexible, articulated, etc.
  • the advantage of such clean mobility is to give an optimum angle of incidence at the leading edge of the element at its different levels.
  • angle of incidence is meant the angle formed by the direction of the relative air current and the chord of the aerodynamic element, or of one of its parts or zones.
  • the stiffening element can have a shape with variable and adjustable geometry. It may for example be a strut or a reel. Thanks to such means, it is possible to obtain a variation by bending, and / or mobility of the parts of said stiffening element with variable geometry, relative to each other, the stiffening element being able to present in its longitudinal direction a curved line. and / or broken.
  • the element of aerodynamic shape is an airfoil divided into at least two parts along a dividing line and adapted to form between them a slit affecting all or part of said line, said airfoil parts generally forming a airfoil plane over the whole of which said means of positioning are suitable to act.
  • the positioning means affect both the overall sail plane and each part of the wing, taken in isolation, so that it is possible, in particular, to arch them individually.
  • said positioning means also make it possible to reduce the area or to lower each part of the airfoil.
  • two consecutive wing parts have an overlap area, said slot being defined by the spacing between said wing parts, in the overlap zone.
  • the spacing is maintained by at least one spacer.
  • USA 3053 219 COON which shows a sail divided into several parts connected by a spacer which constitutes each leg 40 ⁇ fixed to the two facing sail parts, according to the invention, at least one of the two wing parts having an overlap zone is not fixed to the spacer.
  • the spacer which can be roughly wedge-shaped and tapering upstream, can be attached to the other part of the airfoil or, when said wing is held at one end by a support which is integrated into it, such as a mast or a beam, the spacer can be fixed to this support and / or to an aerodynamic fairing of this support.
  • the spacer has a configuration and / or a modifiable position, suitable for participating in the adjustment of the spacing and / or of the geometry of the slot.
  • the two faces of the aerodynamically shaped element belong to separate envelope parts which determine between them a hollow aerodynamic volume;
  • the opening and the means for guiding the air passage are created by a pair of hatches formed respectively in one and the other faces and which are subjected to control means, acting on their closing / opening, on their orientation and their geometry, the opening of the hatch on the upper side being done by displacement of the free upstream edge of the hatch towards the inside of the cavity of the aerodynamic volume, so that the face of the envelope on the upper side retains its aerodynamic profile , despite the opening of the hatch.
  • the hatch can be opened both by moving the free downstream edge of the hatch towards the inside of the aerodynamic volume cavity and by moving the free upstream edge of the hatch towards the outside of said cavity. volume.
  • the face of the casing on the lower surface provides an aerodynamic profile for the passage of air through the opening, and for its flow over the lower surface.
  • the hatches can be flexible.
  • the hatch control means depend on a variable geometry structure housed in the cavity of the hollow aerodynamic volume.
  • This structure is subjected to adjustment means and it gives the different section or sections forming the profile or profiles of the aerodynamic volume. More specifically, said adjustment means act, in size and / or shape, on one or more of the characteristics of the geometry of the structure chosen between the camber the thickness, the twist, the span and the surface, and said structure is connected to the envelope, so that by adjusting the geometry of said structure, one controls that of the aerodynamic volume.
  • a third embodiment suitable for the propulsion of a sailing boat or for the lift of an aircraft, proceeds at the same time from the first embodiment in the sense that it applies to a thin wing , and the second embodiment in the sense that it uses hatches.
  • the aerodynamically shaped element is a wing
  • a hatch creates said opening and said means for guiding said air passage
  • which hatch is defined by a slot called “flexible” substantially perpendicular to the direction of air flow in the normal position of use and by two slots called “stiffened” substantially parallel to said direction, so that the hatch has roughly the shape of a C, the slots stiffened being due to the presence, in the airfoil, of stiffening slats running along said slots and extending beyond those of their ends opposite to said flexible slot.
  • the hatch can be subjected to control means comprising at least one so-called “control” slat integrated into said airfoil in a direction substantially parallel to the rigidified slots, said control batten preferably having at least one zone of weakened rigidity adapted to promote the flexing of said batten at this zone.
  • control batten also regulates the shape of the camber and / or the twist of said element.
  • Each hatch can be subjected to two control slats located on either side of said hatch.
  • said or one of said control slats is substantially coextensive with the lower edge of the airfoil.
  • At least one stiffening slat and at least one control slat can be contics.
  • the canopy of the first or third embodiment is held at one end by a support, such as a mast or a beam
  • said support may be located next to the sail plan or be integrated into a part of the sail plan.
  • the support can, in a manner known per se, have an aerodynamic profile, and according to the invention this aerodynamic profile can be obtained by surrounding said support, over all or part of its length, with a fairing in at least one part, fairing which is rotatably mounted around the support.
  • FIG. 1b We will first describe Figure 1b where we see four wings V1, V2, V3, V4 of the same skeleton length.
  • the wings V1 and V2 have the same ones C1, C2 and the same rope CP1, CP2.
  • the wings V2 and V3 have a different cord CP2, CP3, and a hollow C2, different C3.
  • the wings V1 and V4 have the same hollow C1, C4 and a different cord CP1, CP4. It follows that the wings V1, V2, V3 and V4 all have a camber of different shape.
  • FIG. 1 we see a monohull boat 1 provided with a mast 2 which supports a thin airfoil designated as a whole by 3, in a single part, and which is divided into three parts 3a, 3b, 3c having between them overlap zones 4ab, 4bc. These overlap zones determine between them slots 68 (FIG. 4) with adjustable geometry and which can be more or less open, or else closed.
  • the wing parts have pulling points, in particular, 5-10 ⁇ on their lower edge by means of which the various adjustments and maneuvers of the wing parts are made.
  • the frame 34 fitted with pulleys through which ends come from the pulling points 8 and 9, extends far beyond the boom 36.
  • the terminal 40 On the carriage 35 is articulated the terminal 40 which can be flexible.
  • Bomes 36.40 form a bome with variable geometry. Booms 12, 36, 40 are positioned relative to deck 33 by hoist, carriage, rail assemblies: 50-52, 47-49, 44-46. The concavity of the rail 52 is turned towards the mast 2.
  • a pull point 30 ⁇ 1 to which are fixed two ends 30 ⁇ 2, 302 'connected to the craft.
  • wing parts 3a, 3b, 3c can be controlled individually, in particular as regards their camber, their twisting, their reduction in surface area or their sprawl.
  • the airfoil P passes through the mast which is integrated into the airfoil part 3b. This situation is shown schematically in Figure 2c.
  • the mast 2 ′ could pass alongside the sail plane P.
  • one of the wing parts could be replaced by the mast as seen in Figure 2b.
  • the mast 2 would be suitably profiled to integrate into the aerodynamic shape of the rest of the wing 3a '', 3c ''.
  • spacers 63 are visible in FIGS. 3 and 4, where a flexible wing according to the invention is shown, having only two parts 3d, 3e having an overlap area 4d, e. To allow individual control of these wing parts, the spacers are fixed to only one of them. As can be seen in FIG. 4, the spacers 63 consist of a part 64 mounted at right angles to a flexible support 65, fixed to the wing part 3c, the part 64 or the junction with the support 65 being articulated.
  • the second embodiment of the invention is essentially distinguished from the first by the fact that it is the application of the invention in the case of a thick canopy.
  • Couples 120 - 124 shown according to an example fig. 7 are housed in the aerodynamic element. They regulate the geometry of it.
  • An example of a device fig. 8 controls the hatches.
  • Torque 124 is fixed a halyard to hoist or lower the wing 103. In all cases, the pair or pairs are locked against any rotation around the guide support 102.
  • the section in FIG. 7 shows how a torque can be produced, that is to say using several plates 129 to 132 arranged end to end and hinged together. More precisely, one end of the plate 129 forms the leading edge of the structure and its opposite end is articulated at 133 on the plate 130 ⁇ which has an opening 134 for the passage of the mast 10 ⁇ 2. Opposite the plate 129, the plate 130 artic is articulated at 135 on an intermediate plate 131, itself articulated at 136 on a plate 132. Opposite the articulation 136, the plate 132 forms the trailing edge of the structure.
  • the envelope absorbs differences in length due to the reversibility of the concavity, cambering and twisting. To do this, and / or serve as a reminder, the envelope advantageously has extensible and / or overlapping parts subjected to tensioning means such as 141.
  • each side of the assembly constituted by the plates 129 to 132 are arranged two flexible slats of conformation 137 which are connected to the plates by means of lugs 138 fixed to said plates and sliding in grooves provided in said slats.
  • the slats 137 are fixed to the walls 10 ⁇ 7 and 10 ⁇ 8 of the casing 10 ⁇ 9 or at least in contact with them.
  • the walls 10 ⁇ 7 and 10 ⁇ 8 are only shown diagrammatically as a fragment of a dotted line on the trailing edge side. In fact, at this level, the envelope is in two parts, one, formed by the walls 10 ⁇ 7 and 10 ⁇ 8, the other, by a wall straddling the trailing edge, the ends of one covering the end of the other.
  • Cables 139 returned to the foot of the mast, control the relative position of the plates 129 to 132 between them so that by acting on these cables, the camber of the torque formed by said plates can be modified.
  • the conformation slats 137 being dependent on said plates, they follow their movement and the casing 10 ⁇ 9 follows the shape taken by the slats.
  • the overlapping ends of the walls 10 ⁇ 7 and 10 ⁇ 8 of the envelope are subjected to the tension of tensioners 141.
  • the geometry of the aerodynamic shape is obtained by acting suitably on the length of each batten and / or on the position of each plate, taken individually or in combination, thus giving the desired shape to the profiles of the airfoil by distribution of the camber. along the skeleton of the blade according to the intensity of the general camber.
  • FIG 8 shows a way to control the hatches.
  • the wall 10 ⁇ 7 of the envelope in which are formed two hatches 111b "and 112b", the latter being only partially represented.
  • the wall 10 ⁇ 7 is shaped by means of the slats 137.
  • the hatch 111b '' generally has the shape of a C, the upper 148 and lower 149 branches of which are lined with operating slats 150 ⁇ , one end of which is flush with the vertical branch 151 of the C which defines the opening slot of the hatch.
  • the hatch 112b '' is designed in the same way but we only see its slot 152, aligned with the slot 151, and its lower operating slat 150 ⁇ .
  • the maneuvering slats 150 ⁇ serve as an anchoring point, on the one hand, to a cable 153 which connects them together and, on the other hand, to a series of parallel cables 154 perpendicular to the cable 153.
  • One end of the cable 153 is secured to a carriage 155 slidably mounted in a slide 156, which carriage 154 is itself maneuvered using a cable 157 parallel to the cables 154. It is understood that a traction exerted according to arrow F4 on cables 154 and 157 opens the hatches 111b '' and 112b '' allowing the passage of air according to arrow F2.
  • the third embodiment of the invention proceeds, as mentioned above, from the first and from the second.
  • FIG. 9 we see a boat before a hull 20 ⁇ 1 provided with a non-guyed mast 20 ⁇ 2, integrated into a wing 20 ⁇ 3 equipped with a reefing reduction system 271. It is provided, in the airfoil, a series of hatches 211a, 211b, 211c each of which has substantially the shape of a slightly oblique C. These hatches being identical, only the hatch 211a will be described.
  • the upper 248 and lower 249 branches of the C 211a slot are approximately parallel to the direction of the air flow (arrow F5) and they are fitted with stiffening slats 250 ⁇ .
  • the stiffened slots 248 and 249 are joined to a flexible slot 251a whose direction is not far from the perpendicular relative to that of the arrow F5.
  • the slots 251a-c of the hatches 211a-c are aligned and in their alignment is provided a pull point in 20 ⁇ 4.
  • the wing 20 ⁇ 3 is equipped with a series of control slats 258, on either side of each of the hatches 211a-c, and which have zones 259 weakened in terms of rigidity, so that these zones 259 create preferential deflection points of the slats 258.
  • the thickness of the slats 258 is constant but their height varies.
  • one of the slats 258 - referenced 258'- is coextensive with the lower edge of the wing 20 ⁇ 3.
  • a batten of constant section 260 ⁇ is provided at the head of the blade.
  • the flexibility of the control slats 258 and the slat 260 ⁇ allows the reversibility of the concavity and the edge changes.
  • the slats 250 ⁇ , 258 and 260 ⁇ are housed in sleeves fitted in the airfoil and participate in the adjustment of the camber and / or the twist.
  • a flexible boom 261 is articulated at 262 on the mast 20 ⁇ 2, boom which is connected to the bridge by a sheet hoist 244 and by another hoist 244 'each cooperating with a carriage 271, 272 and rail system, as shown more clearly in Figure 1 (references 44, 45, 46). It is thus possible to orient the boom relative to the hull 20 ⁇ 1 and relative to the wind.
  • the boom 261 itself serves as a support for a rail 263 on which slide two carriages 264 and 264 'connected respectively at the pulling point 267 and 20 ⁇ 4, by two sheets 266 and 266 ', so as to adjust the distance between the different pulling points of the edge of the sail relative to the tack point 270 ⁇ , and to participate in the fixing the intensity of the general arching of the blade.
  • a rope anchoring point is provided at each end 268 of the flexible slots 251a , b and, opposite, outside the hatches, in the canopy 20 ⁇ 7, a rope guide 269.
  • a series of guides are also provided.
  • the rope guides can be rings fixed to the sleeves of the slats.
  • a rope 270 ⁇ connects each anchor point 268 to the guide 269, passes through the series of guides 269a-d and is returned, from the most downstream guide 269d, to a control means. It is understood that a pull on the cables 270 ⁇ leads to close the doors.
  • the same machine can be equipped with several devices according to the invention and / or that the same device can combine different embodiments, that is to say for example, include a wing in a single part divided into two parts having a covering zone forming a slot, one and / or both parts being provided with hatches forming complementary slots.

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EP92401041A 1991-04-17 1992-04-14 Dispositif comprenant au moins un élément de forme aérodynamique à géométrie modifiable, intégrant un système de contrÔle de la couche limite Expired - Lifetime EP0511050B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US08/137,085 US5485799A (en) 1991-04-17 1992-04-14 Device with at least one variable-geometry aerodynamic member including a boundary layer control system

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
FR9104719 1991-04-17
FR9104719A FR2675461A1 (fr) 1991-04-17 1991-04-17 Dispositif aerodynamique a voile pour la propulsion par le vent.
FR9105445A FR2676032A1 (fr) 1991-05-03 1991-05-03 Dispositif aerodynamique a grande portance reglable.
FR9105445 1991-05-03
FR9108750 1991-07-11
FR9108750A FR2678892B1 (fr) 1991-07-11 1991-07-11 Dispositif aerodynamique a voile pour la propulsion par le vent.

Publications (2)

Publication Number Publication Date
EP0511050A1 EP0511050A1 (fr) 1992-10-28
EP0511050B1 true EP0511050B1 (fr) 1996-12-18

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EP92401041A Expired - Lifetime EP0511050B1 (fr) 1991-04-17 1992-04-14 Dispositif comprenant au moins un élément de forme aérodynamique à géométrie modifiable, intégrant un système de contrÔle de la couche limite

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US (2) US5485799A (da)
EP (1) EP0511050B1 (da)
AT (1) ATE146424T1 (da)
AU (1) AU1777092A (da)
CA (1) CA2108368A1 (da)
DE (1) DE69215952T2 (da)
DK (1) DK0511050T3 (da)
ES (1) ES2097890T3 (da)
WO (1) WO1992018381A2 (da)

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Publication number Priority date Publication date Assignee Title
CA2108368A1 (fr) * 1991-04-17 1992-10-29 Pierre Julien Dispositif comprenant au moins un element de forme aerodynamique a geometrie modifiable, integrant un systeme de controle de la couche limite
FR2715124B1 (fr) * 1993-12-01 1998-02-27 Arnaud Ballu Gréement pour bateau à voile.
DE19641560A1 (de) 1996-10-09 1998-04-16 Boehringer Mannheim Gmbh Monoklonale Antikörper gegen einen Komplex aus humanem ACT und einer Serinprotease
US5894807A (en) * 1997-09-18 1999-04-20 Emergency Contingency Plans, Inc. Sailboat
FR2773773B1 (fr) * 1998-01-21 2000-04-14 Arnaud Ballu Voilure a double surface pour engin a propulsion velique
US5988086A (en) * 1998-02-26 1999-11-23 Cerebral Technologies, Inc. Sailboat and methods
US5996519A (en) * 1998-02-26 1999-12-07 Cerebral Technologies, Inc. Sailboats and methods
DE10144113B4 (de) * 2001-09-08 2004-09-30 Josef Stempfle Segelmast
FR2840875A1 (fr) * 2002-06-12 2003-12-19 Frederic Barth Perfectionnement pour greement pour engin a voiles
PL220205B1 (pl) * 2010-02-08 2015-09-30 Janusz Wieczorek Osprzęt żaglowy, zwłaszcza jednostki pływającej
CN103702899B (zh) * 2011-06-08 2018-01-12 索夫特文股份有限公司 框架装置以及带有至少一个框架装置的成型帆装置
FR2988071B1 (fr) * 2012-03-13 2015-06-05 Guy Henri Alphonse Beaup Dispositif de commande et de maintien d'une voile aile destinee a la propulsion des navires
US8635966B2 (en) * 2012-03-24 2014-01-28 Helmuth G. Bachmann Laminar air flow slot venting for sails
PL2925600T3 (pl) * 2012-11-28 2019-06-28 Bray Skrzydło i jego zastosowanie
CN103332283B (zh) * 2013-07-12 2016-02-17 上海交通大学 风扇增升式风帆
DE102014103999A1 (de) 2014-03-24 2015-09-24 Softwing Sa Rahmeneinrichtung für eine Profilsegeleinrichtung und Profilsegeleinrichtung
FR3022525B1 (fr) * 2014-06-18 2017-02-17 Julien Morel Aile pour la propulsion d'un engin
EP3218258A4 (en) * 2014-11-14 2018-08-08 Lamberg, Vemund Adjustable sail and a vessel comprising such a sail
DE102016109564A1 (de) 2016-05-24 2017-11-30 Softwing Sa Verstellbare Rahmeneinrichtung für eine Profilsegeleinrichtung und verstellbare Profilsegeleinrichtung
FR3054139B1 (fr) * 2016-07-19 2018-07-13 Mx Production Dispositif de commande et de controle pour voile de voilier ou de planche a voile ou aile de cerf volant
US20180127075A1 (en) 2016-10-15 2018-05-10 Alistair JOHNSON Tig rig sail system
FR3058386B1 (fr) 2016-11-08 2019-06-28 Ayro Navire a propulsion velique.
US10040529B1 (en) * 2017-07-25 2018-08-07 Steven J. Salani Simplified sailing rig
EP3891063A1 (en) 2018-12-06 2021-10-13 Ayro Ship with sail propulsion

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1567531A (en) * 1923-03-24 1925-12-29 Magni Piero Variable fluido-dynamic wings such as for aeroplanes
US2373089A (en) * 1940-11-02 1945-04-10 Boeing Aircraft Co Stall delaying and indicating mechanism
US2984199A (en) * 1958-01-22 1961-05-16 Walter E Giewald Multi-sail structure
US3053219A (en) * 1961-03-06 1962-09-11 Harold W Coon Sail construction
FR1523172A (fr) * 1966-11-18 1968-05-03 Dispositifs pour l'amélioration de l'écoulement de l'air sur les surfaces soumises à un vent relatif
US3598075A (en) * 1970-02-13 1971-08-10 Clarence E Kenney Sailboat airfoil sail and mast assembly
IT1018417B (it) * 1974-03-08 1977-09-30 Corbellini G Vela a lamelle per imbarcazioni
WO1981002144A1 (fr) * 1980-02-01 1981-08-06 M Rifflart Propulseur velique sur plateau orientable
FR2567098B1 (fr) * 1984-07-05 1987-07-10 Graveline Jean Dispositif aerodynamique a concavite reversible, souple et affalable, pour la propulsion par la force du vent
JPS6328790A (ja) * 1986-07-21 1988-02-06 Mitsubishi Heavy Ind Ltd ロ−タおよびフラツプ付き剛体帆装置
FI881537A (fi) * 1988-03-31 1989-10-01 Hollming Oy Flerdelad vinge.
FR2644752A1 (fr) * 1989-03-21 1990-09-28 Belliard Yvon Greement de navire ou d'engin equivalent
CA2108368A1 (fr) * 1991-04-17 1992-10-29 Pierre Julien Dispositif comprenant au moins un element de forme aerodynamique a geometrie modifiable, integrant un systeme de controle de la couche limite

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WO1992018381A2 (fr) 1992-10-29
ES2097890T3 (es) 1997-04-16
DE69215952T2 (de) 1997-09-11
US5485799A (en) 1996-01-23
ATE146424T1 (de) 1997-01-15
US5603276A (en) 1997-02-18
DE69215952D1 (de) 1997-01-30
EP0511050A1 (fr) 1992-10-28
WO1992018381A3 (fr) 1992-12-23
DK0511050T3 (da) 1997-06-09
AU1777092A (en) 1992-11-17
CA2108368A1 (fr) 1992-10-29

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