Sail for a kite for pulling along a floating craft or a land vehicle

Abstract

The invention relates to a sail (5) for a kite (4) of a device (3) for pulling along a floating craft or a rolling and / or sliding land vehicle, in particular a flexible sail (5) with boxes, in particular with open or closed boxes, or with a simple skin, or with double surfaces, in particular a sail having cords or bridles which distribute a pulling force across a plurality of points attached to the lower surface of the sail, the sail extending over a length L, the sail (5) comprising retaining points (210) intended to cooperate with a launching line (20) to facilitate launching of the sail (5).

Description

[0001] DESCRIPTION

[0002] TITLE: Wing for a kite for traction of a floating boat or a land vehicle.

[0003] Technical field of the invention

[0004] The invention relates to a wing for a kite of a traction device of a floating vessel or a rolling and / or sliding land vehicle. The invention also relates to a traction device comprising such a wing. The invention also relates to a floating vessel or a rolling and / or sliding land vehicle comprising such a traction device or such a wing. The invention also relates to a method for operating such a traction device. The invention also relates to a traction device comprising hardware and / or software elements for implementing such a method. The invention also relates to a computer program comprising code instructions for implementing such a method. The invention also relates to a data storage medium for implementing such a method. The invention also relates to a signal of a data storage medium carrying such a computer program.

[0005] State of the prior art

[0006] A kite for towing a floating vessel, such as a boat or ship, is difficult to operate when launched from the deck of the floating vessel. Consequently, there is a significant risk of the kite being damaged at sea or by contact with the floating vessel or the ground during maneuvers. The classic launch of this type of kite requires an inflation phase and the complete unwinding of the lines intended to mechanically attach it to the floating vessel. This is possible on land but much more difficult at sea. One solution is to let the kite drift on the surface of the water and take off once the lines are unwound. Another solution is to use a specific boat to take off in the wind and, a fortiori, to recover it.Other solutions use a launch mast to hoist and hold the kite in its take-off phase, but the wind variations caused by the ship's movements disrupt inflation and take-off. Such solutions are not satisfactory.

[0007] Presentation of the invention

[0008] The invention relates to a wing that overcomes the above drawbacks. In particular, the invention makes it possible to do without a kite launch mast, secures and stabilizes the flight of the kite during this critical phase of take-off and gaining altitude necessary for towing a floating boat or a rolling and / or sliding land vehicle.

[0009] Summary of the invention

[0010] To achieve this objective, the invention relates to a wing for a kite of a traction device of a floating boat or of a rolling and / or sliding land vehicle, in particular a flexible wing with boxes, in particular with open or closed boxes, or with a single skin, or with double surfaces, in particular a wing having lines or bridles which distribute a traction force in several points attached to the lower surface of the wing, the wing extending over a length, the wing comprising retaining points intended to cooperate with a launch line to facilitate the take-off of the wing.

[0011] The retaining points can be distributed along the length of the wing, especially distributed regularly.

[0012] The kite may include a leading edge and the retaining points may be arranged at a lower area of ​​the leading edge. The kite may include sliding means for such a throwing line at each retaining point, such as an eyelet or carabiner or a loop or pulley.

[0013] The wing may comprise a first wing anchor point and a second wing anchor point, in particular a first and a second wing anchor point arranged substantially at the ends of the wing along its length.

[0014] The invention also relates to a traction device for a floating vessel or a rolling and / or sliding land vehicle comprising a wing as defined above, the traction device comprising:

[0015] - a launch line,

[0016] - a first wing control line connected to the first wing anchor point,

[0017] - a second wing control line connected to the second wing anchor point, the launch line passing through each retaining point and / or being releasably attached to each retaining point.

[0018] The invention also relates to a traction device for a floating vessel or a rolling and / or sliding land vehicle comprising a wing as defined above, the traction device comprising:

[0019] - a single launch line,

[0020] - a first wing control line connected to the first wing anchor point,

[0021] - a second wing control line connected to the second wing anchor point, the single launch line being able to pass through each retaining point and / or be releasably attached to each retaining point. The invention also relates to a traction device for a floating boat or a rolling and / or sliding land vehicle comprising a wing as defined above, the traction device comprising:

[0022] - a single launch line,

[0023] - a first wing control line connected to the first wing anchor point,

[0024] - a second wing control line connected to the second wing anchor point, the single launch line being able to reach each retaining point.

[0025] The traction device may comprise a plate, in particular a plate comprising at least one pulley and / or holes crossed by the throwing line.

[0026] The invention also relates to a floating vessel comprising a traction device as defined previously, comprising a deck comprising a first means for attaching the first control line and a second means for attaching the second control line, the first means of attachment and the second means of attachment being distant from each other by a given value, in particular by more or less 20 percent of two-thirds of the length of the wing.

[0027] The invention also relates to a rolling and / or sliding land vehicle comprising a traction device as defined above, comprising a chassis comprising a first means for attaching the first control line and a second means for attaching the second control line, the first attachment means and the second attachment means being distant from each other by a given value, in particular by more or less 20 percent of two-thirds of the length of the wing. The invention also relates to a method for operating a traction device as defined above, the method comprising the following steps:

[0028] - retain the wing on the floating craft or on the craft by the first anchor point and by at least the retaining point closest to the first anchor point, preferably retain the wing on the floating craft or on the craft by one anchor point and by all the retaining points,

[0029] - release the wing so as to gradually release it at the retaining points so that the wing inflates and / or takes off, the release taking place progressively retaining point after retaining point, moving away from the first anchoring point and approaching the second anchoring point, until the wing is retained only by the first and second anchoring points.

[0030] The release may be controlled, in particular by automatic means by friction, or by automatic means by cruise control, or by manual means, or by a brake.

[0031] The traction device may comprise hardware and / or software elements implementing the method as defined previously, in particular hardware and / or software elements designed to implement the method as defined previously, and / or the device may comprise means for implementing the method as defined previously.

[0032] The invention also relates to a computer program product comprising program code instructions recorded on a computer-readable medium for implementing the steps of the method as defined above when said program operates on a computer or computer program product downloadable from a communication network and / or recorded on a data medium readable by a computer and / or executable by a computer, comprising instructions which, when the program is executed by the computer, lead the latter to implement the method as defined above.

[0033] The invention also relates to a data recording medium, readable by a computer, on which is recorded a computer program comprising program code instructions for implementing the method as defined above or a computer-readable recording medium comprising instructions which, when executed by a computer, cause the latter to implement the method as defined above.

[0034] The invention also relates to a signal of a data medium, carrying the computer program product as defined previously.

[0035] Presentation of figures

[0036] Other advantages and characteristics will emerge more clearly from the following description of an embodiment of a kite wing for a floating craft or a rolling and / or sliding land vehicle and of an embodiment of a method of operating a traction device, and from the appended figures, in which:

[0037] Figure 1 is a partial schematic view of a floating vessel according to one embodiment.

[0038] Figure 2 is a schematic view of a rolling and / or sliding land vehicle according to one embodiment.

[0039] Figure 3 is a schematic sectional view of a single-skin kite wing according to the embodiment.

[0040] Figure 4 is a schematic sectional view of a double-skin kite wing according to the embodiment.

[0041] Figure 5 is a schematic sectional view of a hybrid kite wing according to the embodiment.

[0042] Figure 6 is a bottom view of a kite according to the embodiment. Figure 7 is a view of a traction device according to an embodiment during takeoff of its kite kite.

[0043] Figure 8 is a view of a first phase of launching the wing according to the embodiment.

[0044] Figure 9 is a view of a second phase of launching the wing according to the embodiment.

[0045] Figure 10 is a view of a third phase of launching the wing according to the embodiment.

[0046] Figure 11 is a view of a fourth phase of launching the wing according to the embodiment.

[0047] Figure 12 is a view of a fifth phase of launching the wing according to the embodiment.

[0048] Figure 13 is a superposition of launch phases of a wing according to an alternative embodiment.

[0049] Detailed description

[0050] The direction in which a floating vessel moves in a straight line, in a plane parallel to the water level of a body of water, is defined as the longitudinal direction. By convention, the direction perpendicular to the longitudinal direction, located in a plane parallel to the water level of a body of water, is called the transverse direction. The third direction, perpendicular to the other two, is called the vertical direction.

[0051] Figure 1 schematically illustrates a floating vessel 1. Such a floating vessel 1 is, for example, a boat or a ship.

[0052] Figure 2 schematically illustrates a rolling and / or sliding land vehicle 2. Such a vehicle is, for example, a vehicle intended to be used on a frozen body of water and / or on sand and / or on snow and / or on grass and / or on earth. The floating vessel 1, or the rolling and / or sliding land vehicle 2, comprises a traction device 3.

[0053] The traction device 3 comprises a kite 4. The kite 4 comprises, or includes, a wing 5. The wing 5 is provided with a leading edge 6 or comprises a leading edge 6.

[0054] The traction device 3 of the floating boat 1 or of the rolling and / or sliding land vehicle 2 also comprises a launching line 20 illustrated in particular in FIG. 7. The traction device 3 also comprises a first anchoring point 11 of the wing 5 and a second anchoring point 12 of the wing 5. The traction device 3 also comprises a first control line 21 of the wing 5 connected to the first anchoring point 11 of the wing 5 and a second control line 22 of the wing 5 connected to the second anchoring point 12 of the wing 5.

[0055] As illustrated in Figure 3, the wing 5 is for example of the single-skin or single-skin type 51. In this case, the single skin 51 extends to form the upper surface and the leading edge 6.

[0056] As illustrated in Figure 4, the wing 5 is for example of the double-skin 52 or double-surface type. In this case, for example, one skin extends to form the upper surface and another skin extends to form the lower surface. For example, these two skins join and thus form only one skin delimiting a volume between them. The skin of the lower surface and / or the skin of the upper surface forms the leading edge 6.

[0057] As illustrated in Figure 5, the wing 5 is for example of the hybrid type, namely comprising a main skin forming the upper surface and a secondary skin closing the volume of the leading edge on the lower surface. For example, these two skins meet before the trailing edge and thus form only one skin delimiting a volume between them. For example, the wing 5 comprises boxes or cells or compartments. As illustrated in Figures 4, 5 and 6, air inlets 55 may be provided at the leading edge 6 so as to supply air to the cells, in particular taking into account the air flow or wind V (arrow). In addition, such cells may be open or closed, in particular by means of valves or valves (not illustrated).

[0058] Optionally, the wing 5, or the kite 4, comprises suspension lines 56, in particular of the rope type, optionally connected to each other by one or more bridles.

[0059] Preferably wing 5 is flexible.

[0060] More precisely, as illustrated in Figures 6 and 7 by a double arrow, the wing 5 extends over a length L.

[0061] The wing 5 further comprises retaining points 210 illustrated in particular in FIGS. 3, 4, 5, 6 and 7. The retaining points 210 are intended to cooperate with a launch line 20. The cooperation of the retaining points with the launch line 20 makes it easier to take off the wing 5 from the kite as will be seen later. Preferably, the retaining points 210 are distributed along the length L of the wing 5. For example, the retaining points 210 are distributed regularly along the length L.

[0062] By "regularly" is meant that in the case of n retaining points to be distributed over the length L, the length L is divided into n+1 segments or arcs of the same length allowing the locations of the n retaining points to be positioned. Preferably, no retaining point is provided at each end of the length L. Indeed, preferably, anchor points 1 1 , 12 are provided at the ends of the wing or in the vicinity of the end of the wing.

[0063] More specifically, as illustrated in Figures 3, 4, 5 and 6, the leading edge 6 comprises a lower zone 7. The retaining points 210 are preferably arranged at the lower zone 7 of the leading edge 6. The retaining or attachment points 210 for launching are substantially arranged on a front quarter of the profile of the intrados, that is to say the first quarter with respect to the direction of the wind V. In the case of air inlet 55 as illustrated in Figures 4, 5 and 6, the retaining points are arranged behind the air inlets with respect to the direction of the wind V.

[0064] As illustrated in Figures 3, 4, 5, 6 and 7, the wing 5 comprises a sliding means 220 at each retaining point 210. In other words, the attachment points 210 are equipped with a sliding means 220 in order to ensure the sliding of the launching lines. Each sliding means 220 allows the passage of the launching line 20 if necessary. For example, the sliding means 220 is, or comprises, an eyelet, a carabiner, a loop, a friction ring, or even a diabolo or a pulley.

[0065] As illustrated in Figure 7, the wing 5 comprises the first anchoring point 11 of the wing 5 and the second anchoring point 12 of the wing 5. Preferably, the first and second anchoring points 11, 12 of the wing are arranged substantially at the ends of the wing 5 along its length L.

[0066] Advantageously, a single launch line 20 joins the retaining points 210, for example by doubling them and / or connecting them by a flange or a set of flanges. In other words, the single launch line 20 passes through each retaining point 210, and / or joins each retaining point. The single launch line 20 is fixed, or is optionally fixed, in a releasable manner to each retaining point 210 or at each retaining point. In the case of sliding means 220, the launch line 20 slides in each sliding means.

[0067] Preferably, as illustrated in Figure 7, the traction device 3 comprises a plate or flange 30. For example, the plate 30 comprises at least one pulley and / or holes crossed by the launch line 20. The launch line 20 is for example fixed to the plate 30 at one end of the launch line 20 while the rest of the launch line is free.Thus, the free part of the launch line joins a retaining point 216, then returns to the plate 30, then joins a retaining point 215, then returns to the plate 30, then joins a retaining point 214, then returns to the plate 30, then joins a retaining point 213, then returns to the plate 30, then joins a retaining point 212, then returns to the plate 30, then joins a retaining point 211, then returns to the plate 30, extending with sufficient length so that an operator, or an actuator 32, can release it little by little so as to ensure the smooth takeoff of the wing 4. For example, a hole or eyelet or loop or pulley 31 is arranged at the plate 30 to ensure the deployment or release of the length of the launch line during takeoff. In other words, the lacing line(s) connect(s) the launching points 210 to the plate 30 for concentrating and / or hauling the launching line(s).In the case of a single continuous launch line, it is fixed to the plate and extends from the plate to a first launch point, returns to the plate before joining a second launch point and so on until the nth launch point before joining the plate by crossing it in order to be able to relax the continuous line as will be seen later.

[0068] As illustrated in Figures 1, 2 and 7, the floating craft, respectively the rolling and / or sliding land craft, comprising the traction device 3 further comprises a deck 8, respectively a chassis 9. The deck or the chassis comprises a first attachment means 23 of the first control line 21 and a second attachment means 24 of the second control line 22. Preferably, the first attachment means 23 and the second attachment means 24 are distant from each other by two-thirds of the length L or the span of the wing 5, at least by plus or minus 20 percent of two-thirds of the length L. Preferably, an axis passing through the first attachment means 23 and the second attachment means 24 fixed on the deck 8 or the chassis 9 is perpendicular or substantially perpendicular to the direction of the wind during takeoff.

[0069] Advantageously, the first and second attachment means 23, 24 are mobile, in particular pivoting around a vertical axis arranged substantially between the first and second means 23, 24 so as to be able to orient the axis passing through the means 23, 24 relative to the direction of the wind.

[0070] Preferably, as illustrated in Figures 1 and 2, the floating vessel or the rolling and / or sliding land vehicle comprises a computer program product 100 comprising program code instructions recorded on a computer-readable medium for implementing the steps of the method which will be described later. More preferably, the floating vessel or the rolling and / or sliding land vehicle comprises a data recording medium 101, readable by a computer, on which is recorded a computer program comprising program code instructions for implementing the method which will be described later. The computer program product 100 comprises at least one signal 102 from the data medium 101.

[0071] An embodiment of a method of operation of the traction device 3 aimed at making the wing 5 take off will now be described in relation to figures 8, 9, 10, 11 and 12 illustrating the inflation and progressive take off by a wing lug. For example, the kite comprises a leading edge with closed boxes with a single-skin upper surface, without bridle.

[0072] First, the wing 5 preferably remains folded, preferably in the manner of an accordion, for example in a bag or a net (not shown), for example by being placed on the deck 8 or the frame 9. The launch line 20 is wound for example so that it can be unwound during the take-off process. The first control line 21 connects the first attachment means 23 to the first anchoring point 11 of the wing 5. The second control line 22 connects the second attachment means 24 to the second anchoring point 12 of the wing 5. As a reminder, preferably, the first and second lines 21, 22 pass through the first and second attachment means 23, 24 substantially aligned on an axis perpendicular to the wind and spaced apart by approximately two-thirds of the wingspan of the kite.The second control line 22 is loose (because the wing portion near the second anchor point will only be subjected to the wind at the end of launch or takeoff), possibly wound so as not to hinder the launch process. As illustrated in FIG. 8, the first control line 21 is taut or substantially taut. At least, the first control line 21 is not loose and it holds the first anchor point 11. The launch line 20 which connects the different attachment points 210 and the plate 30 is shortened as much as possible so as to keep the wing folded, partly held, for example in the bag.

[0073] The first control line 21 is pulled, which has the effect of gradually deploying the wing 5 by approaching the first anchoring point 11 of the first attachment means 23 at which the first control line 21 slides, as illustrated in Figures 8 and 9. Thus, the wing 5 is retained on the floating craft or on the craft by the first anchoring point 11 via the first control line 21 and the wing 5 is retained by at least the retaining point 211 closest to the first anchoring point 11, as illustrated in Figure 10. Note that the retaining point 211 is retained by the launch line 20, preferably via a crossing within the plate 30 as illustrated in Figure 5. Thus, Figures 8, 9 and 10 illustrate the main pull line or first control line 21, on the side opposite that of the bag, gradually stretched and blocked while waiting for complete takeoff.This has the effect of stretching the wingtip between the nearest holding point 210 by the lines 56 and the concentration plate 30.

[0074] Then we unroll the launch line 20. The holding points 21 1,

[0075] 212, 213 of the wing 5 held by the launch line 20 are released gradually so as to gradually deploy the wing 5, to make it take the wind and / or to inflate it without jolts or high and / or sudden tension. In the case illustrated in Figures 7 to 12, the single launch line 20 goes back and forth between each retention point and the plate 30. Indeed, as seen previously, the launch line 20 passes through the plate 30, joins and passes at the level of the retention point 21 1 , then joins the plate 30, then joins and passes at the level of the retention point 212, then joins the plate 30, then joins and passes at the level of the retention point

[0076] 213, then joins the plate 30, then joins and passes at the level of the retaining point 214, then joins the plate 30, then joins and passes at the level of the retaining point 215, then joins the plate 30, then joins and passes at the level of the retaining point 216 then joins the plate 30. By "joining" or "passing through" the plate 30, it is meant that the line crosses the plate or approaches at the level of the plate, for example via a carabiner or other sliding means allowing the passage of the launch line 30. Thus, the retaining point 21 1 is first released, before releasing the retaining point 212, before releasing the retaining point 213, before releasing the retaining point 213, before releasing the retaining point 214, before releasing the retaining point 215, before releasing the retaining point 216.More precisely, a progressive release of the launch line is created step by step, by maintaining a release at the level of the retaining point 21 1 , greater than that of the retaining point 212, itself greater than that of the retaining point 213, itself greater than that of the retaining point 214, itself greater than that of the retaining point 215, itself greater than that of the retaining point 215. Preferably, the friction of the launch line 20 at the level of each retaining point and / or at the level of the plate participates in the regulation of the progressive release of the retaining points.

[0077] Optionally, the release of the launch line 20 is controlled, for example by automatic friction means, or by automatic speed regulator means, or by manual means, or by a brake.

[0078] Once all the retaining points have been released by the unwinding of the launch line 20, the wing 5 is retained on the floating craft or on the machine by the first anchoring point 11 and by all the retaining points, as illustrated in figure 11 (only three retaining points are illustrated).

[0079] The wing is then released so as to gradually release it at the retaining points so that the wing inflates and / or takes off. Preferably, the release is carried out gradually retaining point after retaining point, moving away from the first anchoring point 11 and approaching the second anchoring point 12, until the wing is retained only by the first and second anchoring points 11, 12. The wing 5 is retained by the first control line 21 on the first anchoring point 11 and by the second control line 22 on the second anchoring point 12, as illustrated in FIG. 12. The launch line 20 is then kept loose, or even released from the retaining points if this is possible at the sliding means 220 provided at each retaining point.

[0080] Advantageously, to ensure the recovery of the wing 5 after a flight and / or traction phase, the launch line 20 is pulled, possibly after having pulled the second control line 22, so as to bring the retaining points closer to each other and then the first control line 21 is left substantially loose so as to allow the wing to be repatriated, for example at the level of the second attachment means 24. Advantageously again, the wing is folded in the manner of an accordion so that the retaining points are close to each other, in preparation for the next takeoff.

[0081] In summary, as illustrated in Figures 3, 4 and 5, the positioning of the retention points 210 or attachment points of the launch lines, i.e. the connection points of the launch line(s) on the wing, allow inflation and stable flight, in particular at high incidence. In addition, this positioning ensures takeoffs of the wing 5 without stalling. The distribution of the retention points 210 along the length L illustrated in Figure 6 makes it possible to distribute the forces on the wing 5 in a homogeneous manner. This makes it possible, for example, to maintain a given wing shape during launch and / or to avoid folds and / or breaks, in particular at the leading edge 6 of the wing 5. As a reminder, advantageously, the retention points 210 are arranged behind or substantially behind any air inlets 55 relative to the wind direction V.Finally, the positioning of the retaining points 210 at the level of ribs and / or structural reinforcements makes it possible to transmit the tension of the lines to the upper surface of the wing profile. The number of retaining points preferably varies, for example, depending on the size of the kite 4, in particular depending on its wing, in particular its length L or its wingspan.

[0082] Preferably, as illustrated in Figures 7 to 12, a single launch line 20, i.e. a single rope or cord or link is provided. Advantageously, as seen previously, the launch line cooperates with the plate 30 preferably provided with hauling means, and / or holes or orifices. The cooperation of the plate with a single launch line allows the wing to take off smoothly and evenly, step by step, leaving more and more length to the launch line. For this, the length of the launch line is freed, for example by unwinding it if it is rolled up, preferably via a loop 31 on the plate 30 (Figure 7). Thanks to the distribution of the retaining points 21 1 , 212, 213, 214, 215, 216 and the launch line 20 cooperating with them via the plate 30, the take-off and / or inflation of the wing 5 can be done little by little, for example without jolts.In addition, the plate and / or a hauling system makes it possible to significantly reduce the forces required to gradually release slack from the launch line. In other words, the hauling system makes it possible to limit the force required to retain the launch line during takeoff of the wing 5 by multiplying the forces. A single person is then able to gradually release the launch line if necessary. In the case of automation, the actuator 32 only needs a low torque to gradually release the launch line 20. This results in low energy consumption by such an actuator.

[0083] In other words, the plate 30 makes it possible to release, in particular to control the sliding, manually or mechanically, during the take-off phase of lines which can be advantageously grouped into a single continuous line. As an alternative to the single launch line 20, each retaining point 21 1 , 212, 213, 214, 215, 216 can be retained by a specific line. Consequently, with such a structure, the step of progressive release of the wing can be implemented in a different way. For example, one can completely release the retaining point 211, then completely release the retaining point 212, then completely release the retaining point 213, then completely release the retaining point 214, then completely release the retaining point 215 and finally completely release the retaining point 216. According to this alternative, the wing is also gradually released at the retaining points 210 so that it inflates and / or takes off.The release is also carried out progressively, holding point after holding point moving away from the first anchor point 11 and approaching the second anchor point 12, until the wing is held only by the first and second anchor points 11, 12.

[0084] Advantageously, as illustrated in Figure 7, the plate 30 is attached substantially to the first attachment means 23 or to the second attachment means 24, that is to say at or near one of the control and / or main traction lines of the kite. The location of the plate is preferably determined as a function of the control line 21, 22 defined as optimal for launching.

[0085] Thanks to the solution, at the start of deployment of the wing, the tension of the first control line 21 makes it possible to present the possible air inlet(s) to the wind, and / or to gradually inflate the leading edge, as illustrated in Figures 9 and 10. Thus maintained, the deformed profile of the wing, especially behind the leading edge, which then possibly flaps under the influence of the wind, allows a high angle of incidence with low traction and excellent stability. By alternately releasing the lines, or advantageously a single line continuously via the launch line 20, the kite gradually takes its shape and takes off as illustrated in Figures 11 and 12.

[0086] Alternatively, Figure 13 schematically illustrates a variant of the launch sequence adapted to the wings 50 held by a set of suspension lines by joining take-off bridles. Two traction or launch lines 200 each fixed to one end of each ear of the wing 50 make it possible to gain altitude gradually, with lateral self-stability resulting from the separation of the two attachment means 230, 240 or traction points on the boat or land vehicle and the deformed profile, until the main restraint with the traction lines are taut and operational. The two traction lines 200 for take-off can advantageously be released after use.

[0087] Although all the temporary 560 supports or bridles intended for inflation and take-off can be removed after use, they can advantageously remain in place and allow descent, landing and partial folding of the wing, by gradually re-tensioning them.

[0088] In summary, the solution involves a system of additional suspension lines, preferably connected to the same launch line, permanent or temporary, usable on all types of kite, for example flexible box kite, single skin kite, double skin kite, open or closed box kite, held or not by bridle. The solution allows easy deployment of the kite from the ground or from the deck of a ship and / or allows recovery by providing self-stability. Such stability specific to the kite makes it possible to limit, or even eliminate, the need to pilot it.

[0089] Thanks to the solution, a wing of a large kite can be easily launched. Furthermore, the effort required to initiate takeoff, for example manually, is low. Furthermore, the movements are simple to perform. This results in increased safety, particularly during the takeoff phase. Finally, the solution ensures improved stability of the kite, particularly during the inflation and takeoff phase.

[0090] As a note, the solution therefore achieves the desired objective of facilitating the inflation and launching of a kite, in particular intended to tow a floating craft, while improving stability and safety in this critical phase of flight, but also the recovery of the kite and presents the following advantages:

[0091] - it is economical,

[0092] - it is easy to install on a boat or land vehicle.

Claims

CLAIMS 1. Wing (5) for a kite (4) of a traction device (3) of a floating boat (1) or of a rolling and / or sliding land vehicle (2), in particular a flexible wing (5) with boxes, in particular with open or closed boxes, or with a single skin, or with double surfaces, in particular a wing having lines or bridles (56) which distribute a traction force at several points attached to the lower surface of the wing, the wing (5) extending over a length (L), characterized in that the wing (5) comprises retaining points (210) intended to cooperate with a launch line (20) to facilitate the take-off of the wing (5).

2. Wing (5) according to the preceding claim, characterized in that the retaining points (210) are distributed along the length (L) of the wing (5), in particular distributed regularly.

3. Wing (5) according to one of the preceding claims, characterized in that the wing (5) comprises a leading edge (6) and in that the retaining points (210) are arranged at a lower zone (7) of the leading edge (6).

4. Wing (5) according to one of the preceding claims, characterized in that the wing (5) comprises a sliding means (220) for such a throwing line (20) at each retaining point (210), in particular an eyelet or a carabiner or a loop or a pulley.

5. Wing (5) according to one of the preceding claims, characterized in that the wing (5) comprises a first anchoring point (11) of the wing (5) and a second anchoring point (12) of the wing (5), in particular a first and a second anchoring point (11, 12) of the wing arranged substantially at the ends of the wing (5) along its length (L).

6. Traction device (3) for a floating vessel (1) or a rolling and / or sliding land vehicle (2) comprising a wing (5) according to the preceding claim, characterized in that the traction device (3) comprises: - a launch line (20), - a first control line (21) of the wing (5) connected to the first anchor point (11) of the wing (5), - a second control line (22) of the wing (5) connected to the second anchor point (12) of the wing (5), the launch line (20) passing through each retaining point (210) and / or being releasably attached to each retaining point (210). Traction device (3) of a floating boat (1) or a rolling and / or sliding land vehicle (2) comprising a wing (5) according to claim 5, characterized in that the traction device (3) comprises: - a single launch line (20), - a first control line (21) of the wing (5) connected to the first anchor point (11) of the wing (5), - a second control line (22) of the wing (5) connected to the second anchor point (12) of the wing (5), the single launch line (20) passing through each retaining point (210) and / or being releasably attached to each retaining point (210). Traction device (3) of a floating boat (1) or a rolling and / or sliding land vehicle (2) comprising a wing (5) according to claim 5, characterized in that the traction device (3) comprises: - a single launch line (20), - a first control line (21) of the wing (5) connected to the first anchor point (11) of the wing (5), - a second control line (22) of the wing (5) connected to the second anchor point (12) of the wing (5), the single launch line (20) joining each retaining point (210). Traction device (3) according to one of claims 6 to 8, characterized in that the traction device (3) comprises a plate (30), in particular a plate (30) comprising at least one block and / or holes crossed by the launching line (20). Floating boat (1) comprising a traction device (3) according to one of claims 6 to 9, characterized in that it comprises a deck (8) comprising a first attachment means (23) for the first control line (21) and a second attachment means (24) for the second control line (22), the first attachment means (23) and the second attachment means (24) being distant from each other by a given value, in particular by plus or minus 20 percent of two-thirds of the length (L) of the wing (5).Rolling and / or sliding land vehicle (2) comprising a traction device (3) according to one of claims 6 to 9, characterized in that it comprises a chassis (9) comprising a first attachment means (23) of the first control line (21) and a second attachment means (24) of the second control line (22), the first attachment means (23) and the second attachment means (24) being distant from each other by a given value, in particular by plus or minus 20 percent of two-thirds of the length (L) of the wing (5). Method of operating a traction device (3) according to one of claims 6 to 9, the method comprising the following steps:. - retaining the wing (5) on the floating vessel (1) or on the craft (2) by the first anchoring point (11) and by at least the retaining point (211) closest to the first anchoring point (11), preferably retaining the wing (5) on the floating vessel or on the craft by an anchoring point (11; 12) and by all the retaining points (210), - release the wing so as to gradually release it at the retaining points (210) so that the wing inflates and / or takes off, the release taking place gradually retaining point after point retaining device by moving away from the first anchoring point (1 1 ) and approaching the second anchoring point (12), until the wing is retained only by the first and second anchoring points (1 1 , 12). Method according to the preceding claim, characterized in that the release is controlled, in particular by automatic friction means, or by automatic speed regulator means, or by manual means, or by a brake. Traction device (3), characterized in that it comprises hardware and / or software elements implementing the method according to one of claims 12 or 13, in particular hardware and / or software elements designed to implement the method according to one of claims 12 or 13, and / or the device comprising means for implementing the method according to one of claims 12 or 13.Computer program product (100) comprising program code instructions recorded on a computer-readable medium for implementing the steps of the method according to any one of claims 12 or 13 when said program operates on a computer or computer program product downloadable from a communication network and / or recorded on a data medium readable by a computer and / or executable by a computer, characterized in that it comprises instructions which, when the program is executed by the computer, cause the latter to implement the method according to any one of claims 12 or 13.A computer-readable data storage medium (101) on which is recorded a computer program comprising program code instructions for implementing the method according to one of claims 12 or 13 or a computer-readable storage medium comprising instructions which, when executed by a computer,. lead the latter to implement the method according to any one of claims 12 or 13. Signal (102) from a data medium, carrying the computer program product (100) according to claim 15.

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