WO2011023908A1 - Wing having a flexible wing structure and controlled by moving the center of gravity - Google Patents

Wing having a flexible wing structure and controlled by moving the center of gravity Download PDF

Info

Publication number
WO2011023908A1
WO2011023908A1 PCT/FR2010/051777 FR2010051777W WO2011023908A1 WO 2011023908 A1 WO2011023908 A1 WO 2011023908A1 FR 2010051777 W FR2010051777 W FR 2010051777W WO 2011023908 A1 WO2011023908 A1 WO 2011023908A1
Authority
WO
WIPO (PCT)
Prior art keywords
wing
flexible
sail
flexible wing
spacing
Prior art date
Application number
PCT/FR2010/051777
Other languages
French (fr)
Inventor
Gilles Bru
Original Assignee
Air Creation
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Air Creation filed Critical Air Creation
Publication of WO2011023908A1 publication Critical patent/WO2011023908A1/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C31/00—Aircraft intended to be sustained without power plant; Powered hang-glider-type aircraft; Microlight-type aircraft
    • B64C31/028—Hang-glider-type aircraft; Microlight-type aircraft
    • B64C31/032—Hang-glider-type aircraft; Microlight-type aircraft having delta shaped wing

Definitions

  • the object of the invention relates to a wing with flexible wing driven by displacement of the center of gravity.
  • the object of the invention finds a particularly advantageous application for example for free flying wings or ultra-light motorized pendulum type.
  • the flying wings with flexible wing and control by displacement of the center of gravity do not have aerodynamic control surfaces.
  • the roll response of these flying wings is closely dependent on their flying speed ie low at low speed and high speed at high speed. Because of this characteristic, the flying wings which have a high speed range, have either a very poor handling at low speeds that do not allow their practical use, or a hypersensitivity in roll at high speed making the control delicate, even dangerous especially if yaw stability is low.
  • a wing with flexible wings controlled by displacement of the center of gravity comprises a flexible wing comprising a keel provided with two leading edge spars defining an arrow and two transverse spars extending between the keel and the leading edge spars.
  • a soft sail is stretched over the leading edge spars and the keel.
  • Leading edge spars are carried by connectors each mounted on a transverse spar. The position of the connectors along the transverse rails is adjustable to allow to modify before the flight phase, the shape of the wing.
  • Such a flexible wing does not make it possible to optimize the geometry of the wing as a function of the speed of flight, during the different flight phases of the wing.
  • trim systems in pitch to vary the cruising speed in flight.
  • trim systems trim systems
  • the various compensation systems used which are based on the principle of moving the attachment point of the tricycle are heavy and complex and generate significant pitching efforts or induce, for the simplest systems acting on the return strings, deterioration of the stall speed in slow configuration.
  • the object of the invention is therefore to overcome the drawbacks of the state of the art by proposing a wing with flexible wing driven by displacement of the center of gravity, this wing having a geometry which is adapted or optimized according to the speed of the wing during all phases of flight.
  • Another object of the invention is to provide a wing with flexible wing equipped with a simple system to adjust its speed and simultaneously adapt the geometry of the wing at this speed.
  • the object of the invention relates to a wing wing flexible controlled by displacement of the center of gravity comprising:
  • a flexible wing comprising a support keel provided with at least one leading edge spar delimiting an arrow, a flexible sail being stretched on the spar to define a leading edge and a trailing edge and on both sides, two half-sails,
  • the wing comprises:
  • a device for controlling in flight the system for modifying the transverse tension comprising a control member associated with the control structure.
  • the system for modifying the transverse tension comprises a mechanism for spacing and bringing the half-webs together to reduce or increase the transverse tension of the sail substantially at the trailing edge. when respectively the spacing or the approximation of the half-sails.
  • the spacing and approach mechanism acts on the two half-webs by means of two slats extending longitudinally substantially from the leading edge to the trailing edge and on either side of the keel. to extend in the central part of the flexible wing.
  • the flexible sail comprises from the spacing mechanism and approaching and towards the wingtips, transverse reinforcements on which acts the spacing mechanism and approach.
  • the wing comprises a safety member to limit the spacing between the two half-sails to a limit value.
  • the flexible sail comprises between the two half-sails, an elastic spacer compensation band.
  • the spacing and approach mechanism comprises hoists fixed on the half-sails while the control device comprises a cable actuating the hoists and mounted to a winder whose rotary control is provided by the control member.
  • the wing comprises a system for modifying the reflex of the profile of the flexible wing in the central part of the flexible wing.
  • the system for modifying the reflex of the profile of the flexible wing comprises a connecting member between the rear parts of the sail subjected to the spacing and approach mechanism, this connecting member passing below the keel so as to increase or reduce the reflex of the central profile of the flexible wing respectively at the approach or spacing of the two-half sails.
  • Another object of the invention is to propose an aircraft comprising a wing according to the invention, the steering structure of which comprises a tricycle hooked to the keel.
  • Figures 1 and 2 are perspective views respectively from above and below of an embodiment of a wing flexible wing according to the invention.
  • Figure 3 is a partial perspective view of a wing flexible wing according to the invention devoid of a sail.
  • Figures 4 to 6 are enlarged top, rear and rear perspective views, respectively, of a flexible wing wing having a so-called relaxed configuration.
  • Figures 7 to 9 are respectively perspective views from above, rear and rear enlarged of a flexible wing wing having a so-called stretch configuration.
  • the object of the invention relates to a wing 1 with flexible wings and controlled by displacement of the center of gravity.
  • the wing 1 according to the invention is intended to be used for a flexible wing aircraft of any type such as, for example, a pendulum type ultra-light aircraft or a free-flying wing (hang-glider).
  • the wing 1 comprises a flexible wing 2 and a control structure 3 supported by the flexible wing 2.
  • the steering structure 3 is a trapezoid comprising two 4 amounts connected by a control bar 5.
  • the control structure 3 can be performed differently, for example through a tube with handles.
  • the flexible wing 2 comprises a keel 7 extending along the longitudinal axis of symmetry L of the flexible wing 2.
  • the flexible wing 2 also comprises at least one and in the illustrated example, two longitudinal edge sill members. Attack 8 fixed on the front portion 7i of the keel extending on either side of the keel to define between them an arrow.
  • the leading edge spars 8 are mounted on the keel around axes of rotation to allow their folding.
  • the flexible wing 2 also comprises two transverse longitudinal members 9 supported by the keel 7 and extending on either side of this keel 7.
  • transverse longitudinal members 9 supported by the keel 7 and extending on either side of this keel 7.
  • transverse spars 9 it may be envisaged to carry out a 2 different flexible wing not including, for example, transverse spars 9.
  • the flexible wing 2 also comprises a flexible sail 11 stretched over the leading edge spars 8.
  • the flexible sail 11 is fixed and tensioned by any appropriate means (masts, ropes, battens, etc.) which will not be described precisely because the mounting the sail is not part of the subject of the invention and is known to those skilled in the art.
  • the flexible sail 11 thus delimits conventionally at the front of the wing 2, a leading edge 12 and at the rear of the wing 2, a trailing edge 13.
  • the flexible sail 11 is therefore symmetrical with respect to the longitudinal axis L delimiting two half-wings li t , H 2 each extending on one side of the keel 7.
  • the wing 1 comprises a controlled system 20 for modifying the transverse tension of the sail 11 at least at its trailing edge 13. It must be considered that this controlled system 20 makes it possible to modify the tension transverse of the flexible sail 11 relative to the longitudinal direction of the flexible wing 2. In other words, the tension of the flexible sail 11 is modified according to the wingspan of the flexible wing 2. Moreover, the transverse tension of the flexible sail 11 is modified at least at the trailing edge 13 and in practice along the trailing edge 13 and at a longitudinal depth from this trailing edge 13.
  • the controlled system 20 for modifying the transverse tension of the flexible sail 11 thus makes it possible to modify the shape of the wing 2 and in particular to control at least the twisting of the ends of the wing and the lobe of the wing as will be explained in the following description.
  • the wing 1 also comprises a device 21 for controlling in flight the controlled system 20 for modifying the transverse tension of the flexible sail 11.
  • the control device 21 comprises a control member 22 associated with the structure 3 and acting via a transmission 23 on the controlled system 20 for modifying the transverse tension of the flexible sail 11.
  • the transmission 23 is a cable moved by the control member 22 of manual type such as a handle as will be explained in the following description.
  • the controlled system 20 for modifying the transverse tension of the flexible sail 11 comprises a mechanism 25 for spacing and bringing the two half-webs Hi, II 2 closer together in order to reduce or reduce to increase the transverse tension of the sail 11 substantially at the trailing edge 13 respectively when the two semi-webs are moved apart or apart.
  • this spacing and approach mechanism 25 is mounted substantially in the center and under the surface of the extrados of the flexible wing 2 near the trailing edge 13.
  • the spacing and approach mechanism 25 acts on the half-webs Hi and ll ⁇ by means of two slats 30 each fixed to a half-sail 11 1 , 1I 2 ,
  • the two slats 30 extend longitudinally substantially from the leading edge 12 to the trailing edge 13.
  • the two slats 30 thus extend on either side of the keel 7 in the central portion of the flexible wing 2.
  • the two slats 30 are each fixed and close to the front portion 7i of the keel 7 on a different leading edge beam 8.
  • the two slats 30 are mounted on the axes of rotation and mounting of the leading edge spars 8.
  • the two slats 30 are fixed in any suitable manner to the half-webs Hi, H 2 . It should be noted that it can be envisaged that the two slats 30 are not attached to the leading edge spars 8, but being simply mounted integral with the sail 11. It should be noted that the effort of spacing and approximation exerted by the mechanism 25 on the slats 30 allows to distribute in the longitudinal direction, the tension exerted on the half-webs Hi, 112- Of course, the spacing mechanism and approach 25 can act directly on the two half-sails Hi, H 2 . In this case, the traction and release efforts are rather localized by reverberating directly in the sail 11.
  • the spacing and closing mechanism 25 comprises hoists 32 acting on the half-webs Hi, H 2 .
  • hoists 32 are mounted in series on each slat 30, from its free end being established substantially at the trailing edge 13.
  • the hoists 32 are controlled by the cable 23 forming part of the device. 21.
  • the cable 23, which passes alternately from a hoist 32 of a slat 30 to the hoist 32 of the other slat 30, is mounted to a reel 36 whose rotation control is provided by the member of control 22 such as a handle.
  • the cable 23 is mounted to extend substantially parallel to the keel 7 to a return pulley 37 located substantially in line with an amount 4 of the trapezium 3 along which the cable 23 is mounted.
  • the retractor 36 is fixed for example on the upright 4 near the control bar 5.
  • the rotation of the reel 36 in one direction leads to the winding of the cable 23 around the reel so that this traction cable 23 causes the hoists 32 carried by the slats 30 (FIGS.7, 8, 9) to come together, whereas the rotation of the retractor in a contrary direction leads to the unwinding of the cable 23, the slackening of which leads to spacing between them hoists 32 carried by the slats 30 ( Figure 4, 5, 6).
  • the spacing and approach mechanism 25 acts mainly to exert the traction force since the relaxation is ensured essentially by the tension of the sail.
  • the change of the transverse tension of the flexible sail 11 may be made differently from a spacing mechanism and approach 25 acting on the half-sails.
  • the controlled system 20 for modifying the transverse tension of the flexible sail 11 may comprise a mechanism providing a traction and transverse release force making it possible to increase or decrease the transverse tension of the sail 11 at least at its edge. leak 13.
  • the device 21 for controlling the controlled system 20 for modifying the transverse tension of the sail 11 is of the manual type.
  • it may be provided to implement a motorized control device 21.
  • an electric motorized winder can be mounted on the keel 7. This motorized winder which ensures the winding or unwinding of the cable 23 is controlled by a control member 22 such a button control box fixed on the structure of pilot 3 and electrically connected to the motorized winder.
  • the spacing mechanism and approximation 25 is, in the example shown, made by hoists associated with a cable.
  • the spacing mechanism and approach 25 can be made differently for example by a jack.
  • the controlled system 20 for modifying the transverse tension of the flexible sail 11 comprises a safety member 40 to limit the spacing between the two half-sails Hi, H 2 to a limit value.
  • this safety member 40 is formed by a strap limiting the spacing between the half-webs Hi, H2.
  • this safety strap 40 is fixed on the two battens 30 near the trailing edge 13. This safety member 40 thus makes it possible to limit the relaxation of the flexible sail 11 to a limit value.
  • This safety member 40 plays its role in particular during a breakage of the cable 23.
  • the flexible sail 11 comprises at the spacing and approach mechanism 25 and in the direction of the ends of the wing, transverse reinforcements 41 on which acts the spacing mechanism and approaching 25 (FIG. 2).
  • transverse reinforcements 41 arranged in the sail in the direction of the span allow to transmit the tension force of the mechanism 25 to the end of each half-sail Hi, H2.
  • these transverse reinforcements 41 are made by reinforced fabric strips such as strips of composite material webs extending from the slats 30 at the hoists 32 and to the ends of the wing.
  • the flexible sail 11 comprises between the two half-webs Hi, H2, an elastic band 45 for spacing compensation (FIG 1). Indeed, during the approach towards the center of the wing, half-wings Hi, II 2 , the portion of the flexible sail located between the two transverse traction zones is deformed in the presence of a non-elastic sail. To avoid the "yawn" of the sail 11, the sail 11 thus has between the two slats 30, an elastic band 45 of compensation to obtain a sail still stretched between the two slats 30 whatever the distance between these values two slats 30.
  • this elastic compensation strip 45 is removable to facilitate access to the spacing mechanism and approach 25 arranged between the two slats 30.
  • the controlled system 20 for modifying the transverse tension of the flexible sail 11 is particularly effective and simple to implement.
  • Such a system 20 makes it possible to combine simultaneously with a single command, the adjustment of the zero-effort speed, of the wing 1 and the adaptation of the geometry of the flexible wing 2 at this speed by acting on the twisting of the wing. flexible 2 and the lobe (or soft) of the flexible wing 2.
  • FIGS. 4 to 9 illustrate and illustrate the principle of the invention.
  • the piloted modification system 20 thus makes it possible to modify the configuration of the flexible wing 11 in order to place the latter in a so-called relaxed configuration (FIGS.4 to 6) or in a so-called stretched position illustrated in FIGS. 7 to 9.
  • the spacing and approach mechanism 25 exerts practically no tensile force on the two half-wings Hi, II- sails Hi, H 2 have a relatively large lobe or slack.
  • the lobe I corresponds to the distance taken at the trailing edge 13 between the plane passing through the ends of each half-sail (end and center of the wing) and the top of the half-sail.
  • twisting corresponds to the difference in the incidence of the profile of the wing between the center and the end of the wing.
  • the controlled system 20 makes it possible to quickly switch to a so-called taut sail configuration as illustrated in FIGS. 7 to 9.
  • This stretched sail configuration is particularly advantageous for a rapid flight phase.
  • This taut sail configuration is obtained by maneuvering the control lever 22 to bring the two half-sails Hi, H 2 .
  • the kinking of the wingtips is decreased as well as the lobes I. Insofar as the lobe I is minimal, the wing 1 has a perfect road stability without tendency to engage the roll movements.
  • the minimal twisting of the wingtips provides the best aerodynamic performance at the weak impacts and reduces pitching efforts.
  • the center of retracted aerodynamic thrust increases the speed at zero effort.
  • the controlled system 20 is controlled to place the flexible wing 2 in a so-called relaxed configuration as illustrated in FIGS. 4 to 6.
  • the lobe I of the wing 2 is maximum allowing a significant differential movement and providing better handling in roll.
  • the twisting of the wingtips is also maximum so that the central part of the wing picks first to ensure healthy behavior and no surprise at large incidences.
  • Increases in lobe I and twisting increase drag, which is favorable for obtaining steep approach gradients.
  • the advanced aerodynamic thrust center reduces the speed at zero effort.
  • the controlled system 20 makes it possible to precisely control the value of the transverse tension of the sail 11 and consequently to accurately control the values of the lobe and the twisting of the flexible wing.
  • the flexible wing 2 can take all the intermediate configurations between the extreme stretched position and the extreme relaxed position.
  • the wing 1 also comprises a system 50 for modifying the reflex of the profile of the flexible wing 2 in the central part of the sail.
  • the reflex of the profile of a flexible wing 2 corresponds to the profile of the wing 2 taken in the longitudinal vertical plane and having, from the trailing edge 13 and on the rear portion of the flexible wing 2, a concavity turned to the top.
  • the reflex of the profile of a flexible wing corresponds to a trailing edge 13 raised.
  • the system 50 for modifying the reflex of the profile of the flexible wing 2 comprises a connecting member between the rear parts of the sail subjected to the spacing and approach mechanism 25.
  • This connecting member 50 passes below the keel 7 so as to increase or decrease the reflex R of the central profile of the wing flexible respectively at the approximation or spacing of the half-parts Hi, H 2 of the flexible sail.
  • this connecting member is constituted by a strap attached to the two longitudinal strips 30 at substantially the trailing edge 13.
  • the central reflex of the wing 2 is increased simultaneously with the decrease of the lobe and the kinking of the wingtips.
  • the decrease of the lobe and twisting associated with the increase of the reflex of the profile in the central part generates a decrease in drag and therefore an increase in yield allowing higher speeds for a given power (lower consumption, maximum speed in upper tier).
  • a decreased central reflex is obtained in combination with an increase in wing tip lash and twisting.
  • the reduction of the central reflex makes it possible to obtain the lowest possible speed.
  • control structure 3 comprises only a trapezium.
  • this control structure 3 may be different.
  • the control structure 3 may comprise a tricycle hooked to the keel 7 in order to achieve an ultralight pendulum.

Abstract

The invention relates to a wing having a flexible wing structure and controlled by moving the center of gravity, comprising: a flexible wing structure (2) including a supporting keel (7) provided with at least one leading edge spar (8) defining an arrow, a flexible sail (11) being stretched over the spar so as to define a leading edge (12) and a trailing edge (13) and, on either side, two half-sails (H1, H2); and a controlling structure (3) supported by the flexible wing structure, said wing comprising: a controlled system (20) for modifying the transverse tension of the sail (11) at the trailing edge (13) thereof in order to control at least the twist of the tips of the wing structure and the lobe of the wing structure; and a device (21) for controlling, during flight, the system (20) for modifying the transverse tension.

Description

AILE A VOILURE SOUPLE ET A PILOTAGE PAR DEPLACEMENT FLEXIBLE WING WING WITH DISPLACEMENT DRIVING
DU CENTRE DE GRAVITE CENTER OF GRAVITY
L'objet de l'invention concerne une aile à voilure souple pilotée par déplacement du centre de gravité.  The object of the invention relates to a wing with flexible wing driven by displacement of the center of gravity.
L'objet de l'invention trouve une application particulièrement avantageuse par exemple pour les ailes de vol libre ou les Ultra Légers Motorisés de type pendulaire.  The object of the invention finds a particularly advantageous application for example for free flying wings or ultra-light motorized pendulum type.
D'une manière classique, les ailes volantes à voilure souple et pilotage par déplacement du centre de gravité ne possèdent pas de gouvernes aérodynamiques. La réponse en roulis de ces ailes volantes est étroitement dépendante de leur vitesse de vol à savoir faible à basse vitesse et surabondante à haute vitesse. En raison de cette caractéristique, les ailes volantes qui possèdent une plage de vitesse importante, présentent soit une maniabilité très insuffisante aux basses vitesses ne permettant pas leur exploitation pratique, soit une hypersensibilité en roulis à haute vitesse rendant le contrôle délicat, voire dangereux surtout si la stabilité en lacet est faible.  In a conventional manner, the flying wings with flexible wing and control by displacement of the center of gravity do not have aerodynamic control surfaces. The roll response of these flying wings is closely dependent on their flying speed ie low at low speed and high speed at high speed. Because of this characteristic, the flying wings which have a high speed range, have either a very poor handling at low speeds that do not allow their practical use, or a hypersensitivity in roll at high speed making the control delicate, even dangerous especially if yaw stability is low.
Pour tenter d'apporter une réponse à ce problème, il est connu d'équiper ces ailes, d'un système de géométrie variable par modification en vol de l'angle d'ouverture de la structure. Toutefois, cette solution présente des inconvénients notamment en ce qui concerne la détention des câbles latéraux désagréable en turbulence, la détention des cordes de rappel diminuant la stabilité aux faibles incidences et surtout pour les ailes destinées aux vols motorisés, la modification de la vitesse de croisière à effort nul dans le sens inverse de l'effet souhaitable.  In an attempt to provide an answer to this problem, it is known to equip these wings with a system of variable geometry by changing in flight the opening angle of the structure. However, this solution has drawbacks in particular as regards the possession of side cables unpleasant turbulence, the holding of the return ropes decreasing stability at low incidences and especially for the wings for motorized flights, changing the cruising speed zero effort in the opposite direction of the desirable effect.
Par ailleurs, il est connu par le brevet US 3 936 012, une aile à voilure souple pilotée par déplacement du centre de gravité. Cette aile comporte une voilure souple comprenant une quille pourvue de deux longerons de bord d'attaque délimitant une flèche et de deux longerons transversaux s'étendant entre la quille et les longerons de bord d'attaque. Une voile souple est tendue sur les longerons de bord d'attaque et la quille. Les longerons de bord d'attaque sont portés par des connecteurs montés chacun sur un longeron transversal. La position des connecteurs le long des longerons transversaux est réglable pour permettre de modifier avant la phase de vol, la forme de la voilure. Furthermore, it is known from US Pat. No. 3,936,012, a wing with flexible wings controlled by displacement of the center of gravity. This wing comprises a flexible wing comprising a keel provided with two leading edge spars defining an arrow and two transverse spars extending between the keel and the leading edge spars. A soft sail is stretched over the leading edge spars and the keel. Leading edge spars are carried by connectors each mounted on a transverse spar. The position of the connectors along the transverse rails is adjustable to allow to modify before the flight phase, the shape of the wing.
Une telle aile souple ne permet pas d'optimiser la géométrie de la voilure en fonction de la vitesse de vol, lors des différentes phases de vol de l'aile.  Such a flexible wing does not make it possible to optimize the geometry of the wing as a function of the speed of flight, during the different flight phases of the wing.
Dans le domaine des ailes destinées aux vols motorisés, la recherche de l'accroissement des performances conduit à les équiper de systèmes de compensation (trim) en tangage permettant de faire varier la vitesse de croisière en vol. Les divers systèmes de compensation utilisés qui reposent sur le principe du déplacement du point d'accroché du tricycle sont lourds et complexes et engendrent des efforts importants de pilotage en tangage ou induisent, pour les systèmes les plus simples agissant sur les cordes de rappel, des détériorations de la vitesse de décrochage en configuration lente.  In the field of wings for motorized flights, the search for increased performance leads to equip them with trim systems (trim) in pitch to vary the cruising speed in flight. The various compensation systems used which are based on the principle of moving the attachment point of the tricycle are heavy and complex and generate significant pitching efforts or induce, for the simplest systems acting on the return strings, deterioration of the stall speed in slow configuration.
De façon plus fondamentale, aucun de ces systèmes de compensation ne résout le problème de la diminution de la maniabilité avec la réduction de la vitesse et ne permet donc pas une exploitation réelle de la plage de vitesse proposée. En pratique, les ailes volantes rapides se révèlent incapables d'effectuer des approches lentes, de se poser court en conditions turbulentes, notamment en cas de panne moteur.  More fundamentally, none of these compensation systems solves the problem of reducing the handling with the reduction of the speed and therefore does not allow a real exploitation of the proposed speed range. In practice, fast flying wings are unable to perform slow approaches, to land short in turbulent conditions, especially in case of engine failure.
L'objet de l'invention vise donc à remédier aux inconvénients de l'état de la technique en proposant une aile à voilure souple pilotée par déplacement du centre de gravité, cette aile présentant une géométrie qui est adaptée ou optimisée en fonction de la vitesse de l'aile lors de toutes ses phases de vol.  The object of the invention is therefore to overcome the drawbacks of the state of the art by proposing a wing with flexible wing driven by displacement of the center of gravity, this wing having a geometry which is adapted or optimized according to the speed of the wing during all phases of flight.
Un autre objet de l'invention est de proposer une aile à voilure souple équipée d'un système simple pour régler sa vitesse et adapter simultanément la géométrie de la voilure à cette vitesse.  Another object of the invention is to provide a wing with flexible wing equipped with a simple system to adjust its speed and simultaneously adapt the geometry of the wing at this speed.
Pour atteindre un tel objectif, l'objet de l'invention concerne une aile à voilure souple pilotée par déplacement du centre de gravité comportant :  To achieve such an objective, the object of the invention relates to a wing wing flexible controlled by displacement of the center of gravity comprising:
- une voilure souple comprenant une quille de support pourvue d'au moins un longeron de bord d'attaque délimitant une flèche, une voile souple étant tendue sur le longeron pour délimiter un bord d'attaque et un bord de fuite et de part et d'autre, deux demi-voiles, a flexible wing comprising a support keel provided with at least one leading edge spar delimiting an arrow, a flexible sail being stretched on the spar to define a leading edge and a trailing edge and on both sides, two half-sails,
- et une structure de pilotage supportée par la voilure souple.  and a control structure supported by the flexible wing.
Selon l'invention, l'aile comporte :  According to the invention, the wing comprises:
- un système piloté de modification de la tension transversale de la voile au niveau au moins de son bord de fuite pour contrôler au moins le vrillage des bouts de la voilure et le lobe de la voilure,  a controlled system for modifying the transverse tension of the sail at least at its trailing edge so as to control at least the twisting of the ends of the wing and the lobe of the wing,
- et un dispositif pour commander en vol le système de modification de la tension transversale, comportant un organe de commande associé à la structure de pilotage.  and a device for controlling in flight the system for modifying the transverse tension, comprising a control member associated with the control structure.
Selon une caractéristique avantageuse de réalisation, le système de modification de la tension transversale comporte un mécanisme d'écartement et de rapprochement des demi-voiles entre elles afin de diminuer ou d'augmenter la tension transversale de la voile au niveau sensiblement du bord de fuite lors respectivement de l'écartement ou du rapprochement des demi-voiles.  According to an advantageous characteristic of embodiment, the system for modifying the transverse tension comprises a mechanism for spacing and bringing the half-webs together to reduce or increase the transverse tension of the sail substantially at the trailing edge. when respectively the spacing or the approximation of the half-sails.
Avantageusement, le mécanisme d'écartement et de rapprochement agit sur les deux demi-voiles par l'intermédiaire de deux lattes s'étendant longitudinalement sensiblement du bord d'attaque jusqu'au bord de fuite et de part et d'autre de la quille pour s'étendre dans la partie centrale de la voilure souple.  Advantageously, the spacing and approach mechanism acts on the two half-webs by means of two slats extending longitudinally substantially from the leading edge to the trailing edge and on either side of the keel. to extend in the central part of the flexible wing.
Selon une variante préférée de réalisation, la voile souple comporte à partir du mécanisme d'écartement et de rapprochement et en direction des bouts d'aile, des renforts transversaux sur lesquels agit le mécanisme d'écartement et de rapprochement.  According to a preferred embodiment, the flexible sail comprises from the spacing mechanism and approaching and towards the wingtips, transverse reinforcements on which acts the spacing mechanism and approach.
De préférence, l'aile comporte un organe de sécurité pour limiter l'écartement entre les deux demi-voiles à une valeur limite.  Preferably, the wing comprises a safety member to limit the spacing between the two half-sails to a limit value.
Selon une autre caractéristique de réalisation, la voile souple comporte entre les deux demi-voiles, une bande élastique de compensation d'écartement.  According to another characteristic of embodiment, the flexible sail comprises between the two half-sails, an elastic spacer compensation band.
Selon un exemple préféré de réalisation, le mécanisme d'écartement et de rapprochement comporte des palans fixés sur les demi-voiles tandis que le dispositif de commande comporte un câble actionnant les palans et monté jusqu'à un enrouleur dont le pilotage en rotation est assuré par l'organe de commande. According to a preferred embodiment, the spacing and approach mechanism comprises hoists fixed on the half-sails while the control device comprises a cable actuating the hoists and mounted to a winder whose rotary control is provided by the control member.
Selon une variante préférée de réalisation, l'aile comporte un système de modification du réflex du profil de la voilure souple, dans la partie centrale de la voilure souple.  According to a preferred embodiment, the wing comprises a system for modifying the reflex of the profile of the flexible wing in the central part of the flexible wing.
Avantageusement, le système de modification du réflex du profil de la voilure souple comporte un organe de liaison entre les parties arrières de la voile soumises au mécanisme d'écartement et de rapprochement, cet organe de liaison passant en dessous de la quille de manière à augmenter ou diminuer le réflex du profil central de la voilure souple respectivement lors du rapprochement ou de l'écartement des deux-demi voiles.  Advantageously, the system for modifying the reflex of the profile of the flexible wing comprises a connecting member between the rear parts of the sail subjected to the spacing and approach mechanism, this connecting member passing below the keel so as to increase or reduce the reflex of the central profile of the flexible wing respectively at the approach or spacing of the two-half sails.
Un autre objet de l'invention est de proposer un aéronef comportant une aile conforme à l'invention dont la structure de pilotage comporte un tricycle accroché à la quille.  Another object of the invention is to propose an aircraft comprising a wing according to the invention, the steering structure of which comprises a tricycle hooked to the keel.
Diverses autres caractéristiques ressortent de la description faite ci-dessous en référence aux dessins annexés qui montrent, à titre d'exemples non limitatifs, des formes de réalisation de l'objet de l'invention.  Various other characteristics appear from the description given below with reference to the accompanying drawings which show, by way of non-limiting examples, embodiments of the subject of the invention.
Les Figures 1 et 2 sont des vues en perspective respectivement de dessus et de dessous d'un exemple de réalisation d'une aile à voilure souple conforme à l'invention.  Figures 1 and 2 are perspective views respectively from above and below of an embodiment of a wing flexible wing according to the invention.
La Figure 3 est une vue en perspective partielle d'une aile à voilure souple conforme à l'invention dépourvue d'une voile.  Figure 3 is a partial perspective view of a wing flexible wing according to the invention devoid of a sail.
Les Figures 4 à 6 sont des vues respectivement en perspective de dessus, arrière et arrière agrandie d'une aile à voilure souple présentant une configuration dite relâchée.  Figures 4 to 6 are enlarged top, rear and rear perspective views, respectively, of a flexible wing wing having a so-called relaxed configuration.
Les Figures 7 à 9 sont des vues respectivement en perspective de dessus, arrière et arrière agrandie d'une aile à voilure souple présentant une configuration dite tendue.  Figures 7 to 9 are respectively perspective views from above, rear and rear enlarged of a flexible wing wing having a so-called stretch configuration.
Tel que cela ressort plus précisément des Figures 1 et 2, l'objet de l'invention concerne une aile 1 à voilure souple et pilotée par déplacement du centre de gravité. L'aile 1 conforme à l'invention est destinée à être utilisée pour un aéronef à voilure souple de tout type tel que par exemple, un appareil Ultra Léger Motorisé de type pendulaire ou une aile de vol libre (deltaplane). As is more particularly apparent from Figures 1 and 2, the object of the invention relates to a wing 1 with flexible wings and controlled by displacement of the center of gravity. The wing 1 according to the invention is intended to be used for a flexible wing aircraft of any type such as, for example, a pendulum type ultra-light aircraft or a free-flying wing (hang-glider).
Tel que cela ressort plus précisément des Figures 1 à 3, l'aile 1 comporte une voilure souple 2 et une structure de pilotage 3 supporté par la voilure souple 2. Dans l'exemple illustré, la structure de pilotage 3 est un trapèze comprenant deux montants 4 reliés par une barre de contrôle 5. Bien entendu, la structure de pilotage 3 peut être réalisée de manière différente, par l'intermédiaire par exemple d'un tube muni de poignées.  As is more particularly apparent from FIGS. 1 to 3, the wing 1 comprises a flexible wing 2 and a control structure 3 supported by the flexible wing 2. In the example illustrated, the steering structure 3 is a trapezoid comprising two 4 amounts connected by a control bar 5. Of course, the control structure 3 can be performed differently, for example through a tube with handles.
De manière classique, la voilure souple 2 comporte une quille 7 s'étendant selon l'axe longitudinal de symétrie L de la voilure souple 2. La voilure souple 2 comporte également au moins un et dans l'exemple illustré, deux longerons de bord d'attaque 8 fixés sur la partie avant 7i de la quille en s'étendant de part et d'autre de la quille pour délimiter entre eux une flèche. Selon une variante préférée de réalisation, les longerons de bord d'attaque 8 sont montés sur la quille autour d'axes de rotation pour autoriser leur repliement.  In a conventional manner, the flexible wing 2 comprises a keel 7 extending along the longitudinal axis of symmetry L of the flexible wing 2. The flexible wing 2 also comprises at least one and in the illustrated example, two longitudinal edge sill members. Attack 8 fixed on the front portion 7i of the keel extending on either side of the keel to define between them an arrow. According to a preferred embodiment, the leading edge spars 8 are mounted on the keel around axes of rotation to allow their folding.
Selon une caractéristique illustrée sur la variante de réalisation, la voilure souple 2 comporte également deux longerons transversaux 9 supportés par la quille 7 et s'étendant de part et d'autre de cette quille 7. Bien entendu, il peut être envisagé de réaliser une voilure souple 2 différente ne comportant pas, par exemple, de longerons transversaux 9.  According to a feature illustrated on the variant embodiment, the flexible wing 2 also comprises two transverse longitudinal members 9 supported by the keel 7 and extending on either side of this keel 7. Of course, it may be envisaged to carry out a 2 different flexible wing not including, for example, transverse spars 9.
La voilure souple 2 comporte également une voile souple 11 tendue sur les longerons de bord d'attaque 8. La voile souple 11 est fixée et tendue par tous moyens appropriés (mâts, cordes, lattes, etc) qui ne seront pas décrits précisément car le montage de la voile ne fait pas précisément partie de l'objet de l'invention et est connu de l'homme du métier. La voile souple 11 délimite ainsi classiquement à l'avant de la voilure 2, un bord d'attaque 12 et à l'arrière de la voilure 2, un bord de fuite 13. La voile souple 11 est donc symétrique par rapport à l'axe longitudinal L en délimitant deux demi-voiles lit, H2 s'étendant chacune d'un côté de la quille 7. Conformément à l'invention, l'aile 1 comporte un système piloté 20 de modification de la tension transversale de la voile 11 au niveau au moins de son bord de fuite 13. Il doit être considéré que ce système piloté 20 permet de modifier la tension transversale de la voile souple 11 par rapport à la direction longitudinale de la voilure souple 2. En d'autres termes, la tension de la voile souple 11 est modifiée selon l'envergure de la voilure souple 2. Par ailleurs, la tension transversale de la voile souple 11 est modifiée au niveau au moins du bord de fuite 13 et en pratique selon le bord de fuite 13 et selon une profondeur longitudinale à partir de ce bord de fuite 13. Le système piloté 20 de modification de la tension transversale de la voile souple 11 permet ainsi de modifier la forme de la voilure 2 et en particulier de contrôler au moins le vrillage des bouts de la voilure et le lobe de la voilure comme cela sera expliqué dans la suite de la description. The flexible wing 2 also comprises a flexible sail 11 stretched over the leading edge spars 8. The flexible sail 11 is fixed and tensioned by any appropriate means (masts, ropes, battens, etc.) which will not be described precisely because the mounting the sail is not part of the subject of the invention and is known to those skilled in the art. The flexible sail 11 thus delimits conventionally at the front of the wing 2, a leading edge 12 and at the rear of the wing 2, a trailing edge 13. The flexible sail 11 is therefore symmetrical with respect to the longitudinal axis L delimiting two half-wings li t , H 2 each extending on one side of the keel 7. According to the invention, the wing 1 comprises a controlled system 20 for modifying the transverse tension of the sail 11 at least at its trailing edge 13. It must be considered that this controlled system 20 makes it possible to modify the tension transverse of the flexible sail 11 relative to the longitudinal direction of the flexible wing 2. In other words, the tension of the flexible sail 11 is modified according to the wingspan of the flexible wing 2. Moreover, the transverse tension of the flexible sail 11 is modified at least at the trailing edge 13 and in practice along the trailing edge 13 and at a longitudinal depth from this trailing edge 13. The controlled system 20 for modifying the transverse tension of the flexible sail 11 thus makes it possible to modify the shape of the wing 2 and in particular to control at least the twisting of the ends of the wing and the lobe of the wing as will be explained in the following description.
Tel que cela ressort plus précisément de la Fig. 3, l'aile 1 comporte également un dispositif 21 pour commander en vol le système piloté 20 de modification de la tension transversale de la voile souple 11. A cet effet, le dispositif de commande 21 comporte un organe de commande 22 associé à la structure de pilotage 3 et agissant par l'intermédiaire d'une transmission 23 sur le système piloté 20 de modification de la tension transversale de la voile souple 11. Dans l'exemple illustré, la transmission 23 est un câble déplacé par l'organe de commande 22 de type manuel tel qu'une poignée comme cela sera expliqué dans la suite de la description.  As is more particularly apparent from FIG. 3, the wing 1 also comprises a device 21 for controlling in flight the controlled system 20 for modifying the transverse tension of the flexible sail 11. For this purpose, the control device 21 comprises a control member 22 associated with the structure 3 and acting via a transmission 23 on the controlled system 20 for modifying the transverse tension of the flexible sail 11. In the example illustrated, the transmission 23 is a cable moved by the control member 22 of manual type such as a handle as will be explained in the following description.
Selon un exemple préféré de réalisation, le système piloté 20 de modification de la tension transversale de la voile souple 11 comporte un mécanisme 25 d'écartement et de rapprochement des deux demi-voiles Hi, II2 entre elles, afin de diminuer ou d'augmenter la tension transversale de la voile 11 au niveau sensiblement du bord de fuite 13 lors respectivement de l'écartement ou du rapprochement 25 des deux demi- voiles. De préférence, ce mécanisme d'écartement et de rapprochement 25 est monté sensiblement au centre et sous la surface de l'extrados de la voilure souple 2 à proximité du bord de fuite 13. Dans l'exemple de réalisation illustré, le mécanisme d'écartement et de rapprochement 25 agit sur les demi-voiles Hi et ll∑ par l'intermédiaire de deux lattes 30 fixées chacune à une demi-voile 111,1I2, Dans l'exemple illustré, les deux lattes 30 s'étendent longitudinalement sensiblement du bord d'attaque 12 jusqu'au bord de fuite 13. Les deux lattes 30 s'étendent ainsi de part et d'autre de la quille 7 dans la partie centrale de la voilure souple 2. Dans l'exemple illustré, les deux lattes 30 sont fixées chacune et à proximité de la partie avant 7i de la quille 7 sur un longeron de bord d'attaque 8 différent. According to a preferred embodiment, the controlled system 20 for modifying the transverse tension of the flexible sail 11 comprises a mechanism 25 for spacing and bringing the two half-webs Hi, II 2 closer together in order to reduce or reduce to increase the transverse tension of the sail 11 substantially at the trailing edge 13 respectively when the two semi-webs are moved apart or apart. Preferably, this spacing and approach mechanism 25 is mounted substantially in the center and under the surface of the extrados of the flexible wing 2 near the trailing edge 13. In the exemplary embodiment illustrated, the spacing and approach mechanism 25 acts on the half-webs Hi and llΣ by means of two slats 30 each fixed to a half-sail 11 1 , 1I 2 , In illustrated example, the two slats 30 extend longitudinally substantially from the leading edge 12 to the trailing edge 13. The two slats 30 thus extend on either side of the keel 7 in the central portion of the flexible wing 2. In the example shown, the two slats 30 are each fixed and close to the front portion 7i of the keel 7 on a different leading edge beam 8.
De préférence, les deux lattes 30 sont montées sur les axes de rotation et de montage des longerons de bord d'attaque 8. Les deux lattes 30 sont fixées de toute manière appropriée aux demi-voiles Hi, H2. Il est à noter qu'il peut être envisagé que les deux lattes 30 ne se trouvent pas fixées aux longerons de bord d'attaque 8, mais en étant simplement montées solidaires de la voile 11. Il est à noter que l'effort d'écartement et de rapprochement exercé par le mécanisme 25 sur les lattes 30 permet de répartir selon la direction longitudinale, la tension exercée sur les demi-voiles Hi, 112- Bien entendu, le mécanisme d'écartement et de rapprochement 25 peut agir directement sur les deux demi-voiles Hi, H2. Dans ce cas, les efforts de traction et de relâchement sont plutôt localisés en se répercutant directement dans la voile 11. Preferably, the two slats 30 are mounted on the axes of rotation and mounting of the leading edge spars 8. The two slats 30 are fixed in any suitable manner to the half-webs Hi, H 2 . It should be noted that it can be envisaged that the two slats 30 are not attached to the leading edge spars 8, but being simply mounted integral with the sail 11. It should be noted that the effort of spacing and approximation exerted by the mechanism 25 on the slats 30 allows to distribute in the longitudinal direction, the tension exerted on the half-webs Hi, 112- Of course, the spacing mechanism and approach 25 can act directly on the two half-sails Hi, H 2 . In this case, the traction and release efforts are rather localized by reverberating directly in the sail 11.
Le mécanisme d'écartement et de rapprochement 25 comporte des palans 32 agissant sur les demi-voiles Hi, H2. Dans l'exemple illustré, des palans 32 sont montés en série sur chaque latte 30, à partir de son extrémité libre s'établissant sensiblement au niveau du bord de fuite 13. Les palans 32 sont commandés par le câble 23 faisant partie du dispositif de commande 21. Le câble 23, qui passe alternativement d'un palan 32 d'une latte 30 au palan 32 de l'autre latte 30, est monté jusqu'à un enrouleur 36 dont le pilotage en rotation est assuré par l'organe de commande 22 tel qu'une poignée. Le câble 23 est monté pour s'étendre sensiblement parallèlement à la quille 7 jusqu'à une poulie de renvoi 37 située sensiblement à l'aplomb d'un montant 4 du trapèze 3 le long duquel le câble 23 est monté. L'enrouleur 36 est fixé par exemple sur le montant 4 à proximité de la barre de contrôle 5. La rotation de l'enrouleur 36 dans un sens conduit à l'enroulement du câble 23 autour de l'enrouleur de sorte que cette traction du câble 23 provoque le rapprochement entre eux des palans 32 portés par les lattes 30 (Fig. 7, 8, 9), alors que la rotation de l'enrouleur dans un sens contraire conduit au dévidage du câble 23 dont le relâchement conduit à l'écartement entre eux des palans 32 portés par les lattes 30 (Fig. 4, 5, 6). The spacing and closing mechanism 25 comprises hoists 32 acting on the half-webs Hi, H 2 . In the illustrated example, hoists 32 are mounted in series on each slat 30, from its free end being established substantially at the trailing edge 13. The hoists 32 are controlled by the cable 23 forming part of the device. 21. The cable 23, which passes alternately from a hoist 32 of a slat 30 to the hoist 32 of the other slat 30, is mounted to a reel 36 whose rotation control is provided by the member of control 22 such as a handle. The cable 23 is mounted to extend substantially parallel to the keel 7 to a return pulley 37 located substantially in line with an amount 4 of the trapezium 3 along which the cable 23 is mounted. The retractor 36 is fixed for example on the upright 4 near the control bar 5. The rotation of the reel 36 in one direction leads to the winding of the cable 23 around the reel so that this traction cable 23 causes the hoists 32 carried by the slats 30 (FIGS.7, 8, 9) to come together, whereas the rotation of the retractor in a contrary direction leads to the unwinding of the cable 23, the slackening of which leads to spacing between them hoists 32 carried by the slats 30 (Figure 4, 5, 6).
Il est à noter que le mécanisme d'écartement et de rapprochement 25 agit principalement pour exercer l'effort de traction puisque le relâchement est assuré essentiellement par la tension de la voile. Bien entendu, la modification de la tension transversale de la voile souple 11 peut être réalisée différemment d'un mécanisme d'écartement et de rapprochement 25 agissant sur les demi-voiles. Le système piloté 20 de modification de la tension transversale de la voile souple 11 peut comporter un mécanisme assurant un effort de traction et de relâchement transversale permettant d'augmenter ou de diminuer la tension transversale de la voile 11 au moins au niveau de son bord de fuite 13.  It should be noted that the spacing and approach mechanism 25 acts mainly to exert the traction force since the relaxation is ensured essentially by the tension of the sail. Of course, the change of the transverse tension of the flexible sail 11 may be made differently from a spacing mechanism and approach 25 acting on the half-sails. The controlled system 20 for modifying the transverse tension of the flexible sail 11 may comprise a mechanism providing a traction and transverse release force making it possible to increase or decrease the transverse tension of the sail 11 at least at its edge. leak 13.
Dans l'exemple illustré, le dispositif 21 pour commander le système piloté 20 de modification de la tension transversale de la voile 11 est du type manuel. Bien entendu, il peut être prévu de mettre en œuvre un dispositif de commande 21 motorisé. Selon cette variante, un enrouleur motorisé électrique peut être monté sur la quille 7. Cet enrouleur motorisé qui assure l'enroulement ou le déroulement du câble 23 est piloté par un organe de commande 22 tel un boîtier de commande à bouton fixé sur la structure de pilotage 3 et relié électriquement à l'enrouleur motorisé.  In the example illustrated, the device 21 for controlling the controlled system 20 for modifying the transverse tension of the sail 11 is of the manual type. Of course, it may be provided to implement a motorized control device 21. According to this variant, an electric motorized winder can be mounted on the keel 7. This motorized winder which ensures the winding or unwinding of the cable 23 is controlled by a control member 22 such a button control box fixed on the structure of pilot 3 and electrically connected to the motorized winder.
Dans le même sens, le mécanisme d'écartement et de rapprochement 25 est, dans l'exemple illustré, réalisé par des palans associés à un câble. Bien entendu, le mécanisme d'écartement et de rapprochement 25 peut être réalisé différemment par exemple, par un vérin.  In the same direction, the spacing mechanism and approximation 25 is, in the example shown, made by hoists associated with a cable. Of course, the spacing mechanism and approach 25 can be made differently for example by a jack.
Selon une variante préférée de réalisation, le système piloté 20 de modification de la tension transversale de la voile souple 11 comporte un organe de sécurité 40 pour limiter l'écartement entre les deux demi-voiles Hi, H2 à une valeur limite. Dans l'exemple de réalisation illustré, cet organe de sécurité 40 est réalisé par une sangle limitant l'écartement entre les demi-voiles Hi, H2. Tel que cela ressort plus précisément de la Fig. 3, cette sangle de sécurité 40 est fixée sur les deux lattes 30 à proximité du bord de fuite 13. Cet organe de sécurité 40 permet ainsi de limiter le relâchement de la voile souple 11 à une valeur limite. Cet organe de sécurité 40 joue son rôle notamment lors d'une casse du câble 23. According to a preferred embodiment, the controlled system 20 for modifying the transverse tension of the flexible sail 11 comprises a safety member 40 to limit the spacing between the two half-sails Hi, H 2 to a limit value. In the exemplary embodiment illustrated, this safety member 40 is formed by a strap limiting the spacing between the half-webs Hi, H2. As is more particularly apparent from FIG. 3, this safety strap 40 is fixed on the two battens 30 near the trailing edge 13. This safety member 40 thus makes it possible to limit the relaxation of the flexible sail 11 to a limit value. This safety member 40 plays its role in particular during a breakage of the cable 23.
Selon une variante préférée de réalisation, la voile souple 11 comporte au niveau du mécanisme d'écartement et de rapprochement 25 et en direction des bouts de la voilure, des renforts transversaux 41 sur lesquels agit le mécanisme d'écartement et de rapprochement 25 (Fig. 2). Ces renforts transversaux 41 disposés dans la voile dans le sens de l'envergure permettent de transmettre l'effort de tension du mécanisme 25 jusqu'à l'extrémité de chaque demi-voile Hi, H2. Par exemple, ces renforts transversaux 41 sont réalisés par des bandes de toile renforcée telles que des bandes de toiles en matériaux composites s'étendant à partir des lattes 30 au niveau des palans 32 et jusqu'aux bouts de la voilure.  According to a preferred embodiment, the flexible sail 11 comprises at the spacing and approach mechanism 25 and in the direction of the ends of the wing, transverse reinforcements 41 on which acts the spacing mechanism and approaching 25 (FIG. 2). These transverse reinforcements 41 arranged in the sail in the direction of the span allow to transmit the tension force of the mechanism 25 to the end of each half-sail Hi, H2. For example, these transverse reinforcements 41 are made by reinforced fabric strips such as strips of composite material webs extending from the slats 30 at the hoists 32 and to the ends of the wing.
Selon une caractéristique avantageuse de réalisation la voile souple 11 comporte ente les deux demi-voiles Hi, H2, une bande élastique 45 de compensation d'écartement (Fig. 1). En effet, lors du rapprochement vers le centre de la voilure, des demi-voiles Hi, II2, la partie de la voile souple située entre les deux zones de traction transversale se déforme en présence d'une voile non élastique. Pour éviter le "bâillement" de la voile 11, la voile 11 présente ainsi entre les deux lattes 30, une bande élastique 45 de compensation permettant d'obtenir une voile toujours tendue entre les deux lattes 30 quelque soit la valeur d'écartement entre ces deux lattes 30. De préférence, cette bande élastique de compensation 45 est amovible pour faciliter l'accès au mécanisme d'écartement et de rapprochement 25 disposés entre les deux lattes 30. II ressort de la description qui précède que le système piloté 20 de modification de la tension transversale de la voile souple 11 est particulièrement efficace et simple de mise en œuvre. Un tel système 20 permet de conjuguer simultanément avec une seule commande, le réglage de la vitesse à effort nul, de l'aile 1 et l'adaptation de la géométrie de la voilure souple 2 à cette vitesse en agissant sur le vrillage de la voilure souple 2 et le lobe (ou mou) de la voilure souple 2. According to an advantageous embodiment, the flexible sail 11 comprises between the two half-webs Hi, H2, an elastic band 45 for spacing compensation (FIG 1). Indeed, during the approach towards the center of the wing, half-wings Hi, II 2 , the portion of the flexible sail located between the two transverse traction zones is deformed in the presence of a non-elastic sail. To avoid the "yawn" of the sail 11, the sail 11 thus has between the two slats 30, an elastic band 45 of compensation to obtain a sail still stretched between the two slats 30 whatever the distance between these values two slats 30. Preferably, this elastic compensation strip 45 is removable to facilitate access to the spacing mechanism and approach 25 arranged between the two slats 30. It follows from the foregoing description that the controlled system 20 for modifying the transverse tension of the flexible sail 11 is particularly effective and simple to implement. Such a system 20 makes it possible to combine simultaneously with a single command, the adjustment of the zero-effort speed, of the wing 1 and the adaptation of the geometry of the flexible wing 2 at this speed by acting on the twisting of the wing. flexible 2 and the lobe (or soft) of the flexible wing 2.
Les Figures 4 à 9 permettent d'expliciter et d'illustrer le principe de l'invention. Le système piloté de modification 20 permet ainsi de modifier la configuration de la voilure souple 11 afin de placer cette dernière soit dans une configuration dite relâchée (Fig. 4 à 6) soit dans une position dite tendue illustrée aux Fig. 7 à 9. Dans la position dite relâchée (Fig. 4 à 6), le mécanisme d'écartement et de rapprochement 25 n'exerce pratiquement pas d'effort de traction sur les deux demi-voiles Hi, ll∑- Les demi-voiles Hi, H2 présentent un lobe ou un mou I relativement important. Pour mémoire, le lobe I correspond à la distance pris au niveau du bord de fuite 13 entre le plan passant par les extrémités de chaque demi- voile (bout et centre de la voilure) et le sommet de la demi-voile. Pour cette configuration dite relâchée, il est à noter qu'il est obtenu un vrillage important en bout de voilure. Pour mémoire, le vrillage correspond à la différence d'incidence du profil de la voilure entre le centre et l'extrémité de la voilure. Figures 4 to 9 illustrate and illustrate the principle of the invention. The piloted modification system 20 thus makes it possible to modify the configuration of the flexible wing 11 in order to place the latter in a so-called relaxed configuration (FIGS.4 to 6) or in a so-called stretched position illustrated in FIGS. 7 to 9. In the so-called relaxed position (FIGS. 4 to 6), the spacing and approach mechanism 25 exerts practically no tensile force on the two half-wings Hi, II- sails Hi, H 2 have a relatively large lobe or slack. For the record, the lobe I corresponds to the distance taken at the trailing edge 13 between the plane passing through the ends of each half-sail (end and center of the wing) and the top of the half-sail. For this so-called relaxed configuration, it should be noted that there is a significant twisting at the end of the wing. For the record, twisting corresponds to the difference in the incidence of the profile of the wing between the center and the end of the wing.
Il est à noter que le système piloté 20 permet de passer rapidement à une configuration dite voile tendue telle qu'illustrée aux Fig. 7 à 9. Cette configuration voile tendue est particulièrement avantageuse pour une phase de vol rapide. Cette configuration voile tendue est obtenue en manœuvrant la manette de commande 22 afin de rapprocher les deux demi-voiles Hi, H2. Tel que cela ressort clairement des Fig. 7 à 9, le vrillage des bouts de voilure est diminué ainsi que les lobes I. Dans la mesure où le lobe I est minimal, l'aile 1 présente une parfaite stabilité de route sans tendance à l'engagement des mouvements de roulis. Le vrillage minimal des bouts de voilure procure le meilleur rendement aérodynamique aux faibles incidences et réduit les efforts de tangage. Le centre de poussée aérodynamique reculé augmente la vitesse à effort nul. It should be noted that the controlled system 20 makes it possible to quickly switch to a so-called taut sail configuration as illustrated in FIGS. 7 to 9. This stretched sail configuration is particularly advantageous for a rapid flight phase. This taut sail configuration is obtained by maneuvering the control lever 22 to bring the two half-sails Hi, H 2 . As is clear from Figs. 7 to 9, the kinking of the wingtips is decreased as well as the lobes I. Insofar as the lobe I is minimal, the wing 1 has a perfect road stability without tendency to engage the roll movements. The minimal twisting of the wingtips provides the best aerodynamic performance at the weak impacts and reduces pitching efforts. The center of retracted aerodynamic thrust increases the speed at zero effort.
Lors des phases d'approche et d'atterrissage ou lors d'un vol lent, le système piloté 20 est commandé pour placer la voilure souple 2 dans une configuration dite relâchée telle qu'illustrée aux Fig. 4 à 6. Comme expliqué ci-dessus, le lobe I de la voilure 2 est maximal autorisant un mouvement différentiel important et procurant une meilleure maniabilité en roulis. Le vrillage des bouts de voilure est également maximal de sorte que la partie centrale de la voilure décroche en premier pour garantir un comportement sain et sans surprise aux grandes incidences. Les augmentations du lobe I et du vrillage accroissent la traînée, ce qui est favorable pour l'obtention de pentes d'approches importantes. Le centre de poussée aérodynamique avancé diminue la vitesse à effort nul.  During the approach and landing phases or during a slow flight, the controlled system 20 is controlled to place the flexible wing 2 in a so-called relaxed configuration as illustrated in FIGS. 4 to 6. As explained above, the lobe I of the wing 2 is maximum allowing a significant differential movement and providing better handling in roll. The twisting of the wingtips is also maximum so that the central part of the wing picks first to ensure healthy behavior and no surprise at large incidences. Increases in lobe I and twisting increase drag, which is favorable for obtaining steep approach gradients. The advanced aerodynamic thrust center reduces the speed at zero effort.
Il est à noter que le système piloté 20 permet de contrôler avec précision la valeur de la tension transversale de la voile 11 et par suite, de contrôler avec précision les valeurs du lobe et du vrillage de la voilure souple. En d'autres termes, la voilure souple 2 peut prendre toutes les configurations intermédiaires entre la position tendue extrême et la position relâchée extrême.  It should be noted that the controlled system 20 makes it possible to precisely control the value of the transverse tension of the sail 11 and consequently to accurately control the values of the lobe and the twisting of the flexible wing. In other words, the flexible wing 2 can take all the intermediate configurations between the extreme stretched position and the extreme relaxed position.
Selon une caractéristique avantageuse de réalisation, l'aile 1 comporte également un système 50 de modification du réflex du profil de la voilure souple 2 dans la partie centrale de la voile. Pour mémoire, le réflex du profil d'une voilure souple 2 correspond au profil de la voilure 2 prise dans le plan vertical longitudinal et présentant, à partir du bord de fuite 13 et sur la partie arrière de la voilure souple 2, une concavité tournée vers le haut. En d'autres termes le réflex du profil d'une voilure souple correspond à un bord de fuite 13 surélevé.  According to an advantageous characteristic of embodiment, the wing 1 also comprises a system 50 for modifying the reflex of the profile of the flexible wing 2 in the central part of the sail. For the record, the reflex of the profile of a flexible wing 2 corresponds to the profile of the wing 2 taken in the longitudinal vertical plane and having, from the trailing edge 13 and on the rear portion of the flexible wing 2, a concavity turned to the top. In other words the reflex of the profile of a flexible wing corresponds to a trailing edge 13 raised.
Dans l'exemple de réalisation illustré, le système 50 de modification du réflex du profil de la voilure souple 2 comporte un organe de liaison entre les parties arrière de la voile soumises au mécanisme d'écartement et de rapprochement 25. Cet organe de liaison 50 passe en dessous de la quille 7 de manière à augmenter ou à diminuer le réflex R du profil central de l'aile souple respectivement lors du rapprochement ou de l'écartement des demi- parties Hi, H2 de la voile souple. Dans l'exemple illustré, cet organe de liaison est constitué par une sangle fixée sur les deux lattes longitudinales 30 au niveau sensiblement du bord de fuite 13. In the exemplary embodiment illustrated, the system 50 for modifying the reflex of the profile of the flexible wing 2 comprises a connecting member between the rear parts of the sail subjected to the spacing and approach mechanism 25. This connecting member 50 passes below the keel 7 so as to increase or decrease the reflex R of the central profile of the wing flexible respectively at the approximation or spacing of the half-parts Hi, H 2 of the flexible sail. In the example illustrated, this connecting member is constituted by a strap attached to the two longitudinal strips 30 at substantially the trailing edge 13.
En position relâchée de la voilure souple 2, telle qu'illustrée à la Fig. 6, l'organe de liaison 50 forme dans le plan vertical, une sorte de "V" ouvert délimité au centre par la quille 7 et à ses extrémités par les lattes longitudinales 30. Dans cette position relâchée, le réflex R du profil central de la voilure souple 2 est minimum. Quand le mécanisme 25 assure le rapprochement entre les deux demi-voiles Hi, H2 (Fig. 7 à 9), il apparaît que la configuration de l'organe de liaison 50 change conduisant à un resserrement du "V" conduisant à l'agrandissement en hauteur de l'organe de liaison 50 et à son resserrement au niveau de ses extrémités. Il s'ensuit que le bord de fuite 13 se relève dans la partie centrale de la voilure 2 de sorte que le profil de la voilure augmente son réflex R (Fig. 9). La comparaison entre les Fig. 6 et 9 permet de constater que le bord de fuite 13 est surélevé lors de la configuration tendue (Fig. 9) par rapport à la configuration relâchée (Fig. 6). In the relaxed position of the flexible wing 2, as illustrated in FIG. 6, the connecting member 50 forms in the vertical plane, a kind of "V" open delimited in the center by the keel 7 and at its ends by the longitudinal slats 30. In this relaxed position, the reflex R of the central profile of the flexible wing 2 is minimum. When the mechanism 25 ensures the connection between the two half-walls Hi, H 2 (Figures 7 to 9), it appears that the configuration of the connecting member 50 changes leading to a tightening of the "V" leading to the enlarging the height of the connecting member 50 and its tightening at its ends. It follows that the trailing edge 13 rises in the central part of the wing 2 so that the profile of the wing increases its reflex R (FIG 9). The comparison between FIGS. 6 and 9 shows that the trailing edge 13 is raised during the tensioned configuration (Fig. 9) with respect to the relaxed configuration (Fig. 6).
Le réflex central de la voilure 2 est augmenté simultanément avec la diminution du lobe et du vrillage des bouts de voilure. La diminution du lobe et du vrillage associée à l'augmentation du réflex du profil en partie central engendrent une diminution de traînée et donc une augmentation du rendement permettant des vitesses plus importantes pour une puissance donnée (moindre consommation, vitesse maximum en palier supérieur). De même, il est obtenu un réflex central diminué en combinaison avec une augmentation du lobe et du vrillage de bout de voilure. La diminution du réflex central permet d'obtenir la vitesse la plus basse possible.  The central reflex of the wing 2 is increased simultaneously with the decrease of the lobe and the kinking of the wingtips. The decrease of the lobe and twisting associated with the increase of the reflex of the profile in the central part generates a decrease in drag and therefore an increase in yield allowing higher speeds for a given power (lower consumption, maximum speed in upper tier). Likewise, a decreased central reflex is obtained in combination with an increase in wing tip lash and twisting. The reduction of the central reflex makes it possible to obtain the lowest possible speed.
La diminution de l'incidence du profil central entre le vol lent et le vol rapide due à l'augmentation du réflex modère l'amplitude du débattement de la barre de contrôle 5 entre les deux configurations, ce qui améliore l'ergonomie et le contrôle et accroît la plage de vitesse utilisable. Dans la description qui précède, la structure de pilotage 3 comporte uniquement un trapèze. Bien entendu, cette structure de pilotage 3 peut être différente. Par exemple, la structure de pilotage 3 peut comporter un tricycle accroché à la quille 7 afin de réaliser un ultraléger pendulaire. Decreasing the incidence of the central profile between the slow flight and the fast flight due to the increase of the reflex moderates the amplitude of the travel of the control bar 5 between the two configurations, which improves the ergonomics and the control and increases the usable speed range. In the above description, the control structure 3 comprises only a trapezium. Of course, this control structure 3 may be different. For example, the control structure 3 may comprise a tricycle hooked to the keel 7 in order to achieve an ultralight pendulum.
L'invention n'est pas limitée aux exemples décrits et représentés car diverses modifications peuvent y être apportées sans sortir de son cadre.  The invention is not limited to the examples described and shown because various modifications can be made without departing from its scope.

Claims

REVENDICATIONS
1 - Aile à voilure souple pilotée par déplacement du centre de gravité comportant :  1 - Wing with flexible wing driven by displacement of the center of gravity comprising:
- une voilure souple (2) comprenant une quille (7) de support pourvue d'au moins un longeron de bord d'attaque (8) délimitant une flèche, une voile souple (11) étant tendue sur le longeron pour délimiter un bord d'attaque (12) et un bord de fuite (13) et de part et d'autre, deux demi- voiles (Hi, H2),  a flexible wing (2) comprising a support keel (7) provided with at least one leading edge spar (8) delimiting an arrow, a flexible sail (11) being stretched on the spar to delimit an edge; attack (12) and a trailing edge (13) and on both sides, two half-sails (Hi, H2),
- et une structure de pilotage (3) supportée par la voilure souple, caractérisée en ce qu'elle comporte :  - and a control structure (3) supported by the flexible wing, characterized in that it comprises:
- un système piloté (20) de modification de la tension transversale de la voile (11) au niveau au moins de son bord de fuite (13) pour contrôler au moins le vrillage des bouts de la voilure et le lobe de la voilure,  - a controlled system (20) for modifying the transverse tension of the sail (11) at least at its trailing edge (13) to control at least the twisting of the wingtips and the lobe of the wing,
- et un dispositif (21) pour commander en vol le système de modification de la tension transversale (20), comportant un organe de commande (22) associé à la structure de pilotage (3).  - and a device (21) for controlling in flight the transverse voltage modification system (20), comprising a control member (22) associated with the control structure (3).
2 - Aile à voilure souple selon la revendication 1, caractérisée en ce que le système de modification de la tension transversale (20) comporte un mécanisme (25) d'écartement et de rapprochement des demi-voiles entre elles afin de diminuer ou d'augmenter la tension transversale de la voile au niveau sensiblement du bord de fuite (13) lors respectivement de l'écartement ou du rapprochement des demi-voiles.  2 - flexible wing wing according to claim 1, characterized in that the system for modifying the transverse tension (20) comprises a mechanism (25) for spacing and bringing the half-webs together to reduce or increasing the transverse tension of the sail at substantially the trailing edge (13) respectively spacing or bringing closer the half-sails.
3 - Aile à voilure souple selon la revendication 2, caractérisée en ce que le mécanisme d'écartement et de rapprochement (25) agit sur les deux demi-voiles par l'intermédiaire de deux lattes (30) s'étendant longitudinalement sensiblement du bord d'attaque (12) jusqu'au bord de fuite (13) et de part et d'autre de la quille (7) pour s'étendre dans la partie centrale de la voilure souple.  3 - flexible wing wing according to claim 2, characterized in that the spacing mechanism and approach (25) acts on the two half-webs through two slats (30) extending longitudinally substantially from the edge driving (12) to the trailing edge (13) and on both sides of the keel (7) to extend into the central portion of the flexible wing.
4 - Aile à voilure souple selon l'une des revendications 1 à 3, caractérisée en ce que la voile souple (11) comporte à partir du mécanisme d'écartement et de rapprochement (25) et en direction des bouts d'aile, des renforts transversaux (41) sur lesquels agit le mécanisme d'écartement et de rapprochement (25). 4 - flexible wing wing according to one of claims 1 to 3, characterized in that the flexible sail (11) comprises from the spacing mechanism and approach (25) and towards the wing tips, reinforcement transversals (41) on which the spacing and closing mechanism (25) acts.
5 - Aile à voilure souple selon l'une des revendications 2 à 4, caractérisée en ce qu'elle comporte un organe de sécurité (40) pour limiter l'écartement entre les deux demi-voiles à une valeur limite.  5 - flexible wing wing according to one of claims 2 to 4, characterized in that it comprises a safety member (40) to limit the spacing between the two half-sails to a limit value.
6 - Aile à voilure souple selon l'une des revendications 2 à 5, caractérisée en ce que la voile souple (11) comporte entre les deux demi-voiles (Hi, ll∑), une bande élastique de compensation d'écartement (45). 6 - flexible wing according to one of claims 2 to 5, characterized in that the flexible sail (11) comprises between the two half-webs (Hi, ll Σ ), an elastic spacer compensation band (45 ).
7 - Aile à voilure souple selon la revendication 2, caractérisée en ce que le mécanisme d'écartement et de rapprochement (25) comporte des palans (32) fixés sur les demi-voiles tandis que le dispositif de commande (21) comporte un câble (23) actionnant les palans et monté jusqu'à un enrouleur (36) dont le pilotage en rotation est assuré par l'organe de commande (22).  7 - flexible wing wing according to claim 2, characterized in that the spacing mechanism and approach (25) comprises hoists (32) fixed on the half-sails while the control device (21) comprises a cable (23) actuating the hoists and mounted to a winder (36) whose rotation control is provided by the control member (22).
8 - Aile à voilure souple selon l'une des revendications 1 à 7, caractérisée en ce qu'elle comporte un système (50) de modification du réflex (R) du profil de la voilure souple (2), dans la partie centrale de la voilure souple.  8 - flexible wing wing according to one of claims 1 to 7, characterized in that it comprises a system (50) for modifying the reflex (R) of the profile of the flexible wing (2), in the central portion of the flexible wing.
9 - Aile à voilure souple selon la revendication 8, caractérisée en ce que le système (50) de modification du réflex (R) du profil de la voilure souple (2) comporte un organe de liaison entre les parties arrières de la voile soumises au mécanisme d'écartement et de rapprochement (25), cet organe de liaison passant en dessous de la quille (7) de manière à augmenter ou diminuer le réflex (R) du profil central de la voilure souple respectivement lors du rapprochement ou de l'écartement des deux-demi voiles (Hi, H2). 9 - flexible wing according to claim 8, characterized in that the system (50) for modifying the reflex (R) of the profile of the flexible wing (2) comprises a connecting member between the rear parts of the sail subjected to spacing mechanism and approach (25), this connecting member passing below the keel (7) so as to increase or decrease the reflex (R) of the central profile of the flexible wing respectively at the approximation or the spacing of two-half sails (Hi, H 2 ).
10 - Aéronef à voilure souple, caractérisé en ce qu'il comporte une aile (1) conforme à l'une des revendications 1 à 9 dont la structure de pilotage (3) comporte un tricycle accroché à la quille (7).  10 - Aircraft flexible wing, characterized in that it comprises a wing (1) according to one of claims 1 to 9, the steering structure (3) comprises a tricycle attached to the keel (7).
PCT/FR2010/051777 2009-08-27 2010-08-26 Wing having a flexible wing structure and controlled by moving the center of gravity WO2011023908A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0955833A FR2949433B1 (en) 2009-08-27 2009-08-27 FLEXIBLE AND PILOTAGE WING WING BY DISPLACING THE CENTER OF GRAVITY
FR0955833 2009-08-27

Publications (1)

Publication Number Publication Date
WO2011023908A1 true WO2011023908A1 (en) 2011-03-03

Family

ID=41809230

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/FR2010/051777 WO2011023908A1 (en) 2009-08-27 2010-08-26 Wing having a flexible wing structure and controlled by moving the center of gravity

Country Status (2)

Country Link
FR (1) FR2949433B1 (en)
WO (1) WO2011023908A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018218370A1 (en) * 2017-06-01 2018-12-06 Romaeris Corporation Unmanned aerial vehicle with synchronized sensor network

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3936012A (en) 1974-05-03 1976-02-03 Murray Stephen C Hang glider
EP0109906A1 (en) * 1982-11-19 1984-05-30 Jean-Louis Darlet Ultralight glider and sail for the same
DE4308758A1 (en) * 1993-03-19 1994-09-22 Peter Erb Control aid for hang-gliders and ultralight aircraft (trikes)

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3936012A (en) 1974-05-03 1976-02-03 Murray Stephen C Hang glider
EP0109906A1 (en) * 1982-11-19 1984-05-30 Jean-Louis Darlet Ultralight glider and sail for the same
DE4308758A1 (en) * 1993-03-19 1994-09-22 Peter Erb Control aid for hang-gliders and ultralight aircraft (trikes)

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
AIR CRÉATION: "Manuel de Maintenance, Aile Type: Bionix 15", XP002606915, Retrieved from the Internet <URL:http://www.aircreation.fr/LinkClick.aspx?fileticket=jwYq6Lvon6w%3d&tabid=28&mid=759&language=en-US> [retrieved on 20101026] *

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018218370A1 (en) * 2017-06-01 2018-12-06 Romaeris Corporation Unmanned aerial vehicle with synchronized sensor network
CN110719874A (en) * 2017-06-01 2020-01-21 罗马里斯公司 Unmanned aircraft with synchronous sensor network
EP3630600A4 (en) * 2017-06-01 2021-03-10 Romaeris Corporation Unmanned aerial vehicle with synchronized sensor network
US11635772B2 (en) 2017-06-01 2023-04-25 Romaeris Corporation Unmanned aerial vehicle with synchronized sensor network

Also Published As

Publication number Publication date
FR2949433A1 (en) 2011-03-04
FR2949433B1 (en) 2011-09-16

Similar Documents

Publication Publication Date Title
EP0202271B1 (en) Propulsive wing with inflatable armature
EP0511050B1 (en) Device with at least one aerodynamically shaped element with changeable geometry, incorporating a control system of the boundary layer
WO2012101352A1 (en) Motorized aeroplane with hybrid hydrodynamic and aerodynamic structure for taking off and landing on water, the ground or snow
FR2479132A1 (en) HIGH PERFORMANCE BLADE FOR HELICOPTER ROTOR
CA2534404C (en) Rigid wing with variable sustentation due to deployment of a flexible wing
CA1326409C (en) Sailboat with lifting and anti-listing device
WO2011023908A1 (en) Wing having a flexible wing structure and controlled by moving the center of gravity
EP0151591B1 (en) Rigging particularly for sailing board
EP0148805A2 (en) Rigging with high slenderness and simplified handling
FR2462337A1 (en) SAILING EQUIPMENT WITH AUTOMATIC COUNTER-GITE
EP0109906A1 (en) Ultralight glider and sail for the same
WO1990005663A1 (en) Kite frame with inflatable compartment wing
FR2629420A1 (en) WING WITH MULTIPLE PANS
EP1544100A1 (en) Method for reducing the aerodynamic forces on an elevator of an aircraft during takeoff
FR2725418A1 (en) THICK PROFILE RIGGING FOR SAILING BOAT
FR2628698A1 (en) High-performance sailing craft - has steerable lifting sail mast and steerable floats at corners of triangular platform
FR2639605A1 (en) Flexible flying wing provided with towing cables intended in particular for towing a boat
FR2973774A1 (en) METHOD FOR IMPROVING THE AERODYNAMIC EFFICIENCY OF A VERTICAL AIRCRAFT TENSION
FR2940784A1 (en) Multihull sailing ship i.e. catamaran, has adjustment unit, and vertical rotation axle that is arranged at connection arms or hulls to allow rotation of connection arms with respect to hulls in horizontal plane of platform
FR2901539A1 (en) Conjugated component set used in making ultra-light aircraft includes fuselage, wings, empennage, landing gears, control system, fuel system with metal tank fixed in same level of motor, exhaust, lid, valve system, and motor propulsion unit
FR2595655A1 (en) Boat with thick sail which is orientable along three axes
EP3778376A1 (en) Autonomous traction wing
EP4308450A1 (en) Tethered-wing traction system including folding into a windsock
FR2937616A1 (en) RIGGING FOR VEHICLE PROPULSION SAIL AND VEHICLE EQUIPE OF SUCH A RANGE
FR2875786A1 (en) WING DEVICE FOR LIGHT AIRCRAFT, IN PARTICULAR AN AIRCRAFT, COMPRISING A STRUCTURAL STRUCTURE OF THE TUBULAR TYPE.

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 10763753

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 10763753

Country of ref document: EP

Kind code of ref document: A1