• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to an airborne device (10) comprising at least three supporting wings (12) and a connecting device (18), the wings being interconnected by first flexible cables (16), each wing being, in addition, connected to the connecting device (18) by a second flexible cable (20), the connecting device being connected to a third flexible cable (22) intended to be connected to a base (46, 48), the first, second and third cables being stretched when the airborne device is put in the wind.
    公开号:FR3023876A1
    申请号:FR1457001
    申请日:2014-07-21
    公开日:2016-01-22
    发明作者:Rogelio Lozano
    申请人:Institut Polytechnique de Grenoble；
    IPC主号:
    专利说明:

    [0001] The present application relates to an airborne device for the conversion of the kinetic energy of wind into mechanical energy. B13338 - RT 2014 001
    [0002] BACKGROUND OF THE INVENTION Airborne devices used for converting wind kinetic energy into mechanical energy generally include a kite or aerostat. One advantage is that such airborne devices can be used at high altitudes where the winds are generally stronger and / or more regular than at lower altitudes. The airborne device can be used for traction of a vehicle, for example a boat. The airborne device can be used to drive an electric generator. The electric generator can be carried by the airborne device or be located on the ground. The airborne device then forms an airborne wind turbine that allows the conversion of the kinetic energy of the wind into electrical energy. A disadvantage of airborne devices, especially when used as an airborne wind turbine, is the low efficiency, particularly in comparison with a conventional wind turbine. In addition, the structure of the airborne devices can be complex and control of the trajectory followed by the airborne device can be difficult. SUMMARY An object of an embodiment is to overcome some or all of the disadvantages of the previously described airborne devices used for the conversion of kinetic wind energy into mechanical energy. Another object of an embodiment is to increase the efficiency of the airborne device. Another object of an embodiment is that the airborne device has a simple structure. Another object of an embodiment is that the trajectory followed by the airborne device can be controlled in a simple manner. For this purpose, an embodiment provides an airborne device comprising at least three load-bearing wings and a connecting device, the wings being interconnected by first flexible cables, each wing being further connected to the connecting device by a second flexible cable, the connecting device being connected to a third flexible cable to be connected to a base, the first, second and third cables being tensioned when the airborne device is vented. According to one embodiment, the device does not comprise rigid reinforcement connecting the wings to each other. According to one embodiment, the connecting device comprises a first part connected to a second part, the second cables being fixed to the first part and the third cable being fixed to the second part, the first part being adapted to pivot relative to in the second part. According to one embodiment, at least one of the wings comprises at least a first actuator adapted to modify the length of the portion of one of the first cables stretched between said wing and one of the other wings.
    [0003] According to one embodiment, at least one of the wings comprises a second actuator adapted to modify the length of the portion of the second cable stretched between said wing and the connecting device. B13338 - RT 2014 001
    [0004] According to one embodiment, each wing is connected to at least two other wings by at least two first cables. According to one embodiment, each wing comprises first actuators adapted to independently modify the lengths of the portions of said at least two first cables 10 stretched between said wing and the other two wings. According to one embodiment, the device comprises at least two pairs of wings, the two wings of each pair being interconnected by one of the first cables, each wing of each pair being connected to at least one of the wings the other pair by another of the first cables. According to one embodiment, the wingspan of each wing is between 5 m and 50 m. According to one embodiment, at least one of the wings comprises an upper surface connected to a lower surface by a leading edge, a trailing edge and first and second lateral edges, the wing cord increasing and then decreasing from first side edge to the second side edge. According to one embodiment, for each wing, at least one of the first cables enters the wing by the lateral edge 25 of the innermost wing of the airborne device when the airborne device is put to the wind. According to one embodiment, for each wing, the second cable enters the wing by the underside of the wing. One embodiment also provides a system for producing electrical energy, comprising an airborne device as defined above and an electric generator connected to the third cable of the airborne device. One embodiment also provides a transport system, comprising an airborne device as defined previously and a vehicle, in particular a boat, connected to the third cable of the airborne device. BRIEF DESCRIPTION OF THE DRAWINGS These and other features and advantages will be set forth in detail in the following description of particular embodiments in a non-limiting manner with reference to the accompanying figures in which: FIG. perspective, partial and schematic, of an embodiment of an airborne device; Figure 2 is a partial schematic perspective view of an electricity generating system including the airborne device shown in Figure 1; Figure 3 is a partial schematic perspective view of a transport system including the airborne device shown in Figure 1; Figure 4 is a top view, partial and schematic, of an embodiment of a wing of the airborne device shown in Figure 1; Figures 5 and 6 are respectively a perspective view and a front view, partial and schematic, of another embodiment of a wing of the airborne device shown in Figure 1; Figure 7 is a top, partial and schematic view of another embodiment of a wing of the airborne device shown in Figure 1; and FIGS. 8 and 9 are sectional, partial and schematic views of embodiments of a cable of the airborne device shown in FIG. 1. Detailed Description For the sake of clarity, the same elements have been designated by the same references to the different figures and, moreover, the various figures are not drawn to scale. In the remainder of the description, unless otherwise indicated, the terms "substantially", "about", "approximately" and "of the order of" 35 mean "to within 10%".
    [0005] B13338 - RT 2014 001 Figure 1 shows an embodiment of an airborne device 10. The airborne device 10 comprises at least three wings, for example from three to eight wings 12. Preferably, the airborne device comprises at least four wings 12. Advantageously, the airborne device 10 comprises an even number of wings 12. The wings 12 are interconnected by flexible cables. A flexible cable is a cable that, under the action of an external force, can deform, including bending, without breaking or tearing. There is no rigid frame connecting the wings 12 between them. For example, in the case where the airborne device 10 comprises four wings 12, each wing 12 is connected to each adjacent wing by a flexible cable 14 and is connected to the opposite wing by a flexible cable 16. In addition, each wing 12 is connected to a connecting device 18 by a flexible cable 20. The connecting device 18 is connected to an anchoring system, not shown, by a flexible cable 22. According to the intended application, the system of Anchorage may be on the ground, on a buoy, or on a ship. According to one embodiment, the connecting device 18 comprises a first part 24 to which the cables 20 are fixed and connected to a second part 26 to which the cable 22 is fixed. The first part 24 is adapted to pivot relative to the second part 26 around the axis of the cable 22. The connecting device 18 may correspond to a swivel.
    [0006] Each wing 12 corresponds to a supporting wing comprising a lower surface 30 connected to an upper surface 32 by a leading edge 34, a trailing edge 36, an outer lateral edge 38 facing outwardly of the device 10, and a lateral edge 40 inside, oriented towards the inside of the device 10. Each wing 12 may correspond to a profiled wing, for example according to a NACA profile. According to one embodiment, for each wing 12, or the cables 14 and 16 are connected substantially to the same point of the inner side edge 40. According to one embodiment, for each wing 12, the cable 20 is connected to the wing 12 at a point of B13338 - RT 2014 001 6 at a distance from the leading edge 34, the trailing edge, the outer lateral edge 38 and the inner lateral edge 40. As a variant, the cable 20 can be connected to the inner side edge 40.
    [0007] The operation of the airborne device 10 is as follows. Under the action of wind, shown schematically by the arrow 42, the wings 12 move under the effect of lift forces. The centrifugal forces tend to spread the wings 12 radially, so that the cables 14 and 16 are stretched continuously. A rotation movement of the wings 12 is then obtained, which is represented in FIG. 1 by the arrow 44. The lift forces exerted on each wing 12 result in a traction of the cables 20, and therefore by a traction on the cable 22 This results in a conversion of the kinetic energy of the wind 42 into mechanical traction energy of the cable 22. Preferably, the cable 20 is connected to the intrados 30 so that the longitudinal axis of the wing 12 is aligned with the cable 16. The wings 12 of the airborne device 10 turn in the manner of the blades of a wind turbine on the ground. The present embodiment is based on the fact that, for a conventional wind turbine on the ground, the parts of the blades, which in operation are the most effective for capturing the kinetic energy of the wind, are located near the free ends of the blades, there where the driving torque due to the wind is the highest. The wings 12 are therefore located in the useful areas where the driving torque due to the wind 42 is the largest and the cables 14, 16, 20 are located in the areas where the wind-driven driving torque 42 is reduced. Therefore, the surface described by the wings 12 during their movement can be important while the airborne device has a simple structure and a reduced mass. Preferably, the maximum operating diameter of the airborne device 10 is between 20 m and 200 m, preferably between 100 m and 150 m. The weight of the airborne device 10, not counting the cable 22, can be between 20 kg and 20 B13338 - RT 2014 001 7 tons. The rotational speed in operation of the wings can be between 1.5 and 200 revolutions per minute. FIG. 2 shows an embodiment of a power generation system 45 in which the cable 22 of the airborne device 10 is connected to an electric generator 46. As a variant, each wing 12 may comprise an electric generator comprising a turbine driven during the movement of the wing 12. The electrical energy produced can then be transmitted to the ground by the cables 20 and 22.
    [0008] Figure 3 shows an embodiment of a transport system 47 in which the cable 22 of the airborne device 10 is connected to a vehicle 48, in this example a ship. The airborne device 10 is then used as traction means of the vehicle 48.
    [0009] FIG. 4 is a schematic view of an embodiment of one of the wings 12 of the airborne device 10 shown in FIG. 1. Each wing 12 of the airborne device 10 may have substantially the structure shown in FIG. 4. The wing 12 form a partially hollow chamber and is shown schematically in Figure 4 several elements arranged in the internal volume of the wing 12. The wing 12 is, for example, made of composite materials. The cables 14, 16, 20 may be made of synthetic fibers, in particular the product marketed under the name Kevlar.
    [0010] In the remainder of the description, the longitudinal axis D of the wing is called an axis perpendicular to the two most distant parallel planes, one of which is tangential to the outer lateral edge 38 and the other tangential to the inner lateral edge 40. The wingspan E of the wing 12 is the distance between these planes.
    [0011] The span E is between 5 m and 50 m, preferably between 25 m and 35 m. The wing string 12, measured in a plane perpendicular to the longitudinal axis D, is not constant along the axis D. The rope increases from the inner side edge 40 to a maximum rope and then decreases to the outer side edge 38. The maximum chord is between 0.25 m and 5 m, preferably between 1.25 m and 3.5 m. The maximum cord is located substantially between 10% and 45%, preferably between 15% and 30%, of the span from the inner side edge 40. At 50% of the span from the inner side edge 40, the ratio between the rope and the maximum rope is between 60% and 100%, preferably between 70% and 90%. The maximum thickness between the upper surface and the lower surface is between 7% and 25% of the value of the rope at this location, preferably between 8% and 15% of the value of the rope at this location. Each cable 14, 16, 20 has a mean diameter of between 5 mm and 10 cm. The leading edge arrow, FA, is the angle between the axis D and a plane tangent to the leading edge 34. The arrow is positive when the angle, oriented from the axis D to the tangent plane, is counter-clockwise when looking at the upper surface of the wing and negative in the opposite case. According to one embodiment, the arrow of the leading edge FA varies along the axis D of the inner lateral edge 40 to the outer lateral edge 38. According to one embodiment, the arrow of the leading edge FA is successively, away from the inner side edge 40 along the axis D, negative and decreases in absolute value as one moves away from the inner side edge 40 along the axis D, vanishes and then is positive and increases to the outer side edge 38. According to one embodiment, at 20% of the span from the inner side edge 40, the leading edge arrow 34 is between -20 degrees and 5 degrees, and at 60% of the span from the inner side edge 40, the leading edge arrow 34 is between 0 degrees and 10 degrees. The trailing edge arrow, FF, is the angle between a plane tangent to the trailing edge and the axis D. According to one embodiment, the trailing edge arrow FF varies along the axis D of the edge. internal side 40 to the outer lateral edge 38. According to one embodiment, the arrow of the trailing edge FF is successively, away from the inner lateral edge 40 along the axis D, positive, zero, negative, zero and positive. According to one embodiment, at 20% of the span from the inner side edge 40, the arrow of the trailing edge FF is between 30 degrees and 0 degrees, and at 60% of the span. from the inner side edge 40, the trailing edge arrow FF is between -10 degrees and 10 degrees. The wing 12 may comprise twisting, i.e. the angle between the rope and a reference plane, or wedge angle, may vary along the axis D. The wing 12 comprises a control module 50, comprising for example a processor; Sensors 52, connected to the control module 50, for example a speed sensor, a wing position sensor, for example a GPS positioning system (acronym for Global Positioning System), gyroscopes, accelerometers, a Pitot tube, magnetometers and a barometer; Actuators 53, 54, 55, 56, each actuator 53, 54, 55, 56 being controlled by the control module 50 and being connected to one of the cables 14, 16, 20; at least one movable trailing edge flap, two movable flaps 57, 58 being shown in Figure 4; A remote communication module 59 connected to the control module 50; and a storage battery 60 for powering the control module 50, actuators 53, 54, 55, 56 and aileron actuators 57, 58. Alternatively, the battery 60 may be replaced. by an electric generator. As a variant, the electrical energy for supplying the control module 50, the motors 54 for actuating the cables 14, 16, 20 and the actuating motors for the fins 57, 58 can be fed to each wing 30. via the cables 20 and 22. Each actuator 53, 54, 55, 56 is adapted to modify the length of the stretched portion of the cable 14, 16 or 20 outside the wing 12. By way of example, each actuator 53, 54, 55, 56 is adapted to unroll or wind the cable 14, 16, 35 to which it is connected. The length of the portion of each cable B13338 - RT 2014 001 14, 16 extending between two flanges 12 and the length of the portion of each cable 20 extending between a flange 12 and the connecting device 18 can thus be changed. The control module 50 of each wing 12 is adapted to exchange signals remotely, via the communication module 59, with the control modules 50 of the other wings 12, for example by a method of remote transmission of data of the high frequency type. The control module 50 of each wing 12 may furthermore be adapted to exchange signals remotely, via the communication module 59, with a station on the ground. The control of the incidence of each wing 12 is achieved by the control mode 50 by modifying the inclination of the fins 57, 58 and modifying the length of the portions of the cables 14, 16 and 20 stretched in operation between the wings 12 or between the wings 12 and the connecting device 18. According to one embodiment, the incidence of each wing 12 can be modified cyclically during a revolution of the wing 12. According to another embodiment, in the case where the airborne device 10 is connected to an electric generator 46, the operation of the electric generator 46 may comprise an alternation of first and second phases. In each first phase, the impacts of the wings 12 are controlled to increase the traction forces exerted by the airborne device 10, 25 the airborne device 10 away from the electric generator 46. In each second phase, the incidences of the wings 12 are controlled to reduce the tensile forces exerted by the airborne device 10 on the cable 22 so as to bring the airborne device 10 of the generator 46 in spending a minimum of energy. In addition, when the airborne device 10 is raised from the ground to an operating altitude, the tensioned portions of the cables 14, 16, 20 between the flanges 12 or between the flanges 12 and the connecting device 18 may initially be reduced. to reduce the size of the airborne device 10.
    [0012] B13338 - RT 2014 001 11 Figures 5 and 6 show another embodiment of the wing 12 wherein the wing 12 further comprises two fins 62 which may each comprise a movable flap 64. The first drift 62 is projects projecting from the extrados 32 and the second drift 62 projects from the underside 30. The actuation of the movable flap 64 of each fin 62 is controlled by the control module 50. The actuation of the movable flap 64 allows in particular controlling the lateral position of the airborne device 10 relative to the wind 42.
    [0013] Each wing 12 may be provided with a propulsion system. Before launching the airborne device 10, the wings 12 may be arranged on a support and the lengths of the cables 14, 16 and 20 may be reduced. The propulsion system of each wing 12 can be actuated. This causes the tensioning of the cables 14, 16 and the rotation of the wings 12. Under the action of the lift forces, the airborne device 10 rises in the air. The lengths of the cables 14, 16, 20 can be progressively increased as the altitude of the airborne device 10 increases until the airborne device 10 reaches the desired altitude. As soon as the airborne device 10 is exposed to a wind sufficient to maintain the altitude and rotation of the airborne device 10, the propulsion systems of the wings 12 can be deactivated. The propulsion systems can, in addition, be operated in flight, while the airborne device 10 is at its operating altitude, when the power of the wind 42 is not sufficient to maintain the airborne device 10 at this altitude. FIG. 7 shows an embodiment of the wing 12 in which the propulsion system of the wing comprises a motorized propeller 70 which projects from the leading edge 34 of the wing towards the front of the wing according to the direction of rotation of the wing 12 in operation. The motorized propeller 70 can be controlled by the control module 50 or can be remotely controlled from a ground station. An advantage of the use of a motorized propeller B13338 - RT 2014 001 12 is that it allows, in addition, to move the center of gravity of the wing 12 forward in the direction of rotation of the wing 12 in operation. This may be advantageous for improving the stability of the wing. According to one embodiment, the propeller 70 can be removable and folded, at least in part, in the wing 12 when it is not used. Alternatively, the propulsion system may comprise a jet engine, including a rocket engine or a propulsion system with compressed air.
    [0014] Each wing 12 may further comprise a landing gear, not shown, which allows the movement of the wing 12 to the ground. The landing gear can be removable so as to be folded, at least in part, into the wing 12 when not in use.
    [0015] FIG. 8 shows an embodiment in which each cable 14, 16, 20 or 22 or at least one of the cables 14, 16, 20 or 22 has a profiled section including a leading edge 72 and a trailing edge 74 thinned. This allows in particular to reduce the drag of the cable.
    [0016] FIG. 9 shows an embodiment in which each cable 14, 16, 20 or 22 or at least one of the cables 14, 16 or 30 further comprises a core 76 contained in a profiled envelope 78. The core 76 may be in a first material and the envelope 78 may be in a second material, the density of the first material being greater than the density of the second material. This allows to bring the center of gravity of the cable towards the leading edge and thus improve the aerodynamic stability of the cable. Various embodiments with various variants have been described above. It is noted that one skilled in the art can combine various elements of these various embodiments and variants without being creative. In particular, the airborne device 10 can both comprise a propulsion system, such as the propeller 70 shown in FIG. 7, the cables 14, 16, 20 shaped as shown in FIGS. 8 and 8. 9 and a landing gear.
    权利要求:
    Claims (14)
    [0001]
    REVENDICATIONS1. Airborne device (10) comprising at least three supporting wings (12) and a connecting device (18), the wings being interconnected by first flexible cables (14, 16), each wing being further connected to the device link (18) by a second flexible cable (20), the connecting device being connected to a third flexible cable (22) to be connected to a base (46, 48), the first, second and third cables being tensioned when the airborne device is put to the wind.
    [0002]
    2. Airborne device according to claim 1, not comprising rigid reinforcement connecting the wings (12) to each other.
    [0003]
    An airborne device according to claim 1, wherein the connecting device (18) comprises a first portion (24) connected to a second portion (26), the second cables (20) being attached to the first portion and the third cable (22) being fixed to the second part, the first part being adapted to pivot relative to the second part.
    [0004]
    4. Airborne device according to any one of claims 1 to 3, wherein at least one of the wings (12) comprises at least a first actuator (53, 54) adapted to change the length of the portion of one first cables (16) stretched between said wing and one of the other wings.
    [0005]
    5. An airborne device according to any one of claims 1 to 4, wherein at least one of the wings (12) comprises a second actuator (56) adapted to change the length of the portion of the second cable (20) stretched between said wing and the connecting device (18).
    [0006]
    6. An airborne device according to any one of claims 1 to 5, wherein each wing (12) is connected to at least two other wings by at least two first cables (14, 16).
    [0007]
    7. An airborne device according to claims 4 and 6, wherein each wing (12) comprises first actuators (53, 54) adapted to independently modify the lengths of the portions of said at least two first cables stretched between said wing. and the other two wings.
    [0008]
    8. Airborne device according to any one of claims 1 to 7, comprising at least two pairs of wings (12), the two wings of each pair being interconnected by one of the first cables (16), each wing of each pair being connected to at least one of the wings of the other pair by another of the first cables (14). 10
    [0009]
    9. Airborne device according to any one of claims 1 to 8, wherein the span of each wing (12) is between 5 m and 50 m.
    [0010]
    10. Airborne device according to any one of claims 1 to 9, wherein at least one of the wings (12) comprises an upper surface (32) connected to a lower surface (30) by a leading edge (34). , a trailing edge (36) and first and second side edges (38, 40), the wing string increasing and decreasing from the first side edge to the second side edge.
    [0011]
    Apparatus according to claim 10, wherein for each wing (12) at least one of the first cables (14, 16) enters the wing by the side edge (40) of the wing (12). ) the most inside the airborne device when the airborne device is put in the wind.
    [0012]
    12. Device according to claim 10 or 11, wherein, for each wing (12), the second cable (20) enters the wing (12) by the intrados (30) of the wing.
    [0013]
    An electric power generating system (45) comprising an airborne device (10) as claimed in any one of claims 1 to 12 and an electric generator (46) connected to the third cable (22) of the airborne device.
    [0014]
    14. System (47) for transport, comprising an airborne device (10) according to any one of claims 1 to 12 and a vehicle (48), including a boat, connected to the third cable (22) of the airborne device.
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    同族专利:
    公开号 | 公开日
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    US20170210467A1|2017-07-27|
    US10570886B2|2020-02-25|
    WO2016012695A1|2016-01-28|
    FR3023876B1|2019-05-03|
    CN106715897A|2017-05-24|
    EP3172435A1|2017-05-31|
    引用文献:
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    法律状态:
    2015-07-17| PLFP| Fee payment|Year of fee payment: 2 |
    2016-01-22| PLSC| Publication of the preliminary search report|Effective date: 20160122 |
    2016-07-27| PLFP| Fee payment|Year of fee payment: 3 |
    2017-07-28| PLFP| Fee payment|Year of fee payment: 4 |
    2018-07-30| PLFP| Fee payment|Year of fee payment: 5 |
    2019-07-30| PLFP| Fee payment|Year of fee payment: 6 |
    2020-07-30| PLFP| Fee payment|Year of fee payment: 7 |
    2021-07-29| PLFP| Fee payment|Year of fee payment: 8 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1457001A|FR3023876B1|2014-07-21|2014-07-21|AIRBORNE DEVICE|
    FR1457001|2014-07-21|FR1457001A| FR3023876B1|2014-07-21|2014-07-21|AIRBORNE DEVICE|
    CN201580050959.9A| CN106715897B|2014-07-21|2015-07-15|Aerospace equipment|
    PCT/FR2015/051936| WO2016012695A1|2014-07-21|2015-07-15|Airborne device|
    US15/326,705| US10570886B2|2014-07-21|2015-07-15|Airborne device|
    EP15759845.9A| EP3172435A1|2014-07-21|2015-07-15|Airborne device|
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