WO2013123604A1 - Aile en matériau flexible - Google Patents

Aile en matériau flexible Download PDF

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Publication number
WO2013123604A1
WO2013123604A1 PCT/CH2013/000025 CH2013000025W WO2013123604A1 WO 2013123604 A1 WO2013123604 A1 WO 2013123604A1 CH 2013000025 W CH2013000025 W CH 2013000025W WO 2013123604 A1 WO2013123604 A1 WO 2013123604A1
Authority
WO
WIPO (PCT)
Prior art keywords
pressure
wing
tension
pneumatic support
pneumatic
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/CH2013/000025
Other languages
German (de)
English (en)
Inventor
Roland VERHEUL
Rolf Luchsinger
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Prospective Concepts AG
Eidgenoessische Materialpruefungs und Forschungsanstalt
Original Assignee
Prospective Concepts AG
Eidgenoessische Materialpruefungs und Forschungsanstalt
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 Prospective Concepts AG, Eidgenoessische Materialpruefungs und Forschungsanstalt filed Critical Prospective Concepts AG
Priority to EP13705900.2A priority Critical patent/EP2817212A1/fr
Publication of WO2013123604A1 publication Critical patent/WO2013123604A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • B64C31/06—Kites
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H8/00—Sail or rigging arrangements specially adapted for water sports boards, e.g. for windsurfing or kitesurfing
    • B63H8/10—Kite-sails; Kite-wings; Control thereof; Safety means therefor
    • B63H8/12—Kites with inflatable closed compartments
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • 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
    • B64C31/06—Kites
    • B64C2031/065—Kites of inflatable wing type

Definitions

  • the present invention relates to an aerofoil according to the preamble of claim 1.
  • An aerofoil of said type is known from WO 2 1010 094 145, as a further development of kites as known from the prior art.
  • the wing according to WO 2010/094 145 has a curved pneumatic support which extends transversely across its entire width and thus realizes two significant advantages: First, it is possible to give the wing a self-stabilizing V-shape in flight, and secondly Due to the rigidity of the pneumatic carrier used, only a comparatively small number of cranks are required to safely control the wing.
  • such wings can serve land based the alternative Energygewsn Vietnamese, namely at a height of several hundred meters or more use the prevailing wind currents where the wind speeds are higher and more uniform than in the immediate vicinity of the ground,
  • the wing has little mass, and that the number of lines can be reduced because increased mass reduces the energy to be gained and each tether especially at higher altitudes means a not to be underestimated flight resistance, which also the energy to be gained is reduced.
  • Alternative energy can be obtained, for example, that a wing unwinds a rope from a drum, the rotation of the drum is used to generate energy. After the unwinding of the rope, the wing can "fly down" (ie in the direction of the drum, which may be directed obliquely downwards) onto the drum and rewind the rope with little energy consumption. This is followed again by a load cycle until the seed is unwound.
  • the wing shown does not bestow the optimum efficiency because, despite its advantages (reduced number of lines due to stiffly shaped wings and stabilized flight through V-shape), the simple covering that forms its wing surface tends to flutter which makes higher speeds more difficult, especially higher speeds However, they are desirable because the buoyancy of the wing, and ultimately its bearing capacity or, in the case of the abovementioned example of land-based energy production, the power provided via the line increases with the square of the wing speed.
  • a wing-bound wing for example, to provide a trajectory over ground in the form of a victory eight, which means that the wing moves against the ground, so it can be flowed through much faster by the wind, as it relative to the ground prevailing wind speed corresponds.
  • This makes it possible to achieve very high buoyancy values which can only be achieved if the wing itself is designed for high efficiency, which includes various parameters such as angle of attack, suitable load profile (vortex formation) and high speed.
  • the lowest weight of the structure remains in order not to reduce the usable power.
  • tube kites Various designs of tube kites are known from the state of the art, i3, DE 10 2005 014 848, where the fluttering upper membrane is stabilized by battens and at least in the inflow area is brought into a curvature which corresponds to a wing profile. From DE 10 2009 009 305 it is known to equip a tube kite with a lower sail, so that turbulences can be reduced immediately behind the tube.
  • the Front Tube of the Tube Kites ensures minimum stability of the glider when launching and landing the glider, which often allows take-off and landing. In flight, however, especially in the power phase, the stabilizing effect of the Front Tube is too small compared to the operating forces acting on the screen even for a favorable stabilizing residual effect. Accordingly, the contour of the FrontTube is designed for the approximate contour during operation; a different shape could lead to the destruction of the per se flexible front tube.
  • Object of the present invention is to provide a wing of the type mentioned with high efficiency and lowest weight, which is also suitable to produce high power lines on the ground,
  • the inventive arrangement results in a very light wing, which is stiff enough for high flow velocities associated with high lift for only a few load points and has a suitable TragluftiprofSl through upper and lower membrane
  • the low weight of the wing results from the use of flexible components that can be designed as a fabric. It follows, tlass by the erfindungsgernässe arrangement on the ground high power can be generated.
  • FIG. 2 shows a cross section through the wing of FIG. 1 at the location of a side wall
  • FIG. 3 a section of the wing according to the invention in a view from the front
  • FIG. 4 a view of the wing according to the invention from the front
  • FIG. 5 shows a view from below of a section of the wing according to the invention
  • FIG. 8 shows a section of the wing according to the invention in a view from above
  • FIG. 7 shows the wing in a further view from below
  • FIG. 8 shows the wing in a further view from FIG above
  • Fig. 9 shows another embodiment of a side wall
  • Fig. 11 is a view of a node between interconnected pneumatic
  • Figure 1 shows an inventive wing 1 in a view from below. It can be seen in principle flat or flat sections of the wing, these sections are slightly angled against each other (sections A and B) and strong (sections B and C). The entire arrangement consists essentially of textile fabric, but at the same time is extremely stiff, resulting in a wing with high buoyancy, the lines over 2 is provided as a traction. This arrangement makes it possible to drive high flow velocities of, for example, 2 m / s to 60 m / s or more, and to achieve a lift of approximately 50 kg or more per m 2 of airfoil felts. Such wings can reach an area of 10m 2 , 15m 2 or up to several hundred m 2 , without the internal structure being overstressed by the forces acting on the wing.
  • the wing 1 has end sections C set almost vertically, which in the present case serve to align the wing in the wind, so that it is always flowed from the front and only slightly laterally. This is especially be! an iron-guided wing of advantage.
  • the figure shows an example lower textile membrane 3, which forms the lower surface of the wing 1, which is surrounded by the wind, while the corresponding (textile) upper membrane 4 is hidden in the figure, that is, not visible.
  • the lower membrane 3 and the upper membrane 4 may also be non-textile and may consist, for example, of a plastic film or any other suitable material which is suitable for covering the airfoil
  • openings 5 are located in the dynamic pressure region of the leading edge of the wing profile, so that a corresponding inner area of the wing is under increased pressure during operation.
  • openings 5 are located in the dynamic pressure region of the leading edge of the wing profile, so that a corresponding inner area of the wing is under increased pressure during operation.
  • only such an opening can be provided at any location of the wing with sufficient external pressure.
  • Such an opening is not provided in an embodiment (not shown) of the wing according to the invention, the necessary internal pressure being generated via a gas pressure reservoir drawn from a pressure accumulator.
  • connecting lines 8 of the lower diaphragm 3 with inner side walls 10 (FIG. 2) of inner pressure lines 35 (FIG. 6) which constrict the lower diaphragm 3 shallowly and fix it in accordance with the wing profile.
  • the same constricting 6 in the upper membrane are concealed in the present view, ie not visible.
  • FIG. 2 shows a cross section through the wing 1 at the location of a side wall IG, which is also flexibly formed, that is to say, for example, may consist of a textile fabric (or another suitable material).
  • the side wall 10 has an outline 11, which in FIG Substantially corresponds to the desired airfoil profile of the wing at the site of the side wall and has openings 12 which allow air to pass through the side wall 10.
  • a Druckgiied 13 extends in the illustrated preferred embodiment along the lower edge of the side wall 10. Further, a tension member 14 extends along the upper edge of the side wall 10. At the rear edge 15 of the Tragflugis 1, the pressure member 13 and the tension member 14 with operatively connected to one another in a node 16. The node 18 is designed 15 such that acting through this connection in the tension member 14 tensile forces on Druckgiied 13 and this can put under compressive stress.
  • the pressure member 13 is formed as a thin rod, for example made of carbon fiber or Glasmaschinewerkstof- fen or other suitable material, and with high kink resistance.
  • the tension member 14 which could also be designed to be flexible in its capacity as a tension member, but here preferably as a thin rod is formed, which can also take on tensile forces in the event of a negative load of Traglügelabschnitfs.
  • the compound of the side wall 10 with the jeweiüge upper membrane 4 or lower membrane 3 through sewed, that is prepared by a seam, in which case for the pressure member 13 or the tension member 14 is also on the connecting parts sewn and this along extending textile bag, analogous to the tab 40 of Figure 11 ⁇ seen 30 before.
  • a pneumatic support 20 extends transversely through the wing 1.
  • the carrier has an operating pressure inflatable, rod-shaped flexible sheath 21 and a pressure element 22 associated therewith and a tension member associated therewith 23, which elements along the length of the sheath 21 along and during operation (ie standing under operating pressure sheath 21) by this at a distance are held by each other.
  • FIG. 10 shows a specific embodiment for the production of the pneumatic carrier 20. The mode of operation of the (front) pneumatic carrier 20 will be described below with reference to FIG.
  • the shell 21 either made of gas-tight material, or can be performed with an inserted into them, gas-tight bubble, but in any case consists of low-stretch, tensile material, It is also conceivable in the pressure cells 35 gas-tight Inserting bubbles, which are then in turn connected to the openings 5, in the illustrated embodiment, a rear pneumatic support 27 is located in the illustrated embodiment, with a flexible shell 28, which is also inflatable to an operating pressure, with a Druckeiement 19 and a tension element 30th cooperates, these elements 30,31 of the length of the shell 28 along. In contrast to the (front) pneumatic carrier 20, no web is provided in the rear pneumatic carrier 27 in the present embodiment.
  • FIG. 3 shows the section A (FIG. 1) of the wing 1 in a front view, wherein the textile fabrics of the upper membrane 4, the lower embankment 3 and the shell 21 of the (front) pneumatic support 20 are shown in a transparent manner such that the view of the textile web 24 and the extending in this Switzerlandiement 23 fäilt.
  • the side wall shown in FIG. 2 is located in FIG. 3 at location 10 * or at location 10 **.
  • the tension member 23 extends arcuately, preferably in the path of a reverse chain line, along the web 24 along, preferably in sewn on this pocket, so that it is roughly fixed in position. At its ends, it is operatively connected to the pressure member 22 in a knot 25, the knot 25 being designed such that tension exerted by the tension element 24 acts on the pressure element 22, which is then correspondingly under pressure but withstands this stress. so that the distance of the nodes 25 is maintained.
  • the lines 2 (FIG. 1) act on the node 25, the nodes 25 are correspondingly also designed as load points.
  • the pneumatic support 20 is stiff with respect to the buoyancy forces introduced into it, the buoyancy forces being able to be taken into the knot 25, for example, by means of lines 2.
  • the nodes 25 are accordingly also designed as load points for the wing 1.
  • the nodes 25 may represent wing suspension points, for example, on a fuselage,
  • FIG. 1 shows the airfoil 1 (FIG. 1) in a view from the front, again partially transparent, so that the (front) pneumatic supports 20 with their structure (web 24, pressure element 22 and tension element 23) can be seen five rigid, super-light, high loadable wing sections A, B, C with precisely defined wing profiles, suitable to be flown at various angles of attack and high to high speeds, except for the compression elements 22 and, depending on the embodiment, tension elements 23 of flexible material, preferably consist of a textile fabric.
  • Figure 4 shows an aerofoil having at least one transverse flat major section for buoyancy and adjoining thereto at an angle from the main section or end sections which also comprise a transverse pneumatic support with operatively connected compression and tension members wherein the adjacent portions of the pneumatic supports have a common node in the joint of the adjacent wing sections.
  • the specific design of such a common node 25 is shown in more detail below with reference to FIG 10,
  • Figure 5 shows a view from below of the section A of the wing 1 ( Figure 1), wherein the lower membrane 3 is held transparent to the underlying Henden Structures visible do. Obvious is the (front) pneumatic support 20 and the pressure element 22, which here the bar 24 ( Figures 3 and 4) covered.
  • the pressure members 13 of the side walls lö f which are also hidden by the pressure members 13 here.
  • the Druckgiied 19 keeps the node 29 at a distance, so that the intrinsically flexible structure does not collapse under the attack of buoyancy forces, but remains rigid and thus can fulfill their function, namely buoyancy forces lying between the nodes 29 wing sections A, B or C ( Figure 1) in this initiate.
  • the pneumatic supports 20, 27 are stiff with respect to the buoyancy forces introduced therein, and the buoyant forces in the knots 19, 29 can be removed, for example, by lines 2 or stops on an aircraft fuselage.
  • the knots 19, 29 are accordingly also designed as load points for the wing 1.
  • the front pneumatic support can also be designed with tension elements running around it in a spiral manner, for example in an embodiment comprising only one front pneumatic support.
  • an embodiment according to the invention is one in which the rear pneumatic support also has a web with a tension element extending therein,
  • FIG. 6 shows, by way of example, the section A of the wing 1 (FIG. 1) in a view obliquely from above, wherein in turn the upper membrane 3 is shown in transparent so that the view of the inner structure of the wing 1 remains free.
  • the (front) carrier 20 with the web 24, in which the tension element 23 is arranged and in the node 25 with the pressure element 22 is operatively connected. Also shown is the rear pneumatic support 27 with its under operating pressure shell 28, the pressure element 19 and the two helically extending tension elements 30,31-
  • side walls 10 with their compression members 13 and tension members 14, wherein the side walls are preferably sewn to the upper membrane 4 and the lower membrane 3, but can also be connected to other, familiar to those skilled in the art with each other.
  • the side walls 10 are sewn to the shell 21 of the (front) pneumatic support 20, as well as the shell 28 of the rear pneumatic support 27 and thus attack the pneumatic support 20,27 operable (in the present case, the side walls IG embrace the carrier 20,27 completely), db, such that buoyancy forces introduced into it are in turn introduced into the pneumatic supports 20, 27, at least partially in their pressure members 22, 29 and possibly partly in their shells 21, 28.
  • connection of the side walls 10 with the pneumatic supports 20,27 also over the cross section of the carrier 20,27 adapted annular opplungsgiieder, for example, of a plastic or carbon fiber material, which surround the carrier, are provided. Operable the connection is then when the buoyancy forces in flight reliably from the side winds 10 are introduced into the pneumatic support 20,27.
  • the side walls 10 of the pressure cells 35 are directly connected to the upper membrane 4 and the lower membrane 3, such that portions of the upper membrane 4 and the lower membrane 3 form the upper side and the lower surface of the pressure cells 35 and thus the buoyancy forces acting on them be introduced into the side walls.
  • the loaded in flight by the buoyancy forces areas of the upper diaphragm 4 and the lower diaphragm 3 are supported on the side walls 35, which in turn are stretched by the pressure prevailing in the pressure lines 35 operating pressure and thus stiff. Accordingly, the buoyancy forces are introduced into the side walls 10 and in turn introduced by them (see above) in the pneumatic carrier.
  • the surfaces of the wing are formed by a flexible upper membrane 4 and a flexible lower membrane 3, and he built over its transverse dimension in a number of juxtaposed pressure cells 35 without load points.
  • the flexible side walls 10 in outline substantially correspond to the TragfiügelprofÜ be stretched by the operating pressure in the print line 35 and attack on the pneumatic support 20,27 operable, such that in operation buoyancy forces each associated wing section in the side walls and of these be introduced into the pneumatic carrier,
  • the buoyant forces transmittable by the side walls 10 are increased in a preferred embodiment by the combination of the pressure members 13 and traction members 14 provided at the edges of the side walls, which are preferably operatively connected at their ends in a node, the node being formed in the tension members
  • the knots are formed by the pneumatic supports 20, 27 by fixing the ends of the pressure members 13 and tension members 14 to their sheaths 21, 28.
  • the compression or tension members 13, 14 can also be fixed to the web, for example by a loop sewn thereto, which enters a groove or on a transverse bolt at the end of the pressure or tension member 13, 14 attacks (analogous to the attachment of the tension elements according to Figure 11 ⁇ .
  • FIGS. 7 and 8 show the wing 1 in a view from below (FIG. 7) and from above (FIG. 8), wherein the lower membrane 3 and the upper membrane 4 are kept transparent in order to increase the inner structure of the wing 1 demonstrate.
  • the webs 24 of the pneumatic supports 20 are formed of a continuous textile strip which passes through the end of the one carrier 20 without interruption and continues in the next carrier 20.
  • the pressure members 13 and tension members 14 are drawn beyond the (front) pneumatic carrier 20, as shown in more detail in FIG.
  • Figure 9 shows a sidewall 10 with load points, i. at the place of knots 19,29.
  • the pressure member 13 and the tension member 14 are further advanced over the (front) pneumatic support 20, preferably integrally around the leading edge of the wing. This advantageously stabilizes the leading edge, in addition to the overpressure due to the openings 5, to the upper membrane lower membrane from the forces due to the incoming wind.
  • FIG. 10 shows a cross-section through the (front) pneumatic carrier 20. Shown is the casing 21, as well as the web 24 embodied here in duplicate, in which the tension element 23 is arranged.
  • the pressure member 22 is located in a tab 40,
  • the figure shows that here by two flexible fabric each half of the Hüüe and the double-walled web is formed, which allows, among other things, in a particularly simple way to fix the tension element by means of a reinforcing strip 42 via sutures 41 in its position. Seams 43 fix the Druckgüed 22 between the walls of the web 24 and thus also on the shell 21, The arrangement shown allows the above-described interaction of the elements of the pneumatic support 20th
  • FIG. 11 shows, by way of example, a node 29 between two adjacent (front) pneumatic supports 20.
  • the ends of the pressure elements 22 tapering on one another have transverse bolts in which soft loops 46 are suspended at the end of the associated tension elements 23. Between these loops a leash 2 is arranged over its end loop 2 '. This configuration ensures the above-described function of the nodes 29.
  • the two abutting pressure elements 23 with each other via an elastically deformable element, preferably an existing rubber gusset 47, connected, which gives the connection between the sections A, B and C of the wing 1 a certain elasticity, so that spikes in this area can be avoided.
  • the nodes 35 of the rear pneumatic support 27 can basically be constructed the same, but with the difference that then two tension elements are hooked with the corresponding loops in the Querboizen.
  • At least one of the pneumatic supports is provided with a sleeve which is not cylindrical but spindle-shaped, the pressure element and the tension member then extending along an axis of the spindle and the knots at the tips of the spindle Spindle are provided.
  • the Buchelement is designed as a load-bearing rod, while the pressure element can also absorb train.
  • the tension element 23, 30, 31 is in at least one of the pneumatic supports 20, 27 stiff, for receiving also pressure, and the pressure element 22,19 associated therewith also designed tensile strength
  • wing with a pneumatic support structure having a transversely extending therethrough pneumatic carrier wherein the carrier has an inflatable to an operating pressure, rod-shaped flexible sheath and a pressure element associated therewith and a tension member associated therewith which stiffen the shell under operating pressure and are operatively connected at their ends to each other in a knot, at least one opening being provided at the leading edge thereof in the dynamic pressure region, such that an inner region of the wing is under increased pressure during operation.
  • Such an embodiment may then be supplemented with features according to the dependent claims, i. in particular provided with in the wing pressure cells 35, whose side walls are stretched by the operating pressure.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • Tents Or Canopies (AREA)

Abstract

L'invention concerne une aile (1) pourvue d'une structure de support pneumatique, qui comporte un support pneumatique (20, 27) s'étendant transversalement à travers cette structure. Le support comporte une enveloppe flexible (21, 28) en forme de barre pouvant être gonflée à une pression de service, ainsi qu'un élément de pression (22, 19) associé à cette enveloppe, et un élément de traction (23, 30, 31) également associé à cette enveloppe, ces éléments s'étendant le long de la longueur de l'enveloppe (21, 28) et étant retenus à distance les uns des autres par cette enveloppe durant l'utilisation. L'élément de pression (22, 19) et l'élément de traction (23, 30, 31) sont en liaison fonctionnelle l'un avec l'autre à leurs extrémités et forment à chaque fois un nœud (29, 35). Les surfaces de l'aile (1) sont formées par une membrane supérieure flexible (3) et une membrane inférieure flexible (4), et l'aile est divisée sans points de charge sur toute sa dimension transversale en un certain nombre de cellules de pression (35) disposées les unes à côté des autres.
PCT/CH2013/000025 2012-02-22 2013-02-11 Aile en matériau flexible Ceased WO2013123604A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP13705900.2A EP2817212A1 (fr) 2012-02-22 2013-02-11 Aile en matériau flexible

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH233/12 2012-02-22
CH00233/12A CH706134A1 (de) 2012-02-22 2012-02-22 Tragflügel aus flexiblem Material.

Publications (1)

Publication Number Publication Date
WO2013123604A1 true WO2013123604A1 (fr) 2013-08-29

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ID=47749586

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CH2013/000025 Ceased WO2013123604A1 (fr) 2012-02-22 2013-02-11 Aile en matériau flexible

Country Status (3)

Country Link
EP (1) EP2817212A1 (fr)
CH (1) CH706134A1 (fr)
WO (1) WO2013123604A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4400407B1 (fr) 2023-01-12 2025-06-04 Ozone Kites Ltd. Voile d'aile

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3285546A (en) 1964-10-01 1966-11-15 Space Recovery Res Ct Inc Multi-cell wing type aerial device
US4129272A (en) * 1976-08-23 1978-12-12 Jones Andrew W Aerofoil structure
US5244169A (en) 1992-05-15 1993-09-14 Vertigo, Inc. Inflatable structure paraglider
DE4308437A1 (de) * 1993-03-17 1994-09-22 Jordanis Melitopoulos Aerodynamische Vorrichtung mit mindestens einer aufblähbaren flexiblen Tragfläche
DE102005014848A1 (de) 2005-02-23 2006-08-24 Boards & More Ag, Clarens Tubekite
US20090199489A1 (en) * 2008-02-12 2009-08-13 Brown Glen J Externally braced inflatable structures
WO2010094145A2 (fr) 2009-02-17 2010-08-26 Empa Support pneumatique incurvé
DE102009009305A1 (de) 2009-02-12 2010-08-26 Achilles, Peter, Dipl.-Ing. Tubekite mit Untersegel
WO2010094135A1 (fr) 2009-02-23 2010-08-26 2G Robotics Inc. Ensemble dispositif de balayage à laser
WO2011155850A1 (fr) * 2010-06-02 2011-12-15 Aquadria Kite Design Limited Perfectionnements apportés à une aile gonflable

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3285546A (en) 1964-10-01 1966-11-15 Space Recovery Res Ct Inc Multi-cell wing type aerial device
US4129272A (en) * 1976-08-23 1978-12-12 Jones Andrew W Aerofoil structure
US5244169A (en) 1992-05-15 1993-09-14 Vertigo, Inc. Inflatable structure paraglider
DE4308437A1 (de) * 1993-03-17 1994-09-22 Jordanis Melitopoulos Aerodynamische Vorrichtung mit mindestens einer aufblähbaren flexiblen Tragfläche
DE102005014848A1 (de) 2005-02-23 2006-08-24 Boards & More Ag, Clarens Tubekite
US20090199489A1 (en) * 2008-02-12 2009-08-13 Brown Glen J Externally braced inflatable structures
DE102009009305A1 (de) 2009-02-12 2010-08-26 Achilles, Peter, Dipl.-Ing. Tubekite mit Untersegel
WO2010094145A2 (fr) 2009-02-17 2010-08-26 Empa Support pneumatique incurvé
WO2010094135A1 (fr) 2009-02-23 2010-08-26 2G Robotics Inc. Ensemble dispositif de balayage à laser
WO2011155850A1 (fr) * 2010-06-02 2011-12-15 Aquadria Kite Design Limited Perfectionnements apportés à une aile gonflable

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4400407B1 (fr) 2023-01-12 2025-06-04 Ozone Kites Ltd. Voile d'aile

Also Published As

Publication number Publication date
CH706134A1 (de) 2013-08-30
EP2817212A1 (fr) 2014-12-31

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