AIRCRAFT TAKEOFF AND LANDING PLATFORM FOR ELECTRICAL POWER PRODUCTION

Abstract

The invention provides a takeoff and landing platform (28) for an aircraft (12) for the production of electrical energy by means of a generator (24) and comprising: - a fixed support (30), - a receiving structure (32) for the aircraft (12) which is designed to receive the aircraft (12) and which is connected to the fixed support (30). The receiving structure (32) is pivotally mounted relative to the fixed support (30) by means of a swiveling plate (38) so as to allow the positioning of the receiving structure (32) according to the wind direction. The receiving structure (32) for the aircraft (12) has an air-permeable net (34) which is stretched between arms (36) belonging to the receiving structure (32). Figure for the abstract: 2

Description

Title of the invention: AIRCRAFT TAKEOFF AND LANDING PLATFORM FOR PRODUCTION ELECTRICAL ENERGY Technical field of the invention

[0001] The present invention relates to a system for producing electrical energy using an aircraft. More particularly, the invention relates to an aircraft takeoff and landing platform. Technical background

[0002] It is known to construct an electrical power generation system using an aircraft, also called a "flying wind turbine," which is connected to a generator mounted on the ground by means of at least one suspension cable or strut. This type of system makes it possible to access strong and abundant winds blowing at high altitudes.

[0003] The difficulty for this type of system is to be able to easily take off and land the aircraft, possibly autonomously, without the need to design a complex and expensive structure.

[0004] The invention proposes an aircraft takeoff and landing platform incorporating an aircraft reception structure adapted for both aircraft takeoff and landing and having a small footprint.

[0005] This system will be compact and easy to maintain so that it can be deployed in areas with limited infrastructure. Summary of the invention

[0006] The invention proposes an aircraft takeoff and landing platform for the production of electrical energy by means of a generator and comprising: - a fixed support, - an aircraft receiving structure which is designed to receive the aircraft and which is connected to the fixed support; characterized in that the receiving structure is mounted pivotally relative to the fixed support by means of an adjustable plate so as to allow the positioning of the receiving structure according to the wind direction, and in that the aircraft receiving structure includes a flexible, air-permeable device that is stretched between branches belonging to the receiving structure.

[0007] Thus, the invention proposes a takeoff and landing platform for an aircraft without means of propulsion, capable of taking off solely by the force of the wind. The takeoff and landing platform according to the invention allows the aircraft to be brought into an angle of attack that generates sufficient lift for takeoff in order to produce electrical energy through the traction exerted by a cable on a generator installed on the ground. The aircraft is able to land while the generator becomes a drive unit and rewinds the cable to ensure the aircraft has a sufficient descent speed to fly back to the platform.

[0008] According to other characteristics of the takeoff and landing platform:

[0009] - the swiveling plate is mobile in rotation around a main axis of rotation sen vertically;

[0010] - the platform includes a tilting base which supports the receiving structure and which is mounted pivoting relative to the swiveling plate around a pivot axis;

[0011] - the pivot axis is substantially transverse with respect to the principal axis of rotation ;

[0012] - the tilting base includes a passage provided for guiding a suspension cable designed to be connected to the aircraft towards the generator;

[0013] - the tilting base comprises: — a main body comprising the passage, and — two support arms which extend from the main body towards the swiveling plate and which are connected to the swiveling plate by the pivot axis;

[0014] - the main body of the tilting base has a rectangular shape, and each arm the receiving structure has one end which is fixed to a corner of the main body;

[0015] - the flexible device comprises at least two elastic elements which are arranged on either side of a vertical median plane of the receiving structure so as to be able to cushion the landing of the aircraft in the receiving structure;

[0016] - the two elastic elements are stretched between the two arms of a frame lateral, for example in the shape of a V, a C, or a U;

[0017] - the receiving structure comprises a main frame fixed to the base in tiltable and two lateral arms which extend on the opposite side of the tiltable base and which together form a support surface intended to support the aircraft wings in a rest position of the aircraft.

[0018] The invention also proposes an electrical energy production system comprising - an aircraft, - a generator designed to produce electrical energy from the forces applied by the wind to the aircraft via a cable, - at least one suspension line provided to connect the aircraft to the generator; characterized in that it comprises a take-off and landing platform according to one of the previous characteristics. Brief description of the figures

[0019] Other features and advantages of the invention will become apparent upon reading the detailed description that follows, for an understanding of which reference should be made to the accompanying drawings in which:

[0020] [Fig-1] - [Fig.1] is a schematic perspective view of a system of electrical energy production equipped with an aircraft takeoff and landing platform comprising an aircraft reception structure according to a first embodiment of the invention, in a rest position of the aircraft, the aircraft being pitched up to be ready for takeoff;

[0021] [Fig.2] - [Fig.2] is a perspective view of the energy production system electric of the [Fig.l], in a takeoff position of the aircraft where the aircraft has taken off and exerts a pulling force on the cable which connects it to the takeoff platform in order to drive a generator placed on the ground;

[0022] [Fig.3] - [Fig.3] is a perspective view of the energy production system electrical [Fig.1], in a position just before the aircraft lands;

[0023] [Fig.4] - [Fig.4] is a perspective view similar to that of [Fig.1] which illustrates a second embodiment of the system according to the invention when the aircraft is in a rest position;

[0024] [Fig.5] - [Fig.5] is a rear view which schematically represents the structure of reception of the system of the [Fig.4]. Detailed description of the invention

[0025] For the description of the invention and the understanding of the claims, the vertical, longitudinal and transverse orientations according to the V, L, T frame indicated in the figures, whose longitudinal L and transverse T axes extend in a horizontal plane, will be adopted without limitation and without limiting reference to terrestrial gravity.

[0026] In the following description, identical, similar or analogous elements shall be designated by the same alphanumeric references. First method of implementation

[0027] Figures 1, 2 and 3 represent an electrical power generation system 10 comprising: - an aircraft 12, - a generator 24 designed to produce electrical energy from the forces applied by the wind on the aircraft 12, - two suspension lines 26 provided for connecting the aircraft 12 to the generator 24, and - a takeoff and landing platform 28.

[0028] The aircraft 12 comprises a main wing 14 and a secondary wing 16, serving as stabilizer, substantially planar, the main wing 14 having a larger wingspan than the secondary wing 16. The main wing 14 and the secondary wing 16 are each arranged in a plane parallel to each other and they are connected to each other by a rigid structure 18.

[0029] The rigid structure 18 comprises one or two bars arranged parallel to each other and each connected at one end to the main wing 14 and at one end to the secondary wing 16 of the aircraft 12.

[0030] As shown in the illustrative figures, the wings 14, 16 are arranged in the same plane. In addition, two front ailerons 20 are arranged on either side of the main wing 14 and two rear ailerons 22 are arranged on either side of the secondary wing 16 of the aircraft 12.

[0031] Preferably, the wings 14, 16 of the aircraft 12 are made of a low-cost rigid material with easy maintenance and deployment.

[0032] Advantageously the aircraft 12 is entirely made of rigid materials.

[0033] The rigid materials used for the construction of the aircraft are, for example, balsa, foam, or composite materials.

[0034] Each suspension line 26 is in the form of a cable connected at one end to the rigid structure 18 of the aircraft 12 and connected at the other end to a main cable providing the link with the generator 24 via the platform, between a coiled state and a deployed state of the suspension line 26. During the tethered flight phase of the aircraft 12, the suspension lines 26 are in a deployed and tensioned state which allows the generator 24 to produce electrical energy.

[0035] According to an example of an embodiment of the invention shown in the figures, the system 10 is equipped with two suspension lines 26 to pilot the aircraft 12 in space during the takeoff, flight and landing phases.

[0036] According to another embodiment of the invention not shown, the system 10 is equipped with a single suspension line 26. In this case, the piloting of the aircraft 12 in space is carried out by means of an external control element ensuring electronic piloting of the aircraft 12, for example by controlling the position of its ailerons 20, 22.

[0037] The take-off and landing platform 28 includes a fixed support 30 and a receiving structure 32 for the aircraft 12 which is intended to receive the aircraft 12 and which is connected to the fixed support 30.

[0038] As illustrated, the fixed support 30 is installed on a flat surface which can also accommodate the generator 24. It is a pylon (aluminum lattice) or a vertical pole whose height is sufficient to raise the aircraft 12 above the ground surface.

[0039] According to the first embodiment shown in Figures 1 to 3, the receiving structure 32 of the aircraft 12 comprises a flexible device 33 in the form of a net 34 permeable to air and four branches 36 provided for tensioning the net 34.

[0040] According to an example of an embodiment not shown of the receiving structure 32, it includes a frame on which the edge of the net 34 is hung and intended to tension the net 34.

[0041] Advantageously, the net 34 is made of a woven or non-woven textile material, having openwork meshes for the passage of air through the net 34.

[0042] Advantageously, the receiving structure 32 includes at least one elastic element not shown intended to cushion the landing of the aircraft 12 in the receiving structure 32.

[0043] According to a first embodiment of the receiving structure 32, each elastic element is arranged so as to elastically connect a branch 36 with the net 34 of the receiving structure 32. In this case, the elastic element is for example a fastener made of an elastic material such as rubber.

[0044] According to a second embodiment of the receiving structure 32, each branch 36 of the receiving structure 32 has elastic properties so as to be sufficiently flexible to be able to flex during the landing of the aircraft 12 in the receiving structure 32.

[0045] The receiving structure 32 is pivotally mounted about a vertical axis V and a transverse axis T, corresponding to a principal axis A1 and a transverse axis A2, relative to the fixed support 30, so as to allow the receiving structure 32 to be positioned according to the wind direction and thus enable the takeoff or landing of the aircraft 12. The pivoting of the receiving structure 32 about the axes A1 and A2 also allows for a neutral state if the aircraft 12 needs to remain on the ground, for example in strong winds. In this case, the receiving structure 32 keeps the aircraft 12 horizontal so as to minimize its lift. The receiving structure 32 is generally oriented like a weather vane, that is, it follows the wind direction Fv while being free to rotate about the principal axis A1

[0046] More specifically, the pivoting of the receiving structure 32 is ensured by a swiveling plate 38 connected to the fixed support 30 and rotatable about the principal axis Al of rotation, which is substantially vertical. The principal axis Al can be slightly inclined with respect to the vertical, for example, up to an angle of 10 or 15 degrees. The swiveling plate 38 comprises a lower section 40 connected to the fixed support 30, and an upper section 42 connected to the tilting base 46 via a pivoting element 44. The swiveling plate 38 has a substantially trapezoidal shape, having a rounded side forming the upper section 42. The swiveling plate 38 is arranged on the fixed support 30 so as to be inclined at a certain angle with respect to the vertical axis to prevent incorrect positioning of the aircraft 12 relative to the wind.

[0047] The tilting base 46, which can be motorized, supports the receiving structure 32 and is mounted pivoting relative to the swiveling plate 38 around a pivot axis A2 substantially transverse to the main axis Al of rotation. The pivot axis A2 can be slightly inclined relative to a transverse direction T, for example up to an angle of 10 or 15 degrees with respect to the transverse direction T.

[0048] The tilting base 46 comprises: - a main body 48 including a passage 50 provided for guiding the suspension cables 26, - two support arms 52 which extend from the main body 48 to the swiveling plate 38 and which are connected to the swiveling plate 38 by the pivot axis A2.

[0049] The tilting base 46 has a limited pivoting range with respect to the pivot axis A2 so as to block the rotation of the tilting base to maintain the aircraft's incidence at an optimal angle with respect to the wind direction.

[0050] According to an embodiment of the invention illustrated in the figures, the main body 48 of the tilting base 46 has a rectangular shape. The support arms 52 are parallel to each other and are substantially perpendicular to the main body 48 of the tilting base 46. In this case, each arm 36 of the receiving structure 32 has an end that is fixed to a corner of the main body 48 of the tilting base 46, and the net 34 is stretched between each pair of arms 36.

[0051] Advantageously, a wind vane 53, here in the form of a longitudinal plate connected to the steerable plate 38, makes it possible to keep the steerable plate 38 and the receiving structure 32 permanently aligned with the wind axis, even during the flight of the aircraft 12.

[0052] As illustrated in [Fig. 1], in the resting position of aircraft 12 in the receiving structure 32 of the takeoff and landing platform 28, aircraft 12 is resting in the net 34 and the suspension lines 26 are in a coiled state. Aircraft 12 is here in a nose-up position to be ready for takeoff, facing the wind direction Fv.

[0053] In [Fig. 2], during the takeoff phase of aircraft 12 from the reception structure 32 of the takeoff and landing platform 28, the reception structure 32 is oriented by means of the steerable plate 38 and the tilting base 46 so as to position aircraft 12 facing into the wind and initiate takeoff. During this phase, the net 34 is taut and the suspension lines 26 are in an unstretched and tensioned state.

[0054] To reach the flight phase of aircraft 12, aircraft 12 is guided by the suspension lines 26 so as to reach a high altitude. Advantageously, the ascent of aircraft 12 is carried out by forming figure-eights.

[0055] In [Fig. 3], during the landing phase of aircraft 12 towards the reception structure 32 of the takeoff and landing platform 28, the reception structure 32 is oriented by means of the steerable plate 38 and the tiltable base 46 so as to cause the aircraft 12 to land in the receiving structure 32. During this phase, the suspension lines 26 are in an unwound state and they are tensioned so as to guide the aircraft 12 until it lands. Second embodiment

[0056] A second embodiment of the electrical power generation system 10 according to the invention is now described, with reference to Figures 4 and 5. The system 10 is similar to that shown in Figures 1 to 3 and differs from it primarily in its receiving structure 32.

[0057] For the description of this second embodiment of the invention, emphasis will be placed on the differences and the other elements which make up the system, in particular the aircraft 12 and the fixed support 30, will not be described again.

[0058] According to this second embodiment, the receiving structure 32 uses stretched elastic elements 54 in place of the net 34. More specifically, the elastic device 33 equipping the receiving structure 32 here comprises two bands 54, or cords, of elastic material which are fixed at each of their ends to the free ends of two lateral frames 56.

[0059] Advantageously, each lateral reinforcement 56 here has the shape of a V, each elastic element 54 being stretched between the two arms 36 of the V. According to an alternative embodiment (not shown), each lateral reinforcement 56 could have the shape of a C or a U compatible with the takeoff and landing of the aircraft 12.

[0060] The aircraft 12 rests on these lateral frames 56.

[0061] The two elastic elements 54 are thus arranged on either side of a vertical median plane of the receiving structure 32, which allows the elastic device 33 to cushion the landing of the aircraft 12 in the receiving structure 32. Thanks to their V-shape, the lateral reinforcements 56 allow the elastic element 54 to be tensioned, leaving a clearance 59 between the two arms 36 for the elastic deformation of the elastic element 54 when the aircraft 12 lands in the receiving structure 32. Each elastic element 54 constitutes a flexible stop so that the aircraft 12 does not strike the rigid reinforcement during the docking phase.

[0062] The receiving structure 32 here comprises a main frame 58 fixed on the tilting base 46 which extends on the sides by two lateral arms 60. The two lateral arms 60 extend longitudinally towards the rear of the aircraft 12, on the side opposite the tilting base 46. These lateral arms 60 together form a support surface 62 intended to support each part of the main wing 14 of the aircraft 12, when it occupies its rest position.

[0063] LEGEND: 10: system aircraft main wing, secondary wing, rigid structure, front wing, rear wing, generator, suspension line fixed support takeoff and landing platform receiving structure flexible device net branch swiveling plate lower section upper section pivoting element tilting base main body passage support arm, weather vane, elastic element, lateral reinforcement, main reinforcement, lateral arm clearance, support surface : main axis (vertical V) : pivot axis (transverse T) Fv: wind direction

Claims

Demands

1. Take-off and landing platform (28) of an aircraft (12) for the production of electrical energy by means of a generator (24) and comprising: - a fixed support (30), - a receiving structure (32) of the aircraft (12) which is intended to receive the aircraft (12) and which is connected to the fixed support (30); characterized in that the receiving structure (32) is mounted pivotally relative to the fixed support (30) by means of a steerable plate (38) so as to allow the positioning of the receiving structure (32) according to the wind direction, and in that the receiving structure (32) of the aircraft (12) has a flexible device (33) which is stretched between arms (36) belonging to the receiving structure (32).

2. Take-off and landing platform (28) according to claim 1, wherein the flexible device (33) is air-permeable.

3. Take-off and landing platform (28) according to claim 1 or 2, characterized in that the steerable platform (38) is mobile in rotation about a principal axis (Al) of rotation substantially vertical.

4. Take-off and landing platform (28) according to any one of the preceding claims, characterized in that it comprises a tiltable base (46) which carries the receiving structure (32) and which is pivotally mounted relative to the steerable plate (38) around a pivot axis (A2).

5. Take-off and landing platform (28) according to any one of the preceding claims in combination with claim 4, characterized in that the tiltable base (46) has a passage (50) provided for guiding a suspension line (26) intended to be connected to the aircraft (12) towards the generator (24).

6. Take-off and landing platform (28) according to the preceding claim, characterized in that the tilting base (46) comprises: - a main body including the passage (50), and - two support arms which extend from the main body towards the steerable plate (38) and which are connected to the steerable plate (38) by the pivot axis (A2).

7. Take-off and landing platform (28) according to any one of the preceding claims taken in combination with claim 7 dication 4, characterized in that the main body (48) of the tilting base (46) has a rectangular shape, and in that each branch (36) of the receiving structure (32) has an end which is fixed to a corner of the main body (48).

8. Take-off and landing platform (28) according to any one of the preceding claims, characterized in that the flexible device (33) comprises at least two elastic elements (54) which are arranged on either side of a vertical median plane of the receiving structure (32) so as to be able to cushion the landing of the aircraft (12) in the receiving structure (32).

9. Take-off and landing platform (28) according to the preceding claim, characterized in that the two elastic elements (54) are stretched between the two arms (36) of a lateral frame (56), for example in the shape of a V, C, or U.

10. Take-off and landing platform (28) according to any one of the preceding claims taken in combination with claim 4, characterized in that the receiving structure (32) comprises a main frame (58) fixed on the tilting base (46) and two lateral arms (60) extending from the opposite side of the tilting base (46) and together forming a support surface (62) intended to support the wings of the aircraft (12) in a rest position of the aircraft (12).

11. Electrical power generation system (10) comprising: - an aircraft (12), - a generator (24) intended to produce electrical power from the forces applied by the wind on the aircraft (12) via a cable, - at least one suspension line (26) intended to connect the aircraft (12) to the generator (24); characterized in that it comprises a takeoff and landing platform (28) according to any one of the preceding claims.