Profiled Wing System

Abstract

The present disclosure relates to a telescopic profiled wing system (1) for propelling a vehicle by wind power, said profiled wing system comprising a mast (M) and a set of telescopic segments (SG) that cooperate with each other during guidance, The telescopic segments are configured such that at least in a deployed position (P1) the various telescopic segments extend relative to one another in the direction of the mast (M) by forming profiled wings (AP), the profiled wings having first wing surfaces (S1) and second wing surfaces (S2) distributed on both sides of the mast (M), and the system is configured to switch from the deployed position (P1) to a stowed position in which the various segments (SG) are nested together, the profiled wings (AP) being in a position that occupies less space compared to the deployed position.

Description

[Technical Field]

[0001] The present disclosure relates to a telescoping profiled wing system for propelling a vehicle by wind power.

[0002] The present disclosure relates to the field of rigging, more particularly to wind propulsion devices, and in particular to profiled wings or profiled sails, also referred to as "wingsails" or "thick sails" by those skilled in the art. [Background technology]

[0003] From the prior art, in particular from US Pat. No. 5,949,549, a rigging is known which includes a flexible profiled sail and a cambering device configured to vary the camber of the profiled sail according to wind conditions, thereby limiting the risk of entanglement of its components, thereby allowing it to be raised and lowered.

[0004] Such prior art rigging is particularly effective in terms of optimizing the efficiency of the rigging for wind propulsion.

[0005] The inventor has observed that such solutions rely on flexible sails that are prone to tearing and require careful maintenance.

[0006] The prior art is also known from patent document 2, in which a profiled sail comprises two sailing surfaces in contact with the wind, which are flexible, usually made of canvas or flexible film, and which, like patent document 1, are prone to tearing. [Prior art documents] [Patent documents]

[0007] [Patent Document 1] WO2021148734 [Patent Document 2] EP 3 299 275 [Non-patent literature]

[0008] [Non-Patent Document 1] B. Tondu and P. Lopez, "Compte Rendu de l'Academie des Sciences", t.320, pp. 105-114, 1995. Summary of the Invention [Problem to be solved by the invention]

[0009] This disclosure improves the situation. [Means for solving the problem]

[0010] A telescopic profiled wing system for propelling a vehicle by wind power is proposed, said profiled wing system comprising a mast and a set of telescopic segments cooperating with each other during guidance, the telescoping segments are configured so that at least in a deployed position, the various telescoping segments extend relative to one another in the direction of the mast by forming profiled wings, the profiled wings having first and second wing surfaces distributed on both sides of the mast, and the system is configured to switch from the deployed position to a stowed position, in which the various segments are nested together, the profiled wings being in a position that occupies less space compared to the deployed position; All or part of the telescopic segment is two length sections extending in front of each other and respectively forming a first length section forming a first aerofoil surface of the profiled wing and a second length section integral with a second surface of the profiled wing forming a second aerofoil surface of the profiled wing; a U-shaped connecting section that interconnects the first length section and the second length section by extending them at the leading edge of the profiled wing, and the two length sections terminate at the trailing edge of the sail by two free ends;

[0023] The elastically deformable, semi-rigid structure includes: The system includes actuation means configured to interconnect, for all or a portion of the telescoping segment, at least one of the two free ends, on the one hand, and a U-shaped connection section, on the other hand, and to warp the first length section and the second length section of the semi-rigid structure by applying tension to one of the two free ends at the U-shaped connection section of the semi-rigid structure and generating a misalignment between the two free ends.

[0011] According to one embodiment, the actuation means configured to deflect the first and second length sections of the semi-rigid structure comprise at least one actuator having two longitudinal ends, said actuator being activatable and being contractible when activated so that its two longitudinal ends approach each other, said at least one actuator extending along one of the two length sections of the semi-rigid structure, i.e. the first length section or the second length section, said actuator being internal to and housed in the semi-rigid structure, One of the longitudinal ends of the at least one actuator is connected to one of the two free ends, while the other of the two longitudinal ends of the at least one actuator is connected to at least one anchor point integral with the U-shaped connecting section.

[0012] According to one embodiment, the actuator, which connects the anchor point of the U-shaped connection section to one of the free ends of the first length section according to the first possibility and / or the second length section according to the second possibility, bypasses the mast on the side opposite the first length section according to the first possibility or bypasses the mast on the side opposite the second length section according to the second possibility.

[0013] According to one embodiment, the actuation means selectively comprises: In a first camber position, when the second length section has a convex profile, the first length section has a concave profile; In a second camber position, when the first length section has a convex profile, the second length section has a concave profile; The semi-rigid structure is configured to deflect.

[0014] According to one embodiment, said at least one actuator of the actuation means comprises: a first actuator configured to deflect the semi-rigid structure into the first deflected position, one of its longitudinal ends connected to an anchor point of the U-shaped section and the other longitudinal end connected to a free end of the second length section, the first actuator configured in an activated state to retract and pull the free end connected by the first actuator on the one hand and the at least one anchor point on the other hand until a misalignment occurs, the connected free end advancing towards a leading edge relative to the other free end by deflecting the semi-rigid structure, the first length section assuming a concave profile and the second length section assuming a convex profile in the first deflected position; a second actuator configured to deflect the semi-rigid structure into the second deflected position, one of its free ends connected to an anchor point of the U-shaped section and the other longitudinal end connected to a free end of the first length section, the second actuator configured in an activated state to retract and pull the free end connected by the second actuator on the one hand and the at least one anchor point on the other hand until a misalignment occurs, the connected free end advancing towards a leading edge relative to the other free end by deflecting the semi-rigid structure, the second length section assuming a concave profile and the first length section assuming a convex profile in the second deflected position; Includes.

[0015] According to one embodiment, the profiled wing system is selectively configured to: activating the first actuator to induce the first deflection position while maintaining the second actuator in a deactivated state; and activating a second actuator to induce the second deflection position while keeping the first actuator in a deactivated state. The control means is configured to:

[0016] According to one embodiment, all or some of the telescopic segments of the profiled wing can be activated / deactivated and have a fastening system configured to securely fasten the profiled wing on the mast, the fastening system comprising: a first flexible strand connected to the first length section by two longitudinal ends of the first strand and bypassing the mast from the first length section; a second flexible strand connected to the second length section by two longitudinal ends of the second strand and bypassing the mast from the second length section; an actuator system, operable within the structure, configured to arrest the telescoping segment on the mast, inside the semi-rigid structure, between the first and second strands, and switch the first and second strands between a stowed state configured to hold the mast at a distance from the two length sections by the first and second strands under tension, and a deployed state of the first and second strands configured to release the mast, thus allowing movement of the cambering device along the mast; Includes.

[0017] According to one embodiment, the semi-rigid structure of the various telescopic segments comprises, in whole or in part, a spacer system including a first spacer interconnecting the first length section and the second length section, and a second spacer parallel to the first spacer interconnecting the first length section and the second length section; The longitudinal ends of the first strand are fixed at two attachment points on the first length section at the junction region between the first and second spacers and the first length section, respectively, and the longitudinal ends of the second strand are fixed at two attachment points on the second length section at the junction region between the first and second spacers, respectively. The mast extends between the spacers consisting of the first spacer and the second spacer, and the first strand and the second strand are fastened onto the mast, securely holding the mast at a distance from the first spacer on the one hand and the second spacer on the other hand.

[0018] According to one embodiment, the at least one tightening actuation member of the anchoring system and / or the at least one actuator of the actuation means is an artificial muscle that contracts when pressure is supplied by a fluid and relaxes when the fluid pressure decreases, the artificial muscle having an envelope that receives inside a balloon to which fluid is supplied or evacuated, the flexible envelope being in particular in the form of a braid and configured to contract in its length when an increase in fluid is supplied to the balloon, increasing its cross section, and to expand in its length when fluid is evacuated from the balloon, decreasing its cross section.

[0019] According to one embodiment, the various telescoping segments decrease in size according to the height of the mast in said deployed position, such that in the deployed position an upper telescoping segment is inserted into a lower telescoping segment, in said stored position the various telescoping segments are nested relative to one another.

[0020] According to one embodiment, the profiled wing system comprises guide means between successive telescopic segments, including at least one first guide element extending along the height of the lower, telescopic segment, preferably inside the semi-rigid structure of said telescopic segment, which during guiding cooperates with at least one second guide element located below, preferably external to, the upper telescopic segment, which during guiding cooperates with the first guide element along a limited travel to ensure sliding between two successive telescopic segments between the retracted position of the profiled wing and said deployed position.

[0021] According to one embodiment, the various telescoping segments include a top telescoping segment that constitutes the uppermost telescoping segment of the profiled wing in the deployed position, and a bottom telescoping segment that is integrated into the lower part of the mast and constitutes the lowermost telescoping segment in the deployed position, the top telescoping segment being connected to a hoisting halyard carried by the boom at the top of the mast, the halyard being configured to ensure the various telescoping segments are deployed from the stowed position of the profiled wing to the deployed position.

[0022] According to one embodiment, the bottom telescoping segment is connected to the mast via an adjustment device configured to ensure the orientation of the profiled wing around the mast, including a mechanism for adjusting the orientation of the bottom telescoping segment around the mast.

[0023] According to one embodiment, the mechanism for adjusting the orientation of the bottom telescoping segment around the mast comprises: a first portion rotatably connected to the mast, where there is no possibility of rotation between the first portion and the mast; a second part integral with the semi-rigid structure of the bottom telescoping segment via a system of spacers of the bottom telescoping segment, the spacers being hinged and interconnecting the first length section and the second length section; a mechanical, preferably electric, transmission ensuring adjustment of the rotational position of the second part around the first part; Includes.

[0024] In particular, mechanical transmissions a ring gear rotatably connected to the first portion; an electric pinion embedded in the second part; a toothed belt connecting the ring gear to the electric pinion; and The transmission is configured such that rotation of the motorized pinion causes rotation of the second portion relative to the first portion by changing the orientation of the telescoping base segment about the mast.

[0025] The present disclosure further relates to a watercraft-like vehicle including wind propulsion including at least one telescoping wing system according to the present disclosure.

[0026] The vehicle may be a vessel including an upper deck with a mast extending therefrom, and the profiled wing deployed from a lower, bottom, telescoping segment to an upper, top, telescoping segment.

[0027] The mast can extend below the upper deck through a formwork, the mast being fixed to the ship's structure below the formwork, the formwork being positioned below the elevation of the upper deck, and the telescopic wings in the stowed position being configured to be lowered below the upper deck through openings in the upper deck and stored in the formwork.

[0028] The vehicle may include a cover system configured to close an upper opening by abutting against a mast in the retracted and stowed position of the telescoping wings within the formwork and in the extended position of the telescoping wings outside the formwork.

[0029] Other features, details and advantages will become apparent upon reading the following detailed description and examining the accompanying drawings. [Brief explanation of the drawings]

[0030] [Figure 1] FIG. 1 is a diagram of a profiled wing system in a stowed position of the profiled wing, in which the telescoping segments are telescopically fitted together to occupy less vertical space, with the stowed profiled wing positioned above the upper deck of a ship, according to one embodiment. [Figure 2] 2 is a perspective view of FIG. 1 showing the profiled wing in a retracted position above a formwork having an upper opening through which the retracted profiled wing is intended to pass, the upper opening of the formwork being closed by a cover system. [Figure 3] 3 is a continuation of FIG. 2 showing the profiled wings in the retracted position being lowered through the top opening of the cover after the cover system has been opened. [Figure 4] FIG. 1 shows a view of the profiled wing in the stowed position, fully housed and stowed in a formwork below the upper deck of the ship, with the upper opening of the formwork closed by the cover system. [Figure 5] 1A and 1B are front and perspective views of a profiled wing in a deployed position with the various segments extending across the height of the mast. [Figure 6] FIG. 6 is a detail view of FIG. 5 showing the top telescoping segment, hereafter referred to as the top telescoping segment, coupled to the halyard via a spacer connecting the first and second length sections of the semi-rigid structure that forms the top telescoping segment. [Figure 7]FIG. 1 is a diagram of a guide means between two consecutive telescopic segments of a profiled wing, comprising a first guide element extending along the height of the lower telescopic segment and a second guide element integral with the lower end of the upper telescopic segment, configured to cooperate with deployment along the first guide element along a limited movement during guiding. [Figure 8] FIG. 1 is a perspective view of a profiled wing in a deployed position, showing in particular an actuation means including a first actuator and a second actuator configured to deflect the semi-rigid structure of the segment according to two camber positions, respectively, and a system for securing the segment to a mast, including a first strand extending from a first length section of the structure by bypassing the mast and a second strand extending from a second length section of the structure by bypassing the mast, the first and second strands consisting of an activatable actuator inside the structure configured to switch the first and second strands into a retracted state configured to block the telescopic segment on the mast, inside the semi-rigid structure, in a state clipped between the first and second strands, and to hold the mast at a distance from the two length sections by the first and second strands under tension. [Figure 9] FIG. 9 is a detailed view of FIG. 8. [Figure 10] FIG. 1 is a perspective view of the bottom telescoping segment, which is the lowest segment of the profiled wing, showing in more detail a mechanism for changing the orientation of the bottom telescoping segment about the mast, including a first portion rotatably connected to the mast, a second portion pivotally mounted about the first portion and attached to the semi-rigid structure of the segment via a system of spacers, and a mechanical transmission configured to pivot the second portion about the first portion, the mechanical transmission including a motorized pinion embedded in the second portion, a ring gear integral with the first portion, and a toothed belt meshing between the motorized pinion and the ring gear. [Figure 11] FIG. 11 is a bottom view of FIG. [Figure 12] FIG. 10 is a view of the orientation change device when the semi-rigid structure of the bottom telescoping segment is hidden. [Figure 13] FIG. 2 is a detailed view of a ring gear of a mechanical transmission. [Figure 14] 1 is a diagram of a semi-rigid structure of a telescoping segment in a rest position and first and second actuators configured to selectively deflect the structure in first and second deflection positions. [Figure 15] 15 is a schematic diagram of a cross section of the semi-rigid structure of the segment of FIG. 14 in a rest position as a solid line and in two different warped positions, i.e., a first warped position and a second warped position in one direction and the other relative to the rest position as dotted lines; FIG. 15 shows on the right side the offset marked with "d" between the two free ends of the first and second length sections of the structure when the structure is warped in the first warped position. [Figure 16] FIG. 10 is a detailed view of the two free ends of the semi-rigid structure, connected via the medial tendons by a first actuator and a second actuator, respectively. [Figure 17] FIG. 1 is a detailed view of the actuation system of the fastening system according to a first possible variant, in which the first strand includes a retractable first actuation member and the second strand includes a retractable second actuation member, the first actuation member and the second actuation member being in their retracted state such that the mast is clamped between the first and second strands and the first and second length sections of the semi-rigid structure as well as spacers joining the first and second length sections together hold the mast at a distance from the mast and secure it in place. [Figure 18] 18 is a detail view of FIG. 17, in which in the deployed state of the first actuating member and the second actuating member, the first strand and the second strand are slack, releasing the mast. [Figure 19] FIG. 1 is a schematic diagram of an artificial muscle in a non-actuated position, i.e., with pressurized fluid evacuated. [Figure 20]FIG. 20 is a schematic diagram of the artificial muscle of FIG. 19 in an actuated position, i.e., supplied with pressurized fluid, which increases its cross section and causes the actuator to contract lengthwise, bringing its longitudinal ends closer together. [Figure 21] 21 is a cross-sectional view of FIG. 20 showing in cross section the envelope in the form of a braid and the balloon received (sealed) inside the envelope supplied with pressurized fluid. [Figure 22] 1 is a view of a profiled wing in a deployed position, the various telescopic segments being fixed on the mast by tightening the first and second strands of the fastening system, the view transparently showing the bottom telescopic segment with the first actuator activated and the second actuator released, the first actuator being configured to deflect the telescopic segment into a first deflection position, the first actuator retracting and pulling, on the one hand, the free end of the second length section connected by the first actuator and, on the other hand, said at least one anchor point, until a displacement d occurs, and the free end of the first length section advances towards the leading edge BA relative to the other free end of the first length section, thereby deflecting the semi-rigid structure into the first deflection position. [Figure 23] 23 is a view according to FIG. 22, showing transparently the actuator and the system for fixing the telescoping segments of the wing, which are higher than the bottom telescoping segment. DETAILED DESCRIPTION OF THE INVENTION

[0031] The present disclosure relates to a telescoping profiled wing system 1 for propelling a vehicle by wind power, said profiled wing system comprising a mast M and a set of telescoping segments SG cooperating with each other during guidance.

[0032] The mast M may be a unitary, typically tubular, element according to the embodiment shown, or may be telescopic itself so as to be extended and retracted according to an embodiment not shown.

[0033] The telescoping segments are configured to form, at least in a deployed position P1, a profiled wing AP, the various telescoping segments extending relative to one another in the direction of the mast M by forming the profiled wing. The profiled wing AP has a first wing surface S1 and a second wing surface S2 distributed on either side of the mast M. Such a deployed position P1 of the profiled wing AP is shown in Figure 5.

[0034] The system is configured to switch from the deployed position P1 to a retracted position P2 in which the various segments SG are nested together, with the profiled wings AP in a position that takes up less space relative to the deployed position P1. Such a retracted position of the profiled wings AP is shown in Figures 1 to 4.

[0035] According to the present disclosure, all or part of the telescoping segment may be: two length sections extending in front of each other and forming respectively a first length section 20 forming a first wing surface S1 of the profiled wing and a second length section 21 forming a second wing surface S2 of the profiled wing; a U-shaped connecting section 22 that interconnects the first length section 20 and the second length section 21 by extending them at the leading edge BA of the profiled wing, and the two length sections terminate at the trailing edge BF of the sail by two free ends 23, 24; and (respectively) an elastically deformable, semi-rigid structure 2 including:

[0036] The profiled wing system also includes actuation means 4 interconnecting, for all or part of the telescopic segment SG, at least one of the two free ends 23, 24 on the one hand and the U-shaped connecting section 22 on the other hand. The actuation means 4 is configured to apply tension to one of the two free ends 23, 24 at the U-shaped connecting section 22 of the semi-rigid structure 2, thereby generating a displacement d between the two free ends 23, 24, thereby deflecting the first length section and the second length section of the semi-rigid structure. Such a displacement d is shown in Figure 15.

[0037] The semi-rigid structure 2 is usually made of composite material and can usually be in the form of a flat element (like a panel) that extends continuously along the cross section of the structure to form a U-shaped connecting section 22 and a first length section 20 and a second length section 21, respectively, in whole or in part. The flat element extends in height in the direction of the mast M along a dimension that forms the length of the telescopic segment. Alternatively, the flat element can be obtained by assembling a plurality of flat plate sections that articulately form the U-shaped connecting section 22, respectively, and the two length sections (first and second 21 and 22). In general, each semi-rigid structure extends according to said dimension that forms the length of the telescopic segment in the direction of the mast.

[0038] The first and second wing surfaces S1, S2 of the profiled wing formed by the extension of the various segments are thus obtained by a semi-rigid structure 2. A robust system is obtained, avoiding the risk of tears, as may occur in profiled flexible sails according to the prior art, for example as disclosed in patent document EP 0 999 543.

[0039] In other words, the first wing surface S1 and the second wing surface S2, in particular in the deployed position P1, are obtained by extending the semi-rigid structure 2 (exclusively) in the direction of the mast, relative to one another, as shown in particular in Figure 5 et seq. Consequently, the wing surfaces S1 and S2 therefore do not comprise a fabric (or flexible film) under tension that is prone to tearing, in particular in contrast to the prior art disclosed in particular by US Pat. No. 5,999,227 or US Pat. No. 5,999,227, in which the surface in contact with the wind consists of a flexible material such as a flexible sail, i.e. a film or fabric.

[0040] The semi-rigid structures 2 forming the various telescopic segments are shaped and therefore free-standing components, particularly in the storage position P2 when the segments are stored relative to one another, as shown in Figures 1 to 3. The telescopic segments maintain their holding force in the deployed position P1, but also in the storage position P2 when the various semi-rigid structures 2 are nested relative to one another.

[0041] The various segments SG may also include a spacer system 3 including at least one spacer interconnecting a first length section 20 and a second length section 21, said spacer being configured to operate in compression and tension to maintain the spacing between the two length sections 20, 21. The spacer system 3 typically includes a first spacer 30 interconnecting the first length section 20 and the second length section 21, and a second spacer 31 parallel to the first spacer 30 interconnecting the first length section 20 and the second length section 21. The spacers may be of fixed or optionally telescopic length.

[0042] It should be noted that the mast M extends between spacers consisting of a first spacer 30 and a second spacer 31. The spacers (first and second) are configured to operate in tension and compression. Optionally, a third spacer 33 may extend in parallel and connect the first length section 20 and the second length section 21. This third spacer 33 is located inside the structure 2, between the second spacer 31 and the trailing edge BF of the profiled wing AP.

[0043] Each spacer, consisting of the first spacer and the second spacer 30, 31, or even the third spacer 33 of the spacer system 3, can be pivotally hinged at its both ends to the first length section 20 along an axis perpendicular to the plane of the semi-rigid structure and to the second length section 21 along an axis perpendicular to the plane of the semi-rigid structure, and each spacer 30, 31 is configured to pivot relative to the two length sections, i.e. the first length section 20 and the second length section 21, under the effect of the actuation means 4, during cambering and displacement of the free ends 23, 24.

[0044] For this purpose, the hinge connector 32 comprises a first part fixed to the first length section 20 or the second length section 21, or even a second part receiving one end of the spacer 30, 31, the second part being hinged to the first part according to a pivot axis substantially perpendicular to the plane of the semi-rigid structure 2 and pivoting relative to the two length sections during cambering and misalignment of the free ends 23, 24 under the effect of actuation means.

[0045] The control means are configured to control the various actuation means 4 of the telescopic segments SG together in the same direction to camber the first profiled slat S1 and the second profiled slat S2. For example, the various segments SG can assume a (particularly first) cambered position in which the first length section 20 assumes a concave profile when the second length section assumes a convex profile, and / or a (particularly second) cambered position in which said second length section 21 assumes a concave profile when said first length section 20 assumes a convex profile.

[0046] The semi-rigid structure 2 may have a profile with a plane of symmetry in a rest position Pr of the semi-rigid structure 2 in which the first length section 20 and the second length section 21 have a convex profile. The plane of symmetry of the semi-rigid structure 2 in the rest position extends in a direction parallel to the mast M, between the leading edge BA and the trailing edge BF.

[0047] It may be noted that in the rest position Pr of the semi-rigid structure, the first spacer 30 and the second spacer 31 each extend substantially perpendicular to the plane of symmetry.

[0048] In at least one deflection position Pc1 and / or Pc2 of the semi-rigid structure 2 under the action of the actuation means 4, when the second length section 21 has a convex profile, the first length section 20 has a concave profile, or when the first length section 20 has a convex profile, the second length section 21 has a concave profile.

[0049] According to one embodiment, the actuation means 4 configured to deflect the first and second length sections of the semi-rigid structure comprises at least one actuator 40, 41 having two longitudinal ends 40a, 41a, 40b, 41b, said actuator 40, 41 being actuatable and capable of contracting when actuated so that its two longitudinal ends approach each other, said at least one actuator 40, 41 extending along one of the two length sections of the semi-rigid structure, i.e. the first length section 20 or the second length section 21, said actuators 40, 41 being inside the semi-rigid structure 2 and housed in the semi-rigid structure 2.

[0050] One of the longitudinal ends 40a, 41a of said at least one actuator 40, 41 is connected to one of the two free ends 23, 24, while the other of the two longitudinal ends 40b, 41b of said at least one actuator 40, 41 is connected to at least one anchor point fixed to the U-shaped connecting section 22. In particular, one of the longitudinal ends 40a, 41a is connected to one of the ends by an inner tendon 42 guided by a guide 45 fixed to the length section carrying said longitudinal end.

[0051] According to one embodiment, the actuators 40, 41, which connect the anchor points of the U-shaped connecting section 22 to one of the free ends of the first length section 20 according to the first possibility, or to one of the free ends of the second length section 21 according to the second possibility, bypass the mast M on the opposite side of the first length section 20 according to the first possibility, or on the opposite side of the second length section 21 according to the second possibility. Such an embodiment is shown in Figure 14. However, according to another possibility, the actuators can also bypass the mast on the opposite side, which would be disadvantageous in terms of camber performance.

[0052] According to one embodiment, the actuation means 4 selectively: When the second length section 21 has a convex profile, at a first camber position Pc1 where the first length section 20 has a concave profile, When the first length section 20 has a convex profile, at a second camber position Pc2, the second length section 21 has a concave profile. The semi-rigid structure is configured to deflect.

[0053] The camber position can be adjusted during operation, for example, by switching the cambering device from a first camber position Pc1 to a second camber position Pc2 (with an opposite concave surface) during an edge change operation, also in a tuck or jibe operation.

[0054] The actuators used in the actuation means are progressive (not on or off) and have multiple positions that allow the first and second sail surfaces to be deflected more or less strongly in either direction. The concavity of the wind-facing surface of the sail can be adjusted to maximize the force required to propel the vehicle forward according to the wind direction.

[0055] According to one embodiment, said at least one actuator of the actuation means comprises: a first actuator (40) configured to deflect the semi-rigid structure to said first deflection position (Pc1), one of its longitudinal ends (40a) being connected to an anchor point of the U-shaped section, while the other longitudinal end (40b) is connected to the free end (24) of the second length section (21), said first actuator (40) being configured in an activated state to retract and pull the free end (24) connected by the first actuator (40) on the one hand and said at least one anchor point on the other hand until a displacement (d) occurs, the connected free end (24) advancing towards a leading edge (BA) relative to the other free end (23) by deflecting the semi-rigid structure, and wherein the first length section (20) assumes a concave profile and the second length section (21) assumes a convex profile at said first deflection position (Pc1); a second actuator (41) configured to deflect the semi-rigid structure to said second deflection position (Pc2), one of its free ends (41a) being connected to an anchor point of the U-shaped section, while the other longitudinal end (41b) is connected to the free end (23) of the first length section (20), said second actuator (41) being configured in an activated state to retract and pull the free end (23) connected by the second actuator (41) on the one hand and said at least one anchor point on the other hand until a displacement is generated, the connected free end (23) advancing towards a leading edge (BA) relative to the other free end (24) by deflecting the semi-rigid structure, and the second length section (21) adopting a concave profile and the first length section (20) adopting a convex profile at said second deflection position (Pc2); may include:

[0056] According to one embodiment, the profiled wing system is selectively configured to: activating the first actuator 40 to cause the first deflection position Pc1 while keeping the second actuator 41 in a deactivated state; By keeping the first actuator 40 in a deactivated state, the second actuator 41 is activated to cause the second deflection position Pc2. The control means may be configured to:

[0057] According to one embodiment, all or part of the telescopic segment SG has a fastening system 7 which can be activated / deactivated and which is configured to securely fasten the profiled wing on the mast.

[0058] In its operative state, the fastening system 7 is advantageously configured to ensure deflection of the lateral supports due to wind pressure on the profiled wing on the mast, while keeping the mast at a distance from the semi-rigid structure of the system. The fastening system 7 positions said profiled wing by avoiding collisions between the mast M and sensitive parts of the profiled wing system, in particular with the spacers 30, 31.

[0059] As can be seen in the figure, the fastening system 7 comprises: a first flexible strand 71 connected to the first length section 21 by its two longitudinal ends and bypassing the mast M from the first length section 20; a second flexible strand 72 connected by its two longitudinal ends to the second length section 20 and bypassing the mast M from the second length section 21; Includes.

[0060] The mast therefore extends between a first strand 71 and a second strand 72 .

[0061] The fastening system also includes an actuator system that can be activated and configured to switch the first and second strands into a retracted state configured to clamp the cambering device on the mast M, inside the semi-rigid structure, between the first strand 71 and the second strand 72, as shown in the detailed view of Figure 17 inside the semi-rigid structure.

[0062] Advantageously, the mast thus fastened by the first and second strands 71, 72 is held at a distance from the two length sections 20, 21 by the tensioned first and second strands 71, 72, and also from the first and second spacers 30, 31, when present. Wind forces acting on the profiled wing are diverted towards the mast by the tensioned first and second strands 72, 72.

[0063] Conversely, when the actuator system is deactivated, this causes the deployed state of the first and second strands configured to release the mast and allow the telescoping segment to easily move along the mast from the first deployed position P1 to the retracted position P2 or vice versa.

[0064] The semi-rigid structure of the various telescopic segments SG may comprise, in whole or in part, a spacer system 3 including a first spacer 30 interconnecting the first length section 20 and the second length section 21, and a second spacer 31 parallel to the first spacer 30 interconnecting the first length section 20 and the second length section 21.

[0065] Advantageously, both longitudinal ends of the first strand 71 are fixed at two attachment points on the first length section 20 in the junction region between the first and second spacers 30, 31 and the first length section 20, respectively, and both longitudinal ends of the second strand 72 are fixed at two attachment points on the second length section 21 in the junction region between the first and second spacers 30, 31, respectively.

[0066] The mast M then extends between the spacers consisting of the first spacer 30 and the second spacer 31, and the first strand 71 and the second strand 72 are fastened onto the mast, holding it securely at a distance from the first spacer 30 on the one hand and the second spacer 31 on the other hand.

[0067] With regard to the first and second spacers 30, 31, it will be noted that such spacers 30, 31 promote a secure and firm clamping of the mast by the first strand 71 and the second strand 72 due to the compressive action of the spacers which opposes the contraction of the first and second strands 71, 72.

[0068] To optimize the synergy between the spacers 30, 31 and the strands 71, 72, the longitudinal ends of the first strand 71 can each be fixed at two attachment points on the first length section 20 in the junction area between the first and second spacers 30, 31, on the one hand, and the first length section 20, on the other hand; The longitudinal ends of the second strand 72 can each be fixed at two attachment points on the second length section 21 in the junction area between the first and second spacers 30, 31, on the one hand, and the second length section 21, on the other hand.

[0069] Each spacer, consisting of the first spacer and the second spacer 30, 31 of the spacer system 3, can be pivotally hinged at its both ends to the first length section 20 along an axis perpendicular to the plane of the semi-rigid structure and to the second length section 21 along an axis perpendicular to the plane of the semi-rigid structure, respectively, and is configured to pivot relative to the two length sections, i.e. the first length section 20 and the second length section 21, under the effect of the actuation means 4, during cambering and displacement of the free ends 23, 24.

[0070] For this purpose, the telescopic segment SG may comprise a hinge connector 32 comprising a first part fixed to the first length section 20 or the second length section 21, or even a second part receiving one end of the spacer 30, 31, the second part being hinged to the first part according to a pivot axis substantially perpendicular to the plane of the semi-rigid structure 2 and pivoting relative to the two length sections during cambering and displacement of the free ends 23, 24 under the effect of actuation means.

[0071] Additionally, both longitudinal ends of the first strand 71 can advantageously be attached to a first portion of a connector 32 fixed to the first length section 20, and both longitudinal ends of the second strand 72 are attached to a first portion of a connector 32 fixed to the second length section 21.

[0072] According to one embodiment, the actuator system of the fastening system 7 comprises at least one tightening actuation member m having two longitudinal ends e1, e2, said actuation member being capable of being activated and being capable of contracting when activated, so that its two longitudinal ends e1, e2 approach each other.

[0073] The tightening actuation member can be an artificial muscle, in particular a pneumatic muscle. Such an actuator has an envelope that receives a balloon inside, through which fluid is supplied or exhausted. This flexible envelope contracts longitudinally as the fluid supplied to the balloon increases (the muscle contracts) and its cross section increases, and expands longitudinally as the fluid is exhausted from the balloon (the fluid pressure decreases) and its cross section decreases. The contraction of the actuator can be made gradual by controlling the amount of fluid supplied to the balloon.

[0074] Such pneumatic actuation systems are commonly called "artificial muscles" and consist of an expandable tube inserted into a protective braid that forms an envelope, so that the artificial muscle contracts or expands depending on whether the fluid pressure inside it increases or decreases. Such artificial muscles are described, for example, in Non-Patent Document 1.

[0075] Such an artificial muscle is shown schematically in its deployed position in FIG. 19, in its contracted position in FIG. 20, and in cross section in FIG. 21.

[0076] When the balloon B is supplied with pressurized fluid (eg air), the cross section of the balloon increases, which in turn increases the cross section of the envelope Ev, which in FIG. 21 is in the form of a braid.

[0077] The effect of increasing the cross section of the envelope is that the braiding of the envelope brings the longitudinal ends e1 or e2 closer together, thereby generating a force that ensures the contraction of the artificial muscle.

[0078] Such actuators include: Electrification of the profiled wing is not required; a flexible part, which has no possibility of being aggressive or even of being in direct contact with the mast M so as to fasten it without the risk of altering its surface; This has the advantage that:

[0079] According to the first embodiment, the first strand 71 can include a first tightening actuation member m1, in particular a first artificial muscle, and the second strand 72 can include a second tightening actuation member m2, in particular a second artificial muscle.

[0080] One such embodiment is shown in Figure 17, where the first and second tightening actuating members m1 and m2 are artificial muscles. The longitudinal ends e1 and e2 of the first tightening actuating member m1 are fixed at two attachment locations on a first portion of a connector 32 connected to the first length section 20 in the junction regions with the first and second spacers 30 and 31, respectively. Similarly, the longitudinal ends e1 and e2 of the second tightening actuating member m2 are fixed at two attachment locations on a first portion of a connector 32 connected to the second length section 21 in the junction regions with the first and second spacers 30 and 31, respectively.

[0081] The at least one actuator, if appropriate the first actuator 40 and the second actuator 41, ensuring the cambering of the structure can be an actuator that contracts when supplied with a fluid, such as an artificial muscle, in particular a pneumatic muscle. Such an actuator has been described previously and will not be reinvented. It has an envelope that receives a balloon inside, through which fluid is supplied or discharged. This flexible envelope contracts in length when the fluid supplied to the balloon increases (the muscle contracts) and its cross section increases, and expands in length when the fluid is discharged from the balloon (the fluid pressure decreases) and its cross section decreases. The contraction of the actuator can be gradual by controlling the amount of fluid supplied to the balloon. The actuator (in particular the first or second) can also be a pneumatic cylinder.

[0082] According to one embodiment, the artificial muscles of the actuators 40, 41 and / or of the actuating members m of the segments are supplied with fluid by one or more flexible elastic hoses AL1, AL2, AL3 shaped in the shape of a coil (not shown) that extend in the height direction of the mast M. The flexible elastic hoses are configured to be deployed by moving the windings of the coil apart in the deployed position of the profiled wing, and to be contracted by moving the windings of the coil closer to each other due to the elasticity of the coil in the retracted position P2 of the profiled wing AP.

[0083] According to one embodiment, the various telescopic segments SG, in particular the various associated semi-rigid structures, in said deployed position P1 have dimensions that decrease in accordance with the height of the mast M (in particular in the direction perpendicular to the mast), such that in the deployed position an upper telescopic segment is inserted into a lower telescopic segment, in said stored position P2, in which the various telescopic segments are nested with respect to one another.

[0084] In general, the at least one actuator 40, 41 and / or the first and second tightening actuation members m1 and m2 are arranged in a semi-rigid configuration, preferably at the lower end of the telescopic segment SG, such that in the retracted position P2, the at least one actuator and / or the first and second tightening actuation members m1 and m2 can telescope the various segments SG together without creating an obstacle that would substantially limit the retraction of the segments, by maximizing the intertwining between the segments and the vertical compactness of the profiled wings in the retracted position P2.

[0085] In general, the profiled wing system may comprise guide means between successive telescopic segments, including at least one first guide element GD1 extending along the height of the lower, telescopic segment SG and preferably internal to the semi-rigid structure 2 of that telescopic segment, which during guiding cooperates with at least one second guide element GD2, preferably external to the lower part of the upper telescopic segment.

[0086] The second guide element GD2 cooperates with the guide element GD1 along the limited travel during guiding to ensure sliding of the profiled wing AP between the retracted position P2 and the deployed position P1 between two successive telescopic segments. The profiled wing system AP preferably comprises multiple pairs of first guide element GD1 / second guide element GD1, which are distributed over a first length section 20 of two successive segments and over a second length section 21 of two successive segments. The first guide element GD1 is a longitudinally flexible element and the second guide element GD2 is a loop sliding on the longitudinally flexible element.

[0087] Generally, the various telescopic segments SG include a top telescopic segment SGT which constitutes the uppermost telescopic segment of the profiled wing AP in the deployed position P1, and a bottom telescopic segment SGP which is integrated into the lower part of the mast and constitutes the lowermost telescopic segment in the deployed position P1.

[0088] The top telescopic segment SGT is connected to a hoisting halyard DR which is supported on the boom POT at the top of the mast M. The halyard is configured to securely deploy the various telescopic segments from a stowed position P2 to a deployed position P1 of said profiled wing AP.

[0089] The bottom telescopic segment SGP is preferably connected to the mast via an adjustment device configured to ensure the orientation of the profiled wing AP around the mast M. Such an adjustment device comprises a mechanism 5 for adjusting the orientation of the bottom telescopic segment SGP around the mast M.

[0090] The mechanism 5 for adjusting the orientation of the bottom telescopic segment SGP around the mast M comprises: a first part 51 rotatably connected to the mast M, whereby there is no possibility of rotation between the first part 51 and the mast M; a second part 52 fixed to the semi-rigid structure of the bottom telescoping segment via a spacer system 3 of the bottom telescoping segment, the spacer being hinged and interconnecting the first length section 20 and the second length section 21; a mechanical transmission 6, preferably electrically driven, ensuring adjustment of the rotational position of the second part 52 around the first part 51; may include:

[0091] The spacer system may include a first spacer 30, a second spacer 31, and a third spacer 33. It should be noted that the first spacer 30 and the second spacer 31 are hinged at their center on the second portion 52 via an axis pivot that is typically substantially parallel to the mast. The third spacer 33 is hinged to the second portion 52 via, for example, a ball-and-socket connection.

[0092] Generally, the mechanical transmission 6 is a ring gear 60 rotatably connected to the first portion; an electric pinion 61 embedded in the second part; a toothed belt 62 connecting the ring gear 60 to the electric pinion 61; may include:

[0093] The mechanical transmission 6 is therefore configured to cause rotation of the second part 52 relative to the first part 51 by changing the orientation of the bottom telescopic segment SGP around the mast M by rotation of the motorized pinion.

[0094] The first part 51, which is rotatably connected to the mast, can optionally slide relative to the mast, with a movement limited to lowering, to store the profiled wing in its stored position in a formwork preferably located below the upper deck PTA, or conversely, during ascent, to extend the stored wing from the formwork and position it above the upper deck PT of the ship.

[0095] The present disclosure further relates to a watercraft-like vehicle including wind propulsion including at least one telescoping profiled wing system according to the present disclosure.

[0096] The vehicle may be, for example, a monohull or multihull vessel, including an upper deck above which a mast M extends at least partially, and the profiled wing is in the deployed position P1, from a bottom, lower telescopic segment SGP, to a top, upper telescopic segment SGT.

[0097] According to one embodiment, the mast extends below the upper deck PT through a formwork, the mast being fixed to the ship's structure below the level of the formwork, the formwork being arranged below the level of the upper deck, in such a case the telescopic wings, then in the retracted position, are configured to be lowered through an opening in the upper deck below the upper deck PT and stored in the formwork.

[0098] The cover system CV can be configured to close the upper opening in the retracted and stowed position P1 of the telescoping wing AP within the formwork. The cover system CV can also be configured to close the opening in the upper deck PT in the deployed position P1 of the telescoping wing AP, the profiled wing then being outside the formwork. In this latter closed position, the cover system can be placed on the mast, remote from and above its anchoring to the ship made below the formwork. Supporting the cover system on the mast in this way improves the mast's retention and resistance to bending due to the force of the profiled wing. [Explanation of symbols]

[0099] 1 Profiled Wing System 2 Semi-rigid structure 20, 21 First length section and second length section 22 U-shaped connecting section 23, 34 free ends of the first and second sections, respectively 3 Spacer System 30, 31 First spacer and second spacer 33 Third Spacer 32 connectors 4. Operating means 40, 41 Actuators, first and second 42 Medial tendon 5. Mechanism for adjusting the orientation of the bottom telescopic segment (SGP) around the mast 51, 52 First part and second part 6. Mechanical Transmission 60, 61, 62 Ring gear, electric gear and toothed belt (mechanical transmission) respectively 7. Fastening system (for blocking and fastening the segments on the mast) 71, 72 First and second strands AP Profiled Wing AS Semi-rigid structure symmetry plane B Balloon (artificial muscle) Ev envelope (especially braided) BA leading edge BF trailing edge Ev envelope d. Displacement between the two free ends m, m1, m2 each at least one tightening actuation member, first and second tightening actuation members Pr rest position Pc1 First camber position Pc2 Second camber position

Claims

1. A telescoping profiled wing system (1) for propelling a vehicle by wind power, comprising a mast (M) and a set of telescoping segments (SG) that cooperate with each other during guidance; the telescopic segments are configured to form profiled wings at least in a deployed position (P1), in which the various telescopic segments extend relative to one another in the direction of the mast (M) by forming the profiled wings (AP), the profiled wings having first wing surfaces (S1) and second wing surfaces (S2) distributed on both sides of the mast (M), and the system is configured to switch from the deployed position (P1) to a stowed position (P2) in which the various segments (SG) are nested together, the profiled wings (AP) being in a position that occupies less space compared to the deployed position, The telescoping segments each include an elastically deformable, semi-rigid structure (2) extending along a dimension forming the length of the telescoping segment in the direction of the mast, the semi-rigid structure (2) comprising: two length sections extending one behind the other, the first length section (20) forming a first surface (S1) of the profiled wing, and the second length section (21) fixed to the second surface (S2) of the profiled wing (AP) forming the second surface (S2) of the profiled wing; a U-shaped connecting section (22) that interconnects the first length section (20) and the second length section (21) by extending them at the leading edge (BA) of the profiled wing, the two length sections terminating at the trailing edge (BF) of the sail by two free ends (23, 24); Including, the system comprises, for all or part of the telescopic segment, actuation means (4) interconnecting, on the one hand, at least one of the two free ends (23, 24) and, on the other hand, the U-shaped connecting section (22), the actuation means (4) being configured to apply tension to one of the two free ends (23, 24) at the U-shaped connecting section (22) of the semi-rigid structure (2) to generate a displacement (d) between the two free ends (23, 24), thereby deflecting the first length section and the second length section of the semi-rigid structure; the first wing surface (S1) and the second wing surface (S2) of the profiled wing formed by the extension of the various telescopic segments are obtained by the semi-rigid extension structure (2); Telescopic profiled wing system.

2. the actuation means (4) configured to deflect the first and second length sections of the semi-rigid structure comprises at least one actuator (40, 41) having two longitudinal ends (40a, 41a, 40b, 41b), the actuator (40, 41) being actuatable and capable of contracting the two longitudinal ends toward each other when actuated, the at least one actuator (40, 41) extending along one of the two length sections of the semi-rigid structure, i.e., the first length section (20) or the second length section (21), the actuator (40, 41) being internal to the semi-rigid structure (2) and housed therein; 2. The profiled wing system according to claim 1, wherein one of the longitudinal ends (40a, 41a) of the at least one actuator (40, 41) is connected to one of the two free ends (23, 24), while the other of the two longitudinal ends (40b, 41b) of the at least one actuator (40, 41) is connected to at least one anchor point fixed to the U-shaped connecting section (22).

3. 3. The profiled wing system according to claim 2, wherein the actuators (40, 41) connect the anchor points of the U-shaped connecting sections to the free end of the first length section (20) according to a first possibility, or to the free end of the second length section (21) according to a second possibility, and bypass the mast (M) on the side opposite the first length section (20) according to the second possibility, or bypass the mast (M) on the side opposite the second length section (21) according to the second possibility.

4. The actuation means (4) may optionally include: At a first camber position (Pc1) where the first length section (20) has a concave profile when the second length section (21) has a convex profile, At a second camber position (Pc2) where the first length section (20) has a convex profile and the second length section (21) has a concave profile, 4. A profiled wing system according to any one of claims 1 to 3, configured to deflect the semi-rigid structure.

5. The at least one actuator of the actuation means a first actuator (40) configured to deflect the semi-rigid structure to the first deflection position (Pc1), one of its longitudinal ends (40a) being connected to the anchor point of the U-shaped section while the other longitudinal end (40b) is connected to a free end (24) of the second length section (21), the first actuator (40) being configured in an activated state to retract and pull the free end (24) connected by the first actuator (40) on the one hand and the at least one anchor point on the other hand until the displacement (d) occurs, the connected free end (24) advancing towards the leading edge (BA) relative to the other free end (23) by deflecting the semi-rigid structure, the first length section (20) adopting a concave profile and the second length section (21) adopting a convex profile in the first deflection position (Pc1); a second actuator (41) configured to deflect the semi-rigid structure to the second deflection position (Pc2), one of its free ends (41a) being connected to the anchor point of the U-shaped section while the other longitudinal end (41b) is connected to the free end (23) of the first length section (20), the second actuator (41) being configured in an activated state to retract and pull the free end (23) connected by the second actuator (41) on the one hand and the at least one anchor point on the other hand until the displacement (d) occurs, the connected free end (23) moving forward towards the leading edge (BA) relative to the other free end (24) by deflecting the semi-rigid structure, the second length section (21) adopting a concave profile and the first length section (20) adopting a convex profile in the second deflection position (Pc2); 5. The profiled wing system of claim 2, comprising:

6. Selectively, activating the first actuator (40) to cause the first bow position (Pc1) by keeping the second actuator (41) inactive; By keeping the first actuator (40) not activated, the second actuator (41) is activated to cause the second bow position (Pc2).

6. A profiled wing system (1) according to claim 5, comprising control means adapted to:

7. All or part of the telescopic wing segment (SG) has an activatable / deactivatable fastening system (7) configured to securely fasten the profiled wing (AP) on the mast, the fastening system (7) comprising: a first flexible strand (71) connected to the first length section (20) by two longitudinal ends of the first strand (71) and bypassing the mast (M) from the first length section (20); a second flexible strand (72) connected to the second length section (21) by its two longitudinal ends and bypassing the mast (M) from the second length section (21); an actuatable actuator system inside the structure configured to arrest the telescoping segment on the mast (M) inside the semi-rigid structure between the first strand (71) and the second strand (72) and switch the first and second strands (71) to a stowed state configured to hold the mast at a distance from the two length sections (20, 21) by the tensioned first and second strands (71) and to a deployed state of the first and second strands configured to release the mast, allowing movement of a cambering device along the mast; 7. A profiled wing system according to any one of claims 1 to 6, comprising:

8. The semi-rigid structure of the various telescopic segments comprises, in whole or in part, a spacer system (3) including a first spacer (30) interconnecting the first length section (20) and the second length section (21), and a second spacer (31) parallel to the first spacer (30) interconnecting the first length section (20) and the second length section (21); the longitudinal ends of the first strand (71) are fixed at two attachment points on the first length section (20) in the junction region between the first and second spacers (30, 31) and the first length section (20), respectively, and the longitudinal ends of the second strand (72) are fixed at two attachment points on the second length section (21) in the junction region between the first and second spacers (30, 31), respectively; 8. The system according to claim 7, wherein the mast (M) extends between the spacers consisting of the first spacer (30) and the second spacer (31), and the first strand (71) and the second strand (72) are fastened onto the mast and hold the mast securely at a distance from the first spacer (30) on the one hand and from the second spacer (31) on the other hand.

9. 9. The profiled wing system according to any one of claims 2, 3, 5 and / or 7 or 8, wherein the at least one tightening actuation member (m) of the anchoring system and / or the at least one actuator (40, 41) of the actuation means (4) is an artificial muscle that contracts when pressure is supplied by a fluid and relaxes when the fluid pressure decreases, the artificial muscle having an envelope that receives inside a balloon through which the fluid is supplied or discharged, the flexible envelope being in particular in the form of a braid and configured to contract in length when the fluid supplied to the balloon increases, thereby increasing its cross section, and to expand in length when the fluid is discharged from the balloon, thereby decreasing its cross section.

10. 10. A profiled wing system according to any one of claims 1 to 9, wherein the various telescopic segments (SG) in the deployed position (P1) decrease in size according to the height of the mast (M) such that in the deployed position an upper telescopic segment is inserted into a lower telescopic segment in the stored position (P2) where the various telescopic segments are nested relative to one another.

11. 11. The profiled wing system according to claim 1, further comprising guide means between successive telescopic segments, said guide means comprising at least one first guide element (GD1) extending along the height of the telescopic segment (SG) and below, preferably inside, the semi-rigid structure (2) of said telescopic segment, and cooperating during guiding with at least one second guide element (GD2) located below, preferably outside, the upper telescopic segment, said second guide element (GD2) cooperating during guiding with the first guide element (GD1) according to a limited movement to ensure sliding between the two successive telescopic segments between the stored position (P2) and the deployed position (P1) of the profiled wing (AP).

12. 12. A profiled wing system according to any one of claims 1 to 11, wherein the various telescopic segments comprise a top telescopic segment (SGT) which constitutes the uppermost telescopic segment in the deployed position (P1) of the profiled wing (AP) and a bottom telescopic segment (SGP) which is integrated into the lower part of the mast and constitutes the lowermost telescopic segment in the deployed position (P1), the top telescopic segment being connected to a hoisting halyard (DR) carried by a boom (POT) at the top of the mast (M), the halyard being configured to ensure the deployment of the various telescopic segments from the retracted position to the deployed position of the profiled wing (AP).

13. 13. The profiled wing system according to claim 12, wherein the bottom telescoping segment (SGP) is connected to the mast (M) through an adjustment device configured to ensure the orientation of the profiled wing around the mast (M), the adjustment device comprising a mechanism (5) for adjusting the orientation of the bottom telescoping segment (SGP) around the mast (M).

14. The mechanism (5) for adjusting the orientation of the bottom telescopic segment (SGP) around the mast (M) comprises: a first part (51) rotatably connected to the mast, whereby there is no possibility of rotation between the first part (51) and the mast (M); a second part (52) integral with the semi-rigid structure of the bottom telescoping segment via a system (3) of spacers of the bottom telescoping segment, the spacers being hinged and interconnecting the first length section (20) and the second length section (21); a mechanical transmission (6), preferably electric, ensuring adjustment of the rotational position of said second part (52) around said first part (51); 14. The telescoping wing system of claim 13, comprising:

15. The mechanical transmission (6) a ring gear (60) rotatably connected to the first portion; an electric pinion (61) embedded in the second part; a toothed belt (62) connecting the ring gear (60) to the electric pinion (61); Including, The transmission is configured such that rotation of the motorized pinion causes rotation of the second part (52) relative to the first part (51) by changing the orientation of the bottom telescopic segment (SGP) around the mast (M).

15. The profiled wing system of claim 14.

16. 16. A vehicle such as a ship including wind propulsion comprising at least one telescoping wing system according to any one of claims 1 to 15.

17. 17. The vehicle of claim 16, wherein the vehicle is a watercraft including an upper deck above which the mast extends, and the profiled wing in the deployed position from the bottom, lower telescoping segment to the top, upper telescoping segment.

18. 18. The vehicle of claim 17, wherein the mast extends below the upper deck (PT) through a formwork, the mast is fixed to the structure of the ship below the formwork, the formwork is positioned below the elevation of the upper deck, and the profiled wing in the stowed position is configured to be lowered below the upper deck (PT) through an opening in the upper deck and stored in the formwork.

19. 19. The vehicle of claim 18, comprising a cover system (CV) configured to close the upper opening by abutting against the mast in the retracted and stowed position (P2) of the profiled wing (AP) within the formwork and in the deployed position (P1) of the telescoping wing outside the formwork.

Images