EP0511050B1 - Device with at least one aerodynamically shaped element with changeable geometry, incorporating a control system of the boundary layer - Google Patents

Device with at least one aerodynamically shaped element with changeable geometry, incorporating a control system of the boundary layer 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
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.)
Expired - Lifetime
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EP92401041A
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German (de)
French (fr)
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EP0511050A1 (en
Inventor
Pierre Julien
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Individual
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Individual
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Priority claimed from FR9104719A external-priority patent/FR2675461A1/en
Priority claimed from FR9105445A external-priority patent/FR2676032A1/en
Priority claimed from FR9108750A external-priority patent/FR2678892B1/en
Application filed by Individual filed Critical Individual
Priority to US08/137,085 priority Critical patent/US5485799A/en
Publication of EP0511050A1 publication Critical patent/EP0511050A1/en
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Publication of EP0511050B1 publication Critical patent/EP0511050B1/en
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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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Abstract

The element (3) may be a set of sails (3), for example, having at least one aperture (68) for creating an air passage from the windward face to the leeward face and guidance means (4ab, 4bc) for directing the air emerging from the said aperture, on the leeward side, and giving it a direction tangential to the said element. According to the invention, the aperture (68) and the said guidance means (4ab, 4bc) are created temporarily and adjusted by changing the position and/or the geometry of at least a part and/or an area (3a,3b; 3b,3c) of the said device, and the device furthermore comprises means (5-10, 12, 36, 40, 51, 48, 45) suitable for adjusting the geometry of the said element, at least in terms of the shape and concavity of the camber. <IMAGE>

Description

Dispositif comprenant au moins un élément de forme aérodynamique à géométrie modifiable, intégrant un système de contrôle de la couche limite.Device comprising at least one element of aerodynamic shape with modifiable geometry, integrating a control system of the boundary layer.

La présente invention concerne un dispositif comprenant au moins un élément de forme aérodynamique, dont au moins une partie ou zone est repliable, pour la propulsion et/ou la sustentation par l'effet du vent relatif. Un dispositif de ce type est connu notamment d'après WO 86/00591 GRAVELINE.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.

Plus précisément, l'invention concerne un dispositif du type précité à grande portance réglable, qui est destiné à tout engin pouvant être mis en mouvement dans l'air, sur l'eau ou sur terre, tel que bateau, planche à voile, aéronef, aile volante, cerf-volant, char à voile, etc. L'invention est également applicable à la réalisation de maquettes de ces engins de locomotion ou de sport.More specifically, 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.

Avant d'aller plus loin, pour la bonne compréhension de l'art antérieur et de l'invention, on définira le sens d'expressions utilisées dans la présente description et dans les revendications :

  • . intrados : (I - figure 1b) face de l'élément de forme aérodynamique en surpression (autrement dit, face de l'élément qui reçoit le vent) ;
  • . extrados : (E - figure 1b) face de l'élément de forme aérodynamique en dépression ;
  • . bord d'attaque : (BA - figure 1b) point, ligne, région le plus en amont de l'élément de forme aérodynamique, ou d'une de ses parties ou zones, vu dans le sens du déplacement relatif de l'air par rapport audit élément ;
  • . bord de fuite : (BF - figure 1b) point, ligne, région le plus en aval de l'élément de forme aérodynamique, ou d'une de ses parties ou zones, vu dans le sens du déplacement relatif de l'air par rapport audit élément ;
  • . profil : forme d'une section de l'élément de forme aérodynamique prise suivant la direction de l'écoulement de l'air ;
  • . squelette d'un profil : ligne reliant le bord d'attaque au bord de fuite et passant entre l'intrados et l'extrados et à égale distance de ceux-ci;
  • . corde d'un profil : (CP - figure 1b) ligne droite reliant le bord d'attaque au bord de fuite ;
  • . creux d'un profil : (C - figure 1b) distance maximum entre la corde et le squelette d'un profil.
  • . point de tire : point de liaison pouvant servir de commande mobile ou de fixation.
Before going further, for the proper understanding of the prior art and of the invention, the meaning of expressions used in the present description and in the claims will be defined:
  • . lower surface: (I - Figure 1b) face of the aerodynamically shaped element under pressure (in other words, face of the element which receives the wind);
  • . upper surface: (E - Figure 1b) face of the aerodynamically shaped element in depression;
  • . leading edge: (BA - Figure 1b) point, line, region most upstream of the aerodynamically shaped element, or of one of its parts or zones, seen in the direction of relative movement of the air by report to said item;
  • . trailing edge: (BF - figure 1b) point, line, region furthest downstream from the aerodynamically shaped element, or from one of its parts or zones, seen in the direction of relative movement of the air with respect said element;
  • . profile: shape of a section of the aerodynamically shaped element taken in the direction of the air flow;
  • . skeleton of a profile: line connecting the leading edge to the trailing edge and passing between the lower and upper surfaces and equidistant from them;
  • . chord of a profile: (CP - figure 1b) straight line connecting the leading edge to the trailing edge;
  • . hollow of a profile: (C - figure 1b) maximum distance between the rope and the skeleton of a profile.
  • . pull point: link point that can be used as a mobile control or attachment.

Dans les dispositifs du type précité dans lesquels ledit élément a deux faces adaptées à se trouver respectivement côté intrados et côté extrados et dont un exemple est représenté par GRAVELINE, la couche limite de l'écoulement de l'air, côté extrados a tendance à "décoller" de l'élément dans la région de la ligne de plus grand creux, quand celui-ci atteint une certaine importance. Le décollement de l'écoulement limite, et même diminue, les performances aérodynamiques. Pour remédier à cette situation, il a été proposé, par exemple dans DE-1 531 328 LEMOIGNE, de prévoir au moins une ouverture pour établir un passage d'air depuis la face côté intrados vers la face côté extrados, et des moyens de guidage pour diriger l'air émergeant de ladite ouverture, côté extrados, et lui donner une direction tangentielle audit élément.In devices of the aforementioned type in which said element has two faces adapted to be located respectively on the lower side and on the upper side and an example of which is represented by GRAVELINE, the boundary layer of the air flow, on the upper side tends to " take off "from the element in the region of the deepest hollow line, when it reaches a certain importance. The separation of the flow limits, and even decreases, the aerodynamic performance. To remedy this situation, it has been proposed, for example in DE-1,531,328 LEMOIGNE, to provide at least one opening to establish an air passage from the face on the lower side to the side on the upper side, and guide means to direct the air emerging from said opening, on the upper side, and give it a tangential direction to said element.

En autorisant un passage d'air de l'intrados à l'extrados, on réinjecte de l'air en survitesse par rapport à celle de la couche limite qui, ainsi réactivée, suit la forme aérodynamique de l'élément.By authorizing a passage of air from the lower surface to the upper surface, air is reinjected at overspeed relative to that of the boundary layer which, thus reactivated, follows the aerodynamic shape of the element.

Lorsqu'il s'agit de voiles minces, LEMOIGNE propose de les munir de tuyères qui font fortement saillie, côté extrados, en nuisant au profil de la voilure, sur le plan de l'aérodynamisme.When it comes to thin sails, 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.

De son côté US-A-1 567 531 MAGNI décrit une aile épaisse comprenant une première partie à forme de cambrure partiellement réglable et une deuxième partie à forme de cambrure immuable, montée pivotante par rapport à ladite première partie, un passage d'air pouvant être ouvert entre les deux parties, l'ouverture/fermeture dudit passage étant fonction du creux de l'aile (de l'importance dudit pivotement) et le passage étant délimité par deux parois de configuration immuable appartenant respectivement à chacune des deux parties. La géométrie du passage d'air de ce dispositif n'est pas réglable : elle forme toujours un divergent, ce qui ralentit l'air.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.

La présente invention a pour but de proposer un élément aerodynamique à géometrie variable équipé de moyens qui améliorent l'écoulement de l'air de l'intrados à l'extrados, de telle sorte que l'air débouche sur l'extrados en un courant de mêmes direction et sens que ceux de l'écoulement général de l'extrados à l'endroit de jonction dudit courant et dudit écoulement général, et ce :

  • tout en conservant à l'élément sa forme aérodynamique (c'est-à-dire sans décrochement, sans creux ni obstacle qui, entre autres, forme déflecteur), même lorsque le passage de l'air ne se fait pas, quand l'élément aérodynamique est peu cambré, par exemple,
  • et en appliquant un principe qui convient à tout élément de forme aérodynamique, notamment aussi bien aux voilures minces qu'aux voilures épaisses.
The object of the present invention is to propose an aerodynamic element with variable geometry equipped with means which improve the flow of air from the lower surface to the upper surface, so that the air opens onto the upper surface in a current. of the same direction and direction as those of the general flow of the upper surface at the junction of said current and said general flow, and this:
  • while retaining the element its aerodynamic shape (that is to say without a drop, without hollow or obstacle which, among other things, deflector shape), even when the passage of air is not done, when the aerodynamic element is slightly arched, for example,
  • and by applying a principle which is suitable for any element of aerodynamic shape, in particular as well for thin wings as for thick wings.

Ce but est atteint en ce sens que, dans le dispositif selon l'invention, ladite ouverture et lesdits moyens de guidage dudit passage d'air sont réglés en géométrie et ouverture/fermeture par des moyens capables d'agir tant sur la position que sur la géométrie d'au moins une partie et/ou zone dudit dispositif et ledit dispositif comprend, en outre, des moyens adaptés à régler la géométrie dudit élément, dont au moins la cambrure en forme et en creux.This object is achieved in the sense that, in the device according to the invention, 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.

On comprend que l'invention se distingue de l'art antérieur que représente MAGNI en ce sens que les moyens mis en oeuvre par MAGNI pour faire varier la position des parties de son aile épaisse ayant une incidence sur les passages d'air sont, eux, incapables de faire varier en outre la géométrie desdites parties, ou de ne faire varier que cette géométrie, alors que la présente invention offre toutes ces possibilités indépendamment de la forme de la cambrure dudit élément et de son creux.We understand that 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 décrit une voilure souple à profil mince en trois parties formant un plan de voilure quelle que soit son orientation par rapport à l'engin qu'elle équipe. Les trois parties sont positionnées d'une manière immuable par l'espacement et l'alignement de la région de leur bord d'attaque. A la différence de la présente invention, les trois parties de la voilure GIEWALD ne peuvent participer au réglage de la forme de la cambrure car les bords d'attaque n'ont pas de mobilité propre qui leur permette de se positionner d'une manière réglable les uns par rapport aux autres.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. Unlike the present invention, 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.

L'ouverture de passage d'air selon l'invention peut aussi bien être continue que discontinue (il est bien entendu qu'il s'agit ici d'une continuité ou d'une discontinuité dans l'espace, pas dans le temps).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) .

L'invention porte donc sur un dispositif qui comprend l'élément de forme aérodynamique et les moyens qui lui donnent sa géométrie, pour faire varier sa portance et sa traînée et, dans certains cas, son orientation par rapport à l'engin que le dispositif équipe. A cet effet, ces moyens peuvent agir sur la forme et/ou sur l'importance de sa cambrure, de son vrillage, de son envergure, de sa surface... Ainsi, l'élément de forme aérodynamique peut être affalable partiellement et/ou totalement.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. To this end, 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. Thus, the element of aerodynamic shape can be partially collapsible and / or totally.

L'épaisseur peut être fixée par construction et/ou être donnée par réglage grâce aux moyens de positionnement.The thickness can be fixed by construction and / or be given by adjustment using the positioning means.

En ce qui concerne le squelette du profil de l'élément de forme aérodynamique, il peut former une ligne à courbure variable et cette courbure peut n'être jamais nulle. Le squelette peut avoir une courbure ne présentant qu'une seule concavité.As regards 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.

Sans système approprié, la création et/ou le réglage de la ou des ouvertures de passage d'air et des moyens de guigade du courant d'air sont indépendants ce la géométrie générale de l'élément de forme aérodynamique, notamment, de la longueur du squelette, de son profil.Without an appropriate system, 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.

L'élément de forme aérodynamique peut être en une ou plusieurs parties et/ou zones, solidaires ou dissociées. mobiles et/ou immobiles les unes par rapport aux autres. Il peut comporter au moins une zone extensible. La position de l'élément de forme aérodynamique et/ou de ses différentes parties et/ou zones peut être réglable par rapport à l'engin qu'équipe le dispositif auquel appartient l'élément.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.

L'élément de forme aérodynamique et/ou ses différentes parties et/ou zones peuvent être à concavité réversible.The aerodynamically shaped element and / or its various parts and / or zones may be of reversible concavity.

La forme du squelette des profils de ladite forme est un choix de réglage. Les déformations de la forme sont possibles sans engendrer forcément de rupture de courbe autre que celle créée par les passages d'air ouverts, la surface extérieure de l'élément conservant, suivant le réglage, des lignes courbes continues favorisant l'écoulement de l'air.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.

Les moyens de positionnement agissent en positionnant, d'une manière réglable, entre eux-mêmes et/ou entre eux-mêmes et l'engin, certains points et zones de liaison entre l'élément de forme aérodynamique et les moyens de positionnement. Ces moyens peuvent être choisis par exemple entre les éléments suivants, fixes ou mobiles les uns par rapport aux autres dont la géométrie peut être évolutive : poutre, couple, poutre treillis, mât, mât aile pivotant, mât bipode, mât tripode ou mât en forme de L, arceau, pylone, wishbone, bôme, bôme potence, bras articulé, tangon, balestron, entretoise, latte, rail, chariot, palan, vérin, et tout l'acastillage, partie de gréement et moyen de commande mécanique, pneumatique, électro-mécanique et hydraulique connu dans les domaines considérés.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.

Par bôme en forme de potence, on entend une bôme ayant une première et une deuxième branches sensiblement à angle droit, la première branche faisant office de bôme proprement dite et la deuxième branche, montée pivotante sur l'engin qu'équipe le dispositif, faisant office de support pour la première branche.By 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.

Les moyens de positionnement peuvent être situés à l'extérieur, partiellement à l'intérieur ou entièrement à l'intérieur de l'élément de forme aérodynamique, ou encore lui être intégrés.The positioning means can be located outside, partially inside or entirely inside the aerodynamically shaped element, or even be integrated therein.

Ces moyens de positionnement peuvent agir sur l'orientation de l'élément de forme aérodynamique en le faisant pivoter autour d'un axe, par exemple autour d'un mât.These positioning means can act on the orientation of the aerodynamically shaped element by rotating it around an axis, for example around a mast.

Pour résumer, les moyens de positionnement peuvent comprendre une structure comportant un ou plusieurs éléments assimilables à une bôme classique ou en forme de potence, à un balestron ou à un wishbone, le ou lesdits élément(s) comprenant lui-même ou eux-mêmes au moins une partie à géométric variable.To summarize, 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.

Par partie à géométrie variable, on entend articulée et/ou coulissante et/ou flexible et/ou extensible.By variable geometry part is meant articulated and / or sliding and / or flexible and / or extensible.

L'élément de forme aérodynamique peut comporter des points de tire.The aerodynamically shaped element may include pull points.

Les points de tire sont reliés à un espar (bôme, poutre, etc.), ou à une structure mobile, lui-même relié à l'engin qu'équipe le dispositif selon l'invention et/ou lui-même maintenu bar l'opérateur. En variante, les points de tire peuvent être reliés directement audit engin. Les liaisons permettent les réglages en fixant les longueurs entre les points de tire et les points d'ancrage, pouvant eux-mêmes être sur l'engin, sur l'espar, sur une structure intermédiaire, à position réglable.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. Alternatively, 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.

Le dispositif est concu pour s'adapter, entre autres, sur les engins à voile existants en les modifiant un minimum. Ainsi, si le dispositif comporte des étais, haubans, écoutes, hale bas ou autres éléments des moyens de positionnement et du gréement transmettant des efforts, au moins une partie d'entre eux, dont de préférence les étais et les haubans, sera reliée directement à l'engin équipé du présent dispositif.The device is designed to adapt, among other things, to existing sailing machines by modifying them to a minimum. Thus, if 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.

Lorsque ledit élément a un bord d'attaque et un bord de fuite, et dans certaines configurations, ledit bord d'attaque peut être positionné en dehors de l'axe longitudinal et de déplacement de l'engin qu'équipe le dispositif selon l'invention.When said element has a leading edge and a trailing edge, and in certain configurations, said leading edge can be positioned outside the longitudinal and movement axis of the machine fitted on the device according to the invention.

Il est prévu avantageusement au moins un point de tire entre les deux extrémités dudit bord d'attaque et, un élément raidisseur à géométrie variable, continu ou discontinu, peut de préférence équiper ledit bord d'attaque sur tout ou partie de sa longueur, ce qui permet de conférer une mobilité propre au bord d'attaque.Advantageously, 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.

On notera qu'aucun des documents antérieurs précités ne prévoit de moyens permettant de donner une mobilité propre à un bord d'attaque. En particulier, la structure décrite par GRAVELINE comporte un bord d'attaque de géométrie fixe résultant de la forme des pièces 3 déterminée par construction.It will be noted that none of the aforementioned prior documents provides for means making it possible to provide mobility specific to a leading edge. In particular, the structure described by GRAVELINE comprises a leading edge of fixed geometry resulting from the shape of the parts 3 determined by construction.

L'élément raidisseur précité peut, par exemple, être flexible, articulé, etc.The aforementioned stiffening element can, for example, be flexible, articulated, etc.

Une telle mobilité propre a pour intérêt de donner un angle d'incidence optimum au bord d'attaque de l'élément à ses différents niveaux. Par angle d'incidence, on entend l'angle formé par la direction du courant d'air relatif et la corde de l'élément aérodynamique, ou de l'une de ses parties ou zones. L'élément raidisseur peut avoir une forme à géométrie variable et réglable. Il peut s'agir par exemple d'un étais ou d'un enrouleur. Grâce à de tels moyens, il est possible d'obtenir une variation par flexion, et/ou mobilité des parties dudit élément raidisseur à géométrie variable, les unes par rapport aux autres, l'élément raidisseur pouvant présenter suivant son sens longitudinal une ligne courbe et/ou brisée.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. By 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.

Chaque bord d'attaque des différentes parties et/ou zones peut bénéficier des mêmes moyens leur donnant une mobilité propre.Each leading edge of the different parts and / or zones can benefit from the same means giving them their own mobility.

Dans une première forme d'exécution possible de l'invention, adaptée à la propulsion d'un bateau à voile, mais pouvant aussi servir à la sustentation, l'élément de forme aérodynamique est une voilure divisée en au moins deux parties selon une ligne de division et adaptées à former entre elles une fente affectant tout ou partie de ladite ligne, lesdites parties de voilure formant globalement un plan de voilure sur l'ensemble duquel lesdits moyens de positionnement sont adaptés à agir.In a first possible embodiment of the invention, suitable for propelling a sailing boat, but which can also be used for lifting, 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.

Selon l'invention, les moyens de positionnement affectent aussi bien le plan de voilure dans son ensemble que chaque partie de la voilure, prise isolément, de sorte qu'il est possible, en particulier, de les cambrer individuellement. Dans certains cas, lesdits moyens de positionnement permettent en outre de réduire en surface ou d'affaler chaque partie de voilure.According to the invention, 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. In certain cases, said positioning means also make it possible to reduce the area or to lower each part of the airfoil.

Dans un cas particulier de la première forme d'exécution, deux parties consécutives de voilure ont une zone de recouvrement, ladite fente étant définie par l'espacement entre lesdites parties de voilure, dans la zone de recouvrement.In a particular case of the first embodiment, two consecutive wing parts have an overlap area, said slot being defined by the spacing between said wing parts, in the overlap zone.

Un tel recouvrement peut également se faire dans le cas où la fente est discontinue.Such recovery can also be done in the case where the slot is discontinuous.

D'une manière connue en soi, pour éviter que les parties de voilure ne viennent coller l'une à l'autre dans la zone de recouvrement à un moment où l'on désire que la fente soit ouverte, l'espacement est maintenu par au moins un espaceur. A la différence de l'art antérieur, tel que représenté par USA 3053 219 COON par exemple, qui montre une voile divisée en plusieurs parties reliées par un espaceur que constitue chaque patte 40̸ fixée aux deux parties de voile en vis-à-vis, selon l'invention, l'une au moins des deux parties de voilure ayant une zone de recouvrement n'est pas fixée à l'espaceur. L'espaceur, qui peut être grossièrement en forme de coin allant en s'amincissant vers l'amont, peut être fixé à l'autre partie de voilure ou, lorsque ladite voilure est maintenue à une extrémité par un support qui lui est intégré, tel qu'un mât ou une poutre, l'espaceur peut être fixé à ce support et/ou à un carénage aérodynamique de ce support.In a manner known per se, to prevent the blade parts from sticking to each other in the overlap zone at a time when it is desired that the slot is open, the spacing is maintained by at least one spacer. Unlike the prior art, as represented by USA 3053 219 COON for example, which shows a sail divided into several parts connected by a spacer which constitutes each leg 40̸ 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.

De préférence, l'espaceur a une configuration et/ou une position modifiable, propre à participer au réglage de l'espacement et/ou de la géométrie de la fente.Preferably, 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.

Dans une seconde forme d'exécution de l'invention, adaptée à la propulsion d'un bateau à voile ou à servir de plan portant à un aéronef, les deux faces de l'élément de forme aérodynamique appartiennent à des parties d'enveloppe distinctes qui déterminent entre elles un volume aérodynamique creux ; l'ouverture et les moyens de guidage du passage d'air sont créés par une paire de trappes ménagées respectivement dans l'une et l'autre faces et qui sont soumises à des moyens de contrôle, agissant sur leur fermeture/ouverture, sur leur orientation et leur géométrie, l'ouverture de la trappe côté extrados se faisant par déplacement du bord libre amont de la trappe vers l'intérieur de la cavité du volume aérodynamique, de sorte que la face de l'enveloppe côté extrados conserve son profil aérodynamique, en dépit de l'ouverture de la trappe.In a second embodiment of the invention, adapted to the propulsion of a sailing boat or to serve as a plane carrying an aircraft, 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.

Côté intrados, l'ouverture de la trappe peut se faire aussi bien par déplacement du bord libre aval de la trappe vers l'intérieur de la cavité du volume aérodynamique que par déplacement du bord libre amont de la trappe vers l'extérieur de ladite cavité du volume. Dans les deux cas, la face de l'enveloppe côté intrados offre un profil aérodynamique au passage d'air par l'ouverture, et à son écoulement sur l'intrados.On the pressure side, 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. In both cases, 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.

Les trappes peuvent être flexibles.The hatches can be flexible.

Les moyens de contrôle des trappes dépendent d'une structure à géométrie variable logée dans la cavité du volume aérodynamique creux.The hatch control means depend on a variable geometry structure housed in the cavity of the hollow aerodynamic volume.

Cette structure est soumise à des moyens de réglage et elle donne la ou les différentes sections formant le ou les profils du volume aérodynamique. Plus précisément, lesdits moyens de réglage agissent, en grandeur et/ou forme, sur une ou plusieurs des caractéristiques de la géométrie de la structure choisies entre la cambrure l'épaisseur, le vrillage, l'envergure et la surface, et ladite structure est reliée à l'enveloppe, de sorte qu'en réglant la géométrie de ladite structure, on commande celle du volume aérodynamique.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.

Une troisième forme d'exécution, convenant à la propulsion d'un bateau à voile ou à la sustentation d'un aéronef, procède à la fois de la première forme d'exécution en ce sens qu'elle s'applique à une voilure mince, et de la deuxième forme d'exécution en ce sens qu'elle utilise des trappes.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.

Plus précisément, selon cette troisième forme d'exécution, l'élément de forme aérodynamique est une voilure, et une trappe crée ladite ouverture et lesdits moyens de guidage dudit passage d'air, laquelle trappe est définie par une fente dite "souple" sensiblement perpendiculaire à la direction d'écoulement de l'air en position normale d'utilisation et par deux fentes dites "rigidifiées" sensiblement parallèles à ladite direction, de sorte que la trappe a grossièrement la forme d'un C, les fentes rigidifiées l'étant du fait de la présence, dans la voilure, de lattes de rigidification longeant lesdites fentes et se prolongeant au-delà de celles de leurs extrémités opposées à ladite fente souple.More specifically, according to this third embodiment, the aerodynamically shaped element is a wing, and 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.

La trappe peut être soumise à des moyens de contrôle comprenant au moins une latte dite "de commande" intégrée à ladite voilure selon une direction sensiblement parallèle aux fentes rigidifiées, ladite latte de commande présentant, de préférence, au moins une zone de rigidité affaiblie adaptée à favoriser la flexion de ladite latte au niveau de cette zone.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.

De préférence, la latte de commande règle également la forme de la cambrure et/ou du vrillage dudit élément.Preferably, the control batten also regulates the shape of the camber and / or the twist of said element.

Chaque trappe peut être soumise à deux lattes de commande situées de part et d'autre de ladite trappe.Each hatch can be subjected to two control slats located on either side of said hatch.

De préférence, ladite ou l'une desdites lattes de commande est sensiblement coextensive au bord inférieur de la voilure.Preferably, said or one of said control slats is substantially coextensive with the lower edge of the airfoil.

Au moins une latte de rigidification et au moins une latte de commande peuvent être contiques.At least one stiffening slat and at least one control slat can be contics.

Il peut être avantageux qu'une ou des trappes soi(en)t pourvue(s), en outre, de moyens de manoeuvre agissant directement sur sa ou leur position.It may be advantageous for one or more hatches to be provided, in addition, with maneuvering means acting directly on its or their position.

Dans le cas où la voilure de la première ou troisième forme d'exécution est maintenue à une extrémité par un support, tel qu'un mât ou une poutre, ledit support peut être situé à côté du plan de voilure ou être intégré à une partie du plan de voilure. Toujours dans ce même cas, le support peut, d'une manière connue en soi, avoir un profil aérodynamique, et selon l'invention ce profil aérodynamique peut être obtenu en entourant ledit support, sur tout ou partie de sa longueur, d'un carénage en au moins une partie, carénage qui est monté rotatif autour du support.In the case where 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. Still in this same case, 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.

L'invention est décrite en détail ci-après par référence aux dessins annexés dans lesquels :

  • la figure 1 est une vue d'ensemble en perspective cavalière, d'une embarcation munie du dispositif selon l'invention, dans sa première forme d'exécution,
  • la figure 1a est une zone à plus grande échelle de la figure 1,
  • la figure 1b est un schéma illustrant les notions de forme et de creux d'une cambrure et celle de profil,
  • les figures 2a, 2b et 2c sont des représentations schématiques de trois positions possibles du mât par rapport aux parties de voilure,
  • les figures 3 et 4 illustrent la position et la manoeuvre d'espaceurs agissant dans la zone de recouvrement de deux parties de voilure,
  • la figure 5 est une vue d'ensemble, en élévation, d'une embarcation munie du dispositif selon l'invention, dans sa deuxième forme d'exécution,
  • la figure 6 est une coupe prise selon la ligne VIII-VIII de la figure 5, avec omission de la structure interne,
  • la figure 10̸ est une coupe, prise selon la ligne VIII-VIII de la figure 5,
  • la figure 8 est une vue de détail, à plus grande échelle et en perspective cavalière, montrant l'articulation d'une trappe,
  • la figure 9 est une vue d'ensemble, en élévation, d'une embarcation munie du dispositif, selon l'invention, dans sa troisième forme d'exécution,
  • la figure 10 est une représentation schématique, en coupe, d'un mode d'ouverture d'une trappe de la figure 9, et
  • la figure 11 est une vue de détail, à plus grande échelle, montrant des moyens de manoeuvre directe d'une trappe du dispositif selon la figure 9.
The invention is described in detail below with reference to the accompanying drawings in which:
  • FIG. 1 is an overall perspective view of a boat provided with the device according to the invention, in its first embodiment,
  • FIG. 1a is an area on a larger scale of FIG. 1,
  • FIG. 1b is a diagram illustrating the notions of shape and hollow of a camber and that of profile,
  • FIGS. 2a, 2b and 2c are schematic representations of three possible positions of the mast relative to the wing parts,
  • FIGS. 3 and 4 illustrate the position and the operation of spacers acting in the area of overlap of two wing parts,
  • FIG. 5 is an overall view, in elevation, of a boat provided with the device according to the invention, in its second embodiment,
  • FIG. 6 is a section taken on the line VIII-VIII of FIG. 5, with the omission of the internal structure,
  • FIG. 10̸ is a section taken on line VIII-VIII of FIG. 5,
  • FIG. 8 is a detail view, on a larger scale and in perspective, showing the articulation of a hatch,
  • FIG. 9 is an overall view, in elevation, of a boat provided with the device, according to the invention, in its third embodiment,
  • FIG. 10 is a schematic representation, in section, of a method of opening a hatch in FIG. 9, and
  • FIG. 11 is a detail view, on a larger scale, showing means for direct operation of a hatch of the device according to FIG. 9.

On décrira tout d'abord la figure 1b où l'on voit quatre voilures V1, V2, V3, V4 de même longueur de squelette. Les voilures V1 et V2 ont le même ceux C1, C2 et une même corde CP1, CP2. Les voilures V2 et V3 ont Une corde différente CP2, CP3, et un creux C2, C3 différent. Les voilures V1 et V4 ont le même creux C1, C4 et une corde différente CP1, CP4. Il s'ensuit que les voilures V1, V2, V3 et V4 ont toutes une cambrure de forme différente.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.

Si l'on se réfère à la figure 1 et à son détail agrandi de la figure la, on voit une embarcation monocoque 1 munie d'un mât 2 qui supporte une voilure mince désignée dans son ensemble par 3, en une seule partie, et qui est divisée en trois parties 3a,3b,3c ayant entre elles des zones de recouvrement 4ab, 4bc. Ces zones de recouvrement déterminent entre elles des fentes 68 (figure 4) à géométrie réglable et qui peuvent être plus ou moins ouvertes, ou bien fermées. Les parties de voilure présentent des points de tire, notamment, 5-10̸ sur leur bord inférieur par l'intermédiaire desquels sont faits les différents réglages et manoeuvres des parties de voilure.If we refer to FIG. 1 and to its enlarged detail of FIG. 1a, 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, 5-10̸ on their lower edge by means of which the various adjustments and maneuvers of the wing parts are made.

Ainsi des points de tire 5 - 10 partent les bouts :

  • 11 et 69 vers les extrémités de la borne 12 articulée en avant du mât 2,
  • 14-17 vers le pont 33,
  • 7 vers le chariot 35 coulissant sur la borne 36 articulée en arrière du mât 2 et ne pouvant pivoter autour de son axe longitudinal,
  • 23 et 70 vers le cadre 34 du chariot 35,
  • 26, 71 et 29 vers le cadre 34 et la traverse 38 du chariot 35,
  • 31 vers un chariot 42 coulissant sur un rail 43 monté en arrière de la bome 40.
Thus pull points 5 - 10 leave the ends:
  • 11 and 69 towards the ends of the terminal 12 articulated in front of the mast 2,
  • 14-17 towards bridge 33,
  • 7 towards the carriage 35 sliding on the terminal 36 articulated behind the mast 2 and which cannot pivot about its longitudinal axis,
  • 23 and 70 towards the frame 34 of the carriage 35,
  • 26, 71 and 29 towards the frame 34 and the cross member 38 of the carriage 35,
  • 31 to a carriage 42 sliding on a rail 43 mounted behind the terminal 40.

Le cadre 34, équipé de poulies par lesquelles passent des bouts venant des points de tire 8 et 9, déborde largement la bome 36. Sur le chariot 35 est articulé la borne 40 qui peut être flexible. Les bomes 36,40 forment une bome à géométrie variable. Les bomes 12, 36, 40 sont positionnées par rapport au pont 33 par des ensembles palan, chariot, rail : 50-52, 47-49, 44-46.
La concavité du rail 52 est tournée ver le mât 2.The frame 34, fitted with pulleys through which ends come from the pulling points 8 and 9, extends far beyond the boom 36. 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.

Il est en outre prévu, sur le bord d'attaque 30̸0̸ de la partie de voilure 3a, un point de tire 30̸1 auquel sont fixés deux bouts 30̸2, 302' reliés à l'engin.It is further provided, on the leading edge 30̸0̸ of the wing part 3a, a pull point 30̸1 to which are fixed two ends 30̸2, 302 'connected to the craft.

On comprend, d'après les moyens qui viennent d'être décrits en détail, que les parties de voilure 3a, 3b, 3c peuvent être contrôlées individuellement, notamment quant à leur cambrure, à leur vrillage, à leur réduction de surface ou à leur affalage.It is understood, from the means which have just been described in detail, that the 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.

Dans la forme d'exécution de la figure 1, le plan de voilure P passe par le mât qui est intégré à la partie de voilure 3b. Cette situation est schématisée à la figure 2c.In the embodiment of FIG. 1, the airfoil P passes through the mast which is integrated into the airfoil part 3b. This situation is shown schematically in Figure 2c.

En variante, comme le montre la figure 2a, le mât 2' pourrait passer à côté de plan de voilure P.Alternatively, as shown in FIG. 2a, the mast 2 ′ could pass alongside the sail plane P.

En variante encore, l'une des parties de voilure pourrait être remplacée par le mât comme en le voit à la figure 2b. Dans ce cas, le mât 2" serait convenablement profilé pour s'intégrer dans la forme aérodynamique du reste de la voilure 3a'', 3c''.In another variant, one of the wing parts could be replaced by the mast as seen in Figure 2b. In this case, the mast 2 "would be suitably profiled to integrate into the aerodynamic shape of the rest of the wing 3a '', 3c ''.

On sait que lorsque deux parties de voile ont une zone de recouvrement, telle que 4a,b et 4b,c (figure 1) et que la distance entre lesdites parties dans ladite zone est relativement faible, celles-ci peuvent venir se coller l'une à l'autre. Pour éviter une telle fermeture intempestive de la fente que l'on a souhaité ménager entre deux parties de voilure, il est connu de placer un ou plusieurs espaceurs.It is known that when two parts of the sail have an overlap zone, such as 4a, b and 4b, c (FIG. 1) and the distance between said parts in said zone is relatively small, these can stick to each other. one to the other. To avoid such an untimely closing of the slot which it was desired to provide between two wing sections, it is known to place one or more spacers.

De tels espaceurs 63 sont visibles aux figures 3 et 4 où l'on a représenté une voilure souple selon l'invention ne comportant eue deux parties 3d, 3e ayant une zone de recouvrement 4d,e. Pour permettre le contrôle individuel de ces parties de voilure, les espaceurs ne sont fixés qu'à l'une d'elles. Comme on le voit à la figure 4, les espaceurs 63 sont constitués d'une pièce 64 montée en équerre sur un support flexible 65, fixé à la partie de voilure 3c, la pièce 64 ou la jonction avec le support 65 étant articulée. Pour modifier l'importance de l'espacement entre les parties de voilure 3e, 3d, on peut agir sur les espaceurs 63 grâce à un système de câble de traction 66 sur lequel est fixé, en 67, la partie 64, lequel système abat ou relève plus ou moins cette partie 64 et donc, réduit ou augmente l'importance de l'espacement δ obtenu.Such 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. To modify the importance of the spacing between the wing parts 3e, 3d, it is possible to act on the spacers 63 thanks to a system of traction cable 66 on which is fixed, at 67, the part 64, which system cuts or more or less notes this part 64 and therefore reduces or increases the importance of the spacing δ obtained.

La deuxième forme d'exécution de l'invention se distingue essentiellement de la première par le fait qu'il s'agit de l'application de l'invention au cas d'une voilure épaisse.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.

La figure 6 représente un catamaran 101 muni d'un mât rectangulaire 102 et d'une voiture 103 constitutant l'élément aérodynamique. Celui-ci présente deux parois, 107 côté extrados et 108 côté intrados, formant l'enveloppe 109. La voilure 103, figures 5 et 6, comprend quatre paires de trappes 111 a-d et 112 a-d.
Leur ouverture s'effectue sans altérer la courbure aérodynamique des faces 107 et 108:

  • Côté extrados par déplacement du bord libre amont (162) de la trappe vers l'intérieur de la cavité (110),
  • Côté intrados par déplacement du bord libre aval (115) de la trappe vers l'intérieur de la cavité (110) ou par déplacement du bord libre amont de la trappe vers l'extérieur de la cavité.
FIG. 6 represents a catamaran 101 provided with a rectangular mast 102 and a car 103 constituting the aerodynamic element. This has two walls, 107 on the upper side and 108 on the lower side, forming the envelope 109. The airfoil 103, FIGS. 5 and 6, comprises four pairs of hatches 111 ad and 112 ad.
They are opened without altering the aerodynamic curvature of the faces 107 and 108:
  • Upper side by displacement of the upstream free edge (162) of the hatch towards the interior of the cavity (110),
  • Intrados side by displacement of the free downstream edge (115) of the hatch towards the interior of the cavity (110) or by displacement of the free upstream edge of the hatch towards the exterior of the cavity.

Des couples 120 - 124 représentés suivant un exemple fig. 7 sont logés dans l'élément aérodynamique. Ils règlent la géométrie de celui-ci.
Un exemple de dispositif fig. 8 commande les trappes.
Du couple 124 est fixé une drise pour hisser ou affaler la voilure 103.
Dans tous les cas le ou les couples sont bloqués contre toute rotation autour du support guide 102.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.

La coupe de la figure 7 montre comment peut être réalise un couple, à savoir à l'aide de plusieurs plateaux 129 à 132 disposés bout à bout et articulés entre eux. Plus précisément une extrémité du plateau 129 forme le bord d'attaque de la structure et son extrémité opposée est articulée en 133 sur le plateau 130̸ qui présente une ouverture 134 pour le passage du mât 10̸2. A l'opposé du plateau 129, le plateau 130̸ est articulé en 135 sur un plateau intermédiaire 131, lui-même articulé en 136 sur un plateau 132. A l'opposé de l'articulation 136, le plateau 132 forme le bord de fuite de la structure.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 130̸ which has an opening 134 for the passage of the mast 10̸2. 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.

L'enveloppe absorbe les différences de longueur dues à la réversibilité de la concavité, au cambrage et au vrillage. Pour ce faire, et/ou servir de rappel, l'enveloppe présente avantageusement des parties extensibles et/ou à recouvrement soumises à des moyens de tension tels que 141.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.

De chaque côté de l'ensemble constitué par les plateaux 129 à 132 sont disposées deux lattes flexibles de conformation 137 qui sont reliées aux plateaux grâce à des tenons 138 fixés auxdits plateaux et coulissant dans des rainures prévues dans lesdites lattes. Les lattes 137 sont fixées aux parois 10̸7 et 10̸8 de l'enveloppe 10̸9 ou tout au moins en contact avec elles. Les parois 10̸7 et 10̸8 ne sont schématisées que bar un fragment de ligne en pointillés côté bord de fuite. En fait, à ce niveau, l'enveloppe est en deux parties, l'une, formée par les parois 10̸7 et 10̸8, l'autre, par une paroi à cheval sur le bord de fuite, les extrémités de l'une recouvrant les extrémité de l'autre. Des câbles 139, renvoyés au pied du mât, commandent la position relative des plateaux 129 à 132 entre eux de sorte qu'en agissant sur ces câbles, on peut modifier la cambrure du couple formé par lesdits plateaux. Les lattes de conformation 137 étant tributaires desdits plateaux, elles suivent leur déplacement et l'enveloppe 10̸9 épouse la forme prise par les lattes. Les extrémités recouvrantes des parois 10̸7 et 10̸8 de l'enveloppe sont soumises à la traction de tendeurs 141.On 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 10̸7 and 10̸8 of the casing 10̸9 or at least in contact with them. The walls 10̸7 and 10̸8 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 10̸7 and 10̸8, 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 10̸9 follows the shape taken by the slats. The overlapping ends of the walls 10̸7 and 10̸8 of the envelope are subjected to the tension of tensioners 141.

La géométrie de la forme aérodynamique est obtenue en agissant convenablement sur la longueur de chaque latte et/ou sur la position de chaque plateau, pris isolément ou en combinaison, en donnant ainsi la forme voulue aux profils de la voilure par répartition de la cambrure le long du squelette de la voilure suivant l'intensité de la cambrure générale.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.

La figure 8 montre un moyen permettant de contrôler les trappes. Sur cette figure, on voit la paroi 10̸7 de l'enveloppe dans laquelle sont ménagées deux trappes 111b" et 112b", cette dernière n'étant représentée que partiellement. La paroi 10̸7 est conformée au moyen des lattes 137. La trappe 111b'' a généralement la forme d'un C dont les branches supérieure 148 et inférieure 149 sont garnies de lattes de manoeuvre 150̸ dont une extrémité affleure la branche verticale 151 du C qui définit la fente d'ouverture de la trappe. La trappe 112b'' est concue de même facon mais on ne voit que sa fente 152, alignée avec la fente 151, et sa latte de manoeuvre inférieure 150̸.Figure 8 shows a way to control the hatches. In this figure, we see the wall 10̸7 of the envelope in which are formed two hatches 111b "and 112b", the latter being only partially represented. The wall 10̸7 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 150̸, 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 150̸.

Au voisinage des fentes 151, 152, les lattes demanoeuvre 150̸ servent de point d'ancrage, d'une part, à un câble 153 qui les relie entre elles et, d'autre part, à une série de cables parallèles 154 perpendiculaires au câble 153. L'une des extrémités du câble 153 est solidarisée à un chariot 155 monté coulissant dans une glissière 156, lequel chariot 154 est lui-même manoeuvré à l'aide d'un câble 157 parallèle aux câbles 154. On comprend cu'une traction exercée selon la flèche F4 sur les câbles 154 et 157 ouvre les trappes 111b'' et 112b'' permettant le passage d'air selon la flèche F2.In the vicinity of the slots 151, 152, the maneuvering slats 150̸ 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.

La troisième forme d'exécution de l'invention procède, comme on l'a dit plus haut, de la première et de la deuxième.The third embodiment of the invention proceeds, as mentioned above, from the first and from the second.

Si l'on se reporte à la figure 9, on voit une embarcation avant une coque 20̸1 munie d'un mât 20̸2 non haubanné, intégré à une voilure 20̸3 équipée d'un système de réduction par prise de ris 271. Il est prévu, dans la voilure, une série de trappes 211a, 211b, 211c dont chacune a sensiblement la forme d'un C légèrement oblique. Ces trappes étant identiques, on ne décrira que la trappe 211a. Les branches supérieure 248 et inférieure 249 de la fente en C 211a sont approximativement parallèles à la direction de l'écoulement de l'air (flèche F5) et elles sont équipées de lattes de rigidification 250̸. Les fentes rigidifiées 248 et 249 sont réunies bar une fente souple 251a dont la direction est peu éloignée de la perpendiculaire par rapport à celle de la flèche F5. Les fentes 251a-c des trappes 211a-c sont alignées et dans leur alignement est prévu un point de tire en 20̸4. La voilure 20̸3 est équipée d'une série de lattes de commande 258, de part et d'autre de chacune des trappes 211a-c, et qui présentent des zones 259 affaiblies sur le plan de la rigidité, de sorte que ces zones 259 créent des points de fléchissement préférentiel des lattes 258. En pratique, l'épaisseur des lattes 258 est constante mais leur hauteur présente des variations. On notera que l'une des lattes 258 -référencée 258'- est coextensive au bord inférieur de la voilure 20̸3. Il est enfin prévu une latte de section constante 260̸ en tête de voilure. La flexibilité des lattes de commande 258 et de la latte 260̸ permet la réversibilité- de la concavité et les changements de bord. Les lattes 250̸, 258 et 260̸ sont logées dans des fourreaux amenagés dans la voilure et participent au réglage de la cambrure et/ou du vrillage.If we refer to FIG. 9, we see a boat before a hull 20̸1 provided with a non-guyed mast 20̸2, integrated into a wing 20̸3 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 250̸. 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 20̸4. The wing 20̸3 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. In practice, the thickness of the slats 258 is constant but their height varies. It will be noted that one of the slats 258 - referenced 258'- is coextensive with the lower edge of the wing 20̸3. Finally, a batten of constant section 260̸ is provided at the head of the blade. The flexibility of the control slats 258 and the slat 260̸ allows the reversibility of the concavity and the edge changes. The slats 250̸, 258 and 260̸ are housed in sleeves fitted in the airfoil and participate in the adjustment of the camber and / or the twist.

Une bôme flexible 261 est articulée en 262 sur le mât 20̸2, bôme qui est reliée au pont par un palan d'écoute 244 et par un autre palan 244' coopérant chacun avec un système de chariot 271, 272 et de rail, tel que représenté plus clairement à la figure 1 (références 44, 45, 46). Il est ainsi possible d'orienter la bôme par rapport à la coque 20̸1 et par rapport au vent.A flexible boom 261 is articulated at 262 on the mast 20̸2, 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 20̸1 and relative to the wind.

La bôme 261 sert elle-même de support à un rail 263 sur lequel glissent deux chariots 264 et 264' reliés respectivement aux point de tire 267 et 20̸4, par deux écoutes 266 et 266', de manière à régler la distance entre les différents points de tire de la bordure de la voile par rapport au point d'amure 270̸, et à participer à la fixation de l'intensité du cambrage général de la voilure.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 20̸4, 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 270̸, and to participate in the fixing the intensity of the general arching of the blade.

Lorsque l'on cambre la bôme 261 en agissant sur la position des chariots 271 et 272, les lattes de commande 258 et 258' fléchissent particulièrement dans les zones de rigidité moindre 259 tandis que les lattes de rigidification 250̸ résistent au fléchissement. Il s'ensuit l'ouverture des trappes 211a-c comme on le voit schématisé à la figure 10 où l'on voit également un filin 30̸7 limitant l'ébattement de la trappe 211a. Il s'agit donc d'une solution simplifiée de commande des trappes.When the boom 261 is arched by acting on the position of the carriages 271 and 272, the control slats 258 and 258 ′ bend particularly in the zones of less rigidity 259 while the stiffening slats 250̸ resist bending. It follows the opening of the hatches 211a-c as shown schematically in Figure 10 where we also see a rope 30̸7 limiting the deflection of the hatch 211a. It is therefore a simplified hatch control solution.

On peut cependant affiner le réglage en munissant les trappes de moyens qui agissent directement sur les trappes et qui sont représentés à la figure 11. Il est prévu, dans ce cas, un point d'ancrage de filin à chaque extrémité 268 des fentes souples 251a,b et, en-vis-à-vis, à l'extérieur des trappes, dans la voilure 20̸7, un guide de filin 269. Le long des fentes rigidifiées et jusqu'au mât 20̸2, est également prévue une série de guides de câble 269a-269d. Les guides de filin peuvent être des anneaux fixés aux fourreaux des lattes. Un filin 270̸ relie chaque point d'ancrage 268 au guide 269, passe par la série de guides 269a-d et est renvoyé, depuis le guide 269d le plus aval, vers un moyen de commande. On comprend qu'une traction sur les filins 270̸ aboutit à fermer les trappes.It is however possible to refine the adjustment by providing the hatches with means which act directly on the hatches and which are shown in FIG. 11. In this case, a rope anchoring point is provided at each end 268 of the flexible slots 251a , b and, opposite, outside the hatches, in the canopy 20̸7, a rope guide 269. Along the rigidified slots and up to the mast 20̸2, a series of guides are also provided. cable 269a-269d. The rope guides can be rings fixed to the sleeves of the slats. A rope 270̸ 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 270̸ leads to close the doors.

L'invention n'est pas limitée aux formes d'exécution décrites et représentées à titre d'exemples.The invention is not limited to the embodiments described and shown by way of examples.

En particulier et entre autres variantes possibles :

  • une fraction quelconque de l'élément de forme aérodynamique peut être à profil épais et la ou les parties mobiles dudit élément peut ou peuvent aussi bien être située(s) dans une zone mince que dans une zone épaisse ;
  • une ou plusieurs lattes de commande 258 (figure 9), c'est-à-dire comportant au moins une zone de flexibilité préférentielle, pourraient être utilisées dans une autre forme d'exécution que celle de la figure 9, pour mieux contrôler la forme des parties ou zones de la voilure, ou même on pourrait avoir recours, à cet effet, à une ou plusieurs lattes classiques telles que 260̸ ;
In particular and among other possible variants:
  • any fraction of the aerodynamically shaped element can be of thick profile and the moving part or parts of said element can or can be located in a thin zone as well as in a thick zone;
  • one or more control slats 258 (FIG. 9), that is to say comprising at least one preferable flexibility zone, could be used in another embodiment than that of FIG. 9, to better control the form parts or areas of the airfoil, or even one or more conventional slats such as 260̸ could be used for this purpose;

Enfin, il est bien entendu qu'un même engin peut être équipé de plusieurs dispositifs selon l'invention et/ou qu'un même dispositif peut combiner différentes formes d'exécution, c'est-à-dire par exemple, comporter une voilure en une seule partie divisée en deux parties ayant une zone de recouvrement formant fente, l'une et/ou les deux parties étant munies de trappes formant fentes complémentaires.Finally, it is understood that 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.

Claims (12)

  1. Device comprising at least one element (3, 103, 203) of aerodynamic shape, at least one part or zone of which can be folded up, for propulsion and/or lift using the effect of the relative wind, the said element having two faces designed to be located respectively on the pressure face side and the suction face side, at least one opening (68; 113, 114; 251a-c) being provided to establish a passage of air from the pressure face side to the suction face side, and guide means (4ab, 4bc, 111a,b, 211a-c) being provided to direct the air emerging from said opening on the suction face side, and give it a direction which is tangential to the said element characterized in that the said opening 58, 113, 114) and the said guide means (4ab, 4bc, 4de, 111, 112, 211) of the said air passage are adjusted in terms of geometry and opening/closing by means (23, 26, 29, 70, 71; 14, 15, 165, 17, 69; 144, 170; 150, 154; 244, 244', 258, 261) capable of acting upon both the position and the geometry of at least one part and/or zone (3a, 3b; 3b, 3c; 107, 108; 203) of the said element, and in that the said device further comprises means (5-10, 12, 36, 40, 51, 48, 45; 258, 261, 272) designed to adjust the geometry of the said element, namely, at least the curvature in terms of shape and in terms of hollow.
  2. Device according to claim 1, in which the said element is a sail structure (3) divided along a dividing line into at least two parts (3a-c; 3d-e) which are designed to form between them a slit (68) affecting all or part of the said line, the said sail structure parts overall forming a sail structure plane (P) characterized in that two consecutive sail structure parts (3a,b; 3b,c; 3d,e) have an overlap zone (4ab, 4bc; 4 de), the said slit (68) being defined by the spacing (δ) between the said sail structure parts in the overlap zone, and the said spacing (δ) being maintained by at least one spacer (63), at least one of the two sail structure parts ( 3a,b; 3b,c; 3d,e) having this overlap zone not being fixed to the spacer.
  3. Device according to claim 1 or 2, characterized in that the two faces (107, 108) of the said element (103) belong to separate skin parts (109) which define between them a hollow aerodynamic volume, and in that the said opening and the said guide means are created by a pair of flaps (111a,b; 112a,b) which are formed respectively in the one and the other side and subjected to control means (150, 153, 154, 157) which act on their closing/opening, on their orientation and on their geometry. The opening of the flap on the suction face side takes place by displacing the upstream free edge ((162) of the flap towards the inside of the cavity (110) of the aerodynamic volume so that the face (107) of the skin (109) on the suction face side retains its aerodynamic profile despite the opening of the flap.
  4. Device according to claim 3, characterized in that the opening of the flap (111a, 112a) on the pressure face side takes place by displacing the downstream free edge ((162) of the flap towards the inside of the cavity (110) of the aerodynamic volume, or by displacing the upstream free edge of the flap towards the outside of the said cavity so that the face (108) of the skip on the pressure face side offers an aerodynamic profile to the passage of air.
  5. Device according to claim 1 or 2, characterized in that the said element is a sail structure (203) and in that a flap (211a-c) creates the said opening and guide means of said passage of air, which flap is defined by a slit (251a-c) termed "supple" substantially perpendicular to the direction of the airflow (F5) in the normal position of use and by two slits (248a-c, 249a-c) termed "stiffened" substantially parallel to the said direction so that the flap has roughly the shape of a C, the said stiffened slits (248a-c, 249a-c) being so owing to the presence, in the sail structure, of stiffening battens (250) running alongside the said slits and extending beyond those of their ends which are opposite the said supple slit (251a-c).
  6. Device according to claim 5, characterized in that the said flap (211a-c) is subjected to control means comprising at least one batten termed "control batten" (258) built into the said sail structure in a direction substantially parallel to the stiffened slits (248a-c, 249a-c), the said control batten having at least one zone of weakened stiffness (259) designed to promote the bending of the said batten at the level of this zone.
  7. Device according to claim 5 or 6, characterized in that the said flap (211a, b) is further provided with manoeuvring means (268, 269, 269a-d, 270) acting directly on its position.
  8. Device according to any one of claims 1-7, of the type in which the element is a sail structure which includes at least two leading edges, characterized in that at least one of the said leading edges is equipped with a continuous or discontinuous stiffening element whose geometry is variable and adjustable (129,137,139,133; 300, 301, 302).
  9. Device according to any one of claims 1-8, characterized in that the creation and/or adjustment of the air passage opening(s) and of the guide means for the airflow are independent of the overall geometry of the said element of aerodynamic shape, particularly the length of its skeleton and of its profile.
  10. Device according to any one of claims 1-9, of the type in which the said element includes at least two leading edges, characterized in that at least one leading edge is provided with means (12, 50, 51, 52; 5, 69; 35, 36, 8, 9, 23, 70, 26, 71, 47, 48, 49; 129, 139) giving it its own mobility.
  11. Device according to claim 10, characterized in that, in the case where the most upstream leading edge of the said element has its own mobility, the said means giving it its own mobility include at least one rail (52).
  12. Water or land craft equipped with a device according to any one of claims 1 through 11, the said device further comprising means to vary the direction of at least one of said elements (3, 103, 203) with respect to the said craft, and means to partially and/or totally reduce the surface of at least one of said elements (3, 103, 203), the device modified in that the means (23, 26, 29, 70, 71; 14, 15, 165, 17, 69; 150, 154; 244, 244', 258, 261) adjusting the said guide means (4ab, 4bc, 4de, 111, 112, 211) and the said opening (68, 113, 114) are capable of acting upon the position and/or the geometry of at least one part and/or zone (3a, 3b; 3b, 3c; 107, 108; 203) of the said element.
EP92401041A 1991-04-17 1992-04-14 Device with at least one aerodynamically shaped element with changeable geometry, incorporating a control system of the boundary layer Expired - Lifetime EP0511050B1 (en)

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 (en) 1991-04-17 1991-04-17 Aerodynamic sail device for propulsion by the wind
FR9105445A FR2676032A1 (en) 1991-05-03 1991-05-03 Aerodynamic device with great adjustable lift
FR9105445 1991-05-03
FR9108750 1991-07-11
FR9108750A FR2678892B1 (en) 1991-07-11 1991-07-11 AERODYNAMIC VEIL FOR WIND PROPULSION.

Publications (2)

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EP0511050A1 EP0511050A1 (en) 1992-10-28
EP0511050B1 true EP0511050B1 (en) 1996-12-18

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US (2) US5485799A (en)
EP (1) EP0511050B1 (en)
AT (1) ATE146424T1 (en)
AU (1) AU1777092A (en)
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DE (1) DE69215952T2 (en)
DK (1) DK0511050T3 (en)
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WO (1) WO1992018381A2 (en)

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

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