Remote control system for Magnus effect aircraft.

Abstract

1. A remote control system for an aircraft, comprising: a Magnus effect aircraft with a cylinder (1) extending along a longitudinal axis (Y), the cylinder (1) being capable of rotating around the longitudinal axis (Y); a pair of rotatable elements (2) arranged at a distance from the aircraft; a drive means (3) arranged to drive a rotational movement of the pair of rotatable elements (2); and a connecting cable (4) arranged to connect the pair of rotatable elements (2) to the aircraft cylinder (1) such that the rotational movement of the pair of rotatable elements (2) driven by the drive means (3) is mechanically transmitted to the aircraft cylinder (1) to rotate the cylinder (1) around the longitudinal axis (Y).

Description

[Technical field]

[0001] The present invention relates to the technical field of systems for controlling Magnus effect aircraft.

[0002] The present invention relates in particular to - Producing electrical energy; -Carrying payloads, e.g. for communications or surveillance is applicable to. [Background technology]

[0003] The operation of Magnus effect aircraft is known to those skilled in the art and is described in particular in the book "Airborne Wind Energy: Advances in Technology Development and Research" by R. Schmehl et al., Springer, pages 280 and 304.

[0004] Systems for controlling Magnus effect aircraft known from the prior art include - a Magnus effect aircraft comprising a cylinder extending along a longitudinal axis, the cylinder being capable of rotating about the longitudinal axis; an electric motor arranged on the aircraft to rotate the cylinder about its longitudinal axis; a winch having a rotatable drum; a connecting cable arranged to connect the aircraft to the winch so that the lifting motion of the aircraft can be mechanically transmitted to the winch, the connecting cable being a power cable arranged to supply power to the motor; - a generator arranged to convert the rotation of the drum of the winch obtained by the mechanical transmission of the lifting motion of the aircraft into electrical energy; Equipped with.

[0005] Such prior art systems are not entirely satisfactory for overcoming the problem of autonomy insofar as the motors for driving the cylinders on board the aircraft must be powered by the connecting cables, which limits the choice of connecting cables, which must be electrically conductive. However, the couplings of the electrical connecting cables are subject to high stresses and are therefore at risk of deteriorating and breaking down. Summary of the Invention

[0006] The present invention aims to address all or some of the above mentioned shortcomings. To this end, the subject matter of the invention comprises: - a Magnus effect aircraft comprising a cylinder extending along a longitudinal axis, the cylinder being capable of rotating about the longitudinal axis; a rotatable element positioned away from the aircraft; and - drive means arranged to drive the rotational movement of the rotatable element; a connecting cable arranged to connect the rotatable element to the aircraft cylinder such that a rotational movement of the rotatable element driven by the drive means is mechanically transmitted to the aircraft cylinder to rotate the cylinder about its longitudinal axis; A remote control system for an aircraft comprising:

[0007] Such a system according to the invention therefore does not require an electric motor on board the aircraft to rotate the cylinder about its longitudinal axis (i.e. the pitch axis of the aircraft). In fact, according to the invention, the cylinder is rotated about its longitudinal axis by mechanical transfer via the connecting cable by a rotatable element, which makes it possible to reduce the energy conversion losses compared to the prior art. Unlike the prior art, the choice of the connecting cable is not limited and it does not have to be electrically conductive, which overcomes the problem of potential degradation of the coupling.

[0008] Thus, the rotational drive of the cylinder about its longitudinal axis can be offset, for example in a land or sea station where the rotatable element and the means for driving the rotatable element can be located, which allows for a lighter aircraft.

[0009] The system according to the invention may comprise one or more of the following features.

[0010] According to one feature of the invention, the connecting cable is wrapped around the aircraft cylinder such that a rotational movement of the rotatable element driven by the drive means is mechanically transmitted by friction on the connecting cable to the aircraft cylinder, causing the cylinder to rotate about its longitudinal axis.

[0011] One of the advantages offered is therefore that it allows a direct mechanical transfer between the connecting cable and the aircraft cylinder in order to control the aircraft along the pitch axis by controlling the rotational speed of the cylinder about its longitudinal axis.

[0012] According to one feature of the invention, the system comprises a transmission device arranged to mechanically cooperate with the connecting cable and the aircraft cylinder, such that a rotational movement of the rotatable element driven by the drive means is mechanically transmitted by the transmission device to the aircraft cylinder to rotate the cylinder about its longitudinal axis.

[0013] One of the advantages offered is therefore that it allows an indirect mechanical transfer (by means of a transmission device) between the connecting cable and the aircraft cylinder in order to control the aircraft along the pitch axis by controlling the rotational speed of the cylinder about its longitudinal axis.

[0014] According to one feature of the invention, the transmission device comprises an arrangement in which the mechanical transmission of the rotational motion of the rotatable element to the cylinder is interrupted, so that the cylinder can freely rotate about its longitudinal axis, the transmission device preferably comprising a freewheel or a clutch.

[0015] One of the advantages offered by this configuration is therefore the ability to rewind the connecting cable without transmitting power to the aircraft cylinder when the mechanical transmission is interrupted.

[0016] According to one feature of the invention, the aircraft in a lifting state is intended to be subjected to a wind and the system comprises control means arranged to control the drive means as a function of the wind.

[0017] Thus, one of the advantages offered is the ability to control the torque and rotational speed of the rotatable element.

[0018] According to one feature of the invention, the aircraft comprises guide means arranged to guide the connecting cable between two positions relative to the cylinder defining the maximum roll angle.

[0019] One advantage thus provided is that of facilitating piloting of the aircraft by controlling the roll angle of the aircraft. The guide means is arranged relative to the cylinder for maintaining movement of the connecting cable along an axis parallel to the longitudinal axis of the cylinder between two positions which define a maximum roll angle.

[0020] According to one feature of the invention, the cylinder has first and second longitudinal ends, and the system includes first and / or second attachment cables secured to the first and / or second longitudinal ends, respectively, of the cylinder and connected to first and / or second winches, respectively.

[0021] Thus, one of the advantages provided is the ability to control the aircraft along the roll axis by controlling the length of the first and / or second attachment cables between the aircraft and the first and / or second winches, respectively.

[0022] According to one aspect of the invention, the system comprises an anchoring zone located away from the aircraft, the connecting cable being fixed to the anchoring zone.

[0023] Thus, one of the advantages offered by the anchoring zone is the ability to control the torque applied to the cylinder independent of the balance between the aerodynamic forces and the sum of the tensions in each section of the connecting cable.

[0024] According to one aspect of the invention, the system comprises a pair of rotatable elements located remotely from the aircraft; - the drive means is arranged to drive the rotational movement of the pair of rotatable elements; the connecting cable is arranged to connect the pair of rotatable elements to the aircraft cylinder such that a rotational movement of the pair of rotatable elements driven by the drive means is mechanically transmitted to the aircraft cylinder to rotate the cylinder about its longitudinal axis.

[0025] Thus, one of the advantages offered by the pair of rotatable elements is to control the two directions of rotation of the aircraft cylinder around its longitudinal axis (pitch axis), thus avoiding crossing of the connecting cable. By controlling the length of the connecting cable between the aircraft and the rotatable elements, it is possible to generate a reciprocating lifting motion (forward and backward) of the aircraft. The pair of rotatable elements includes a first and a second rotatable element. The first and second rotatable elements may be independent in the sense that they may have different rotational speeds (winding, unwinding, stopping).

[0026] According to one aspect of the invention, a system includes: an additional pair of rotatable elements positioned away from the aircraft; and -Additional connection cables and Equipped with - the drive means is arranged to drive the rotational movement of the further pair of rotatable elements; the additional connecting cable is arranged to connect the additional pair of rotatable elements to the aircraft cylinder such that a rotational movement of the additional pair of rotatable elements driven by the drive means is mechanically transmitted to the aircraft cylinder to rotate the cylinder about its longitudinal axis.

[0027] One advantage offered is therefore the ability to transmit the desired power to the cylinder at any time, including when unwinding the connecting cable or the additional connecting cable.

[0028] According to one aspect of the present invention, the aircraft comprises first and second cylinders extending along first and second longitudinal axes, respectively, the first and second cylinders being capable of rotating about the first and second longitudinal axes, respectively; the connecting cable is arranged to connect the pair of rotatable elements to a first cylinder of the aircraft such that a rotational movement of the pair of rotatable elements driven by the drive means is mechanically transmitted to the first cylinder of the aircraft to rotate the first cylinder about the first longitudinal axis; the additional connecting cable is arranged to connect the additional pair of rotatable elements to the second cylinder of the aircraft such that a rotational movement of the additional pair of rotatable elements driven by the drive means is mechanically transmitted to the second cylinder of the aircraft to rotate the second cylinder about the second longitudinal axis.

[0029] Thus, one of the advantages offered is that the aircraft can be controlled along the yaw axis by introducing a difference in rotational speed between one pair of rotatable elements and an additional pair of rotatable elements. This results in a differential drag that generates a torque around the yaw axis of the aircraft. In this case, it is possible to eliminate the need for a tail device to stabilize the aircraft along the yaw axis. It is also possible to contemplate dynamic flight, which envisages maneuvering the aircraft around the yaw axis by making a figure-eight trajectory at a given altitude to go back and forth. The term "dynamic flight" is understood to mean a flight in which the aircraft is constantly moving and continuously adapts to the characteristics of the wind.

[0030] According to one aspect of the invention, a system includes: - two pairs of rotatable elements positioned away from the aircraft; -Two connection cables and and a first and second assembly each comprising: the aircraft comprises first and second cylinders extending along first and second longitudinal axes, respectively, the first and second cylinders being capable of rotating about the first and second longitudinal axes, respectively; - the drive means are arranged to drive the rotational movement of the rotatable elements of the first and second assemblies; each connecting cable of the first assembly is arranged to connect a pair of rotatable elements of the first assembly to a first cylinder of the aircraft such that a rotational movement of the rotatable elements of the first assembly driven by the drive means is mechanically transmitted to the first cylinder of the aircraft to rotate the first cylinder about the first longitudinal axis; each connecting cable of the second assembly is arranged to connect a pair of rotatable elements of the second assembly to a second cylinder of the aircraft such that a rotational movement of the rotatable elements of the second assembly driven by the drive means is mechanically transmitted to the second cylinder of the aircraft to rotate the second cylinder about the second longitudinal axis.

[0031] One of the advantages offered is therefore the ability to transmit the desired power to the corresponding cylinder at any time, including when unwinding one of the two connecting cables of the corresponding assembly.

[0032] According to one aspect of the invention, the aircraft in a lifting state has a yaw axis and is intended to receive a wind, the system comprising: a first branch connected to a first cylinder; a second branch connected to a second cylinder; and the first and second branches form a sweep angle adapted to stabilize the aircraft along the yaw axis as a function of the wind.

[0033] According to one feature of the invention, the rotatable element is the drum of a winch.

[0034] Therefore, one of the advantages offered by a winch is - the length of the connecting cable extending between the drum and the aircraft; -Drum rotation speed and The advantage of this is that it allows you to control both.

[0035] According to one feature of the invention, a connecting cable is arranged to connect the aircraft to the rotatable element such that the lifting motion of the aircraft can be mechanically transmitted to the rotatable element.

[0036] According to one aspect of the invention, the system comprises a converter arranged to convert the rotation of a rotatable element obtained by mechanical transmission of the lifting motion of the aircraft into energy.

[0037] One of the advantages offered is therefore the ability to recover the mechanical energy resulting from the lifting motion of the aircraft.

[0038] According to one aspect of the invention, an aircraft in a lifting condition has a yaw axis and is intended to receive a wind, the system comprising a tail device arranged to stabilise the aircraft along the yaw axis as a function of the wind. [Brief description of the drawings]

[0039] Further features and advantages will become apparent from the detailed disclosure of various embodiments of the invention, which disclosure includes examples and references to the accompanying drawings. [Figure 1] 1 is a schematic perspective view of a system according to the invention, showing in particular the presence of anchoring zones in which the connecting cables are fixed. [Diagram 2]FIG. 2 is a schematic perspective view of a system according to the invention, showing in particular the presence of a plurality of rotatable elements manufactured in the form of return pulleys. [Diagram 3] FIG. 1 is a schematic perspective view of a system according to the invention, showing in particular the presence of a linear motor which indirectly drives the rotary movement of a rotatable element. [Figure 4a] FIG. 1 is a schematic perspective view of a system according to the invention, showing in particular the presence of a transmission shaft (with stabilizer) which rotates a rotatable element, the transmission shaft being attached to the rotatable element against the action of elastic return means. [Figure 4b] FIG. 1 is a schematic perspective view of a system according to the invention, showing in particular a reeving connected to a rotatable element. [Diagram 5] 1 is a schematic perspective view of a system according to the invention, showing in particular a connecting cable forming a continuous loop; [Figure 6] 6 is a schematic side view of a first main embodiment of the system according to the invention, and the inset in Fig. 6 is an exploded view of an embodiment of the means for guiding the connecting cable, making it possible to guide the connecting cable between two positions relative to the cylinder so as to define a maximum roll angle. [Figure 7] FIG. 7 is a schematic perspective view of a first main embodiment of the system according to the invention shown in FIG. 6; [Figure 8] 1 is a schematic perspective view of an embodiment of an aircraft cylinder belonging to a system according to the invention; FIG. [Figure 9] FIG. 2 is a schematic perspective view of a second main embodiment of the system according to the invention, showing in particular the presence of two cylinders. [Figure 10] FIG. 2 is a schematic perspective view of a system according to the invention, showing in particular the sweep angle between two cylinders. [Figure 11] FIG. 2 is a partial schematic top view of a system according to the invention, showing in particular an elbow element connecting two cylinders. [Figure 12] FIG. 2 is a schematic perspective view of a third main embodiment of a system according to the invention; [Figure 13] FIG. 13 is a schematic perspective view of a fourth main embodiment of a system according to the invention; [Figure 14a] FIG. 1 is a schematic perspective view of a system according to the invention, showing in particular the presence of an attachment cable at one end of the cylinder. [Figure 14b] FIG. 2 is a schematic perspective view of a system according to the invention, showing in particular the presence of two attachment cables at the ends of the cylinder. [Figure 15] 1 is a schematic perspective view of one embodiment of a system according to the present invention; [Figure 16] In particular, it is a schematic diagram showing the means for converting the rotation of a rotatable element obtained by mechanical transmission of the lifting motion of the aircraft into energy. [Figure 17a] FIG. 2 is a partial schematic perspective view of the system according to the invention, showing the position of the tail device during the power generation phase. [Figure 17b] 1 is a schematic perspective partial view of a system according to the invention, showing the position of the tail device during the stage of unwinding the connecting cable. It should be noted that the above drawings are schematic and are not necessarily drawn to scale for ease of reading and so that the drawings can be easily understood. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0040] For simplicity, in the various embodiments, identical elements, or elements providing the same functionality, use the same reference numbers.

[0041] The object of the present invention is to an aircraft of the Magnus effect type, comprising a cylinder 1 extending along a longitudinal axis Y, the cylinder 1 being capable of rotating about the longitudinal axis Y; a rotatable element 2 arranged away from the aircraft; and - drive means 3 arranged to drive the rotational movement of the rotatable element 2; a connecting cable 4 arranged to connect the rotatable element 2 to the aircraft cylinder 1 such that a rotational movement of the rotatable element 2 driven by the drive means 3 is mechanically transmitted to the aircraft cylinder 1 to rotate the cylinder 1 about its longitudinal axis Y; A remote control system for an aircraft comprising: aircraft

[0042] The cylinder 1 forms the wing of the aircraft. Rotating the cylinder 1 about a longitudinal axis Y makes it possible to use the Magnus effect to increase the lift of the aircraft. The cylinder 1 has first and second longitudinal ends 10, 11 (shown in FIG. 8). The aircraft advantageously comprises first and second disks 100, 110 mounted respectively on the first and second longitudinal ends 10, 11 of the cylinder 1 so as to improve the aerodynamic performance of the aircraft. The first and second disks 100, 110 are advantageously removably mounted on the first and second longitudinal ends 10, 11 of the cylinder 1 so as to disengage from the cylinder 1 so as to provide a landing gear function. The first and second disks 100, 110 advantageously rotate freely relative to the cylinder 1 when the aircraft is on the ground. In flight, the first and second disks 100, 110 rotate together with the cylinder 1.

[0043] The cylinder 1 advantageously has a circular cross section with a diameter indicated by D. The cylinder 1 advantageously has a length along a longitudinal axis Y indicated by L, establishing an LD ratio ranging between 6 and 12.

[0044] The cylinder 1 is advantageously filled with a gas having a mass density lower than the air density so as to generate an Archimedean lift force. The mass of the aircraft is therefore smaller than the mass of the air, so that the aircraft becomes an aerostat. The gas can be hydrogen or helium. The gas can be pressurized, for example between 20 and 50 mbar, depending on the dimensions of the cylinder 1, so that the pressure of the gas in the cylinder 1 is higher than atmospheric pressure. The cylinder 1 can be manufactured in the form of a balloon. The cylinder 1 can be equipped with a casing made of an airtight textile material. The pressurized gas hardens the cylinder 1. To improve the mechanical strength of the cylinder 1, the cylinder 1 is provided with a reinforcing member 12, which can advantageously be manufactured in the form of a longitudinal rod extending along an axis parallel to the longitudinal axis Y of the cylinder 1. As shown in FIG. 8, the cylinder 1 can be equipped with an internal element 13, manufactured for example in the form of a disk, which is arranged to reinforce the mechanical strength of the cylinder 1. The internal element 13 can also be arranged inside the cylinder 1, for example to form a compartment for the pressurized gas.

[0045] The aircraft advantageously comprises a dynamoelectric machine arranged to convert mechanical energy (rotation of the cylinder 1 about the longitudinal axis Y) into electrical energy. The electrical energy generated by the dynamoelectric machine can power components of the aircraft such as sensors, on-board computers, de-icing devices, devices for maintaining the pressure of the gas in the cylinder 1, etc. It is also possible to use other types of machines capable of converting the mechanical energy of the rotation of the cylinder 1 about the longitudinal axis Y (for example into heat for de-icing).

[0046] The aircraft is advantageously equipped with means for obtaining characteristics of the wind blowing against the cylinder 1, such as an anemometer arranged to send data representative of the characteristics of the wind V to a processing / control means, such as a microcontroller. The processing / control means may be on board the aircraft. The aircraft is advantageously equipped with means for obtaining parameters specific to the cylinder 1, such as an inertial unit arranged to send data representative of the orientation of the cylinder relative to the wind V, the velocity of the cylinder 1, the acceleration of the cylinder 1, etc. to the processing / control means.

[0047] The aircraft may be provided with first and second cylinders 1, 1' extending along first and second longitudinal axes Y, Y', respectively, and the first and second cylinders 1, 1' are capable of rotating around the first and second longitudinal axes Y, Y', respectively.

[0048] The aircraft comprises a support structure 5 arranged to support the cylinder 1. The cylinder 1 is mounted on the support structure 5 so that it can rotate about a longitudinal axis Y. The support structure 5 may comprise a set of branches forming a frame for the cylinder. The support structure may comprise two longitudinal branches 50, each extending along a first axis parallel to the longitudinal axis Y of the cylinder 1. The support structure 5 may comprise two transverse branches 51, each extending along a second axis perpendicular to the first axis and connected to the longitudinal branches 50. The cylinder 1 may be mounted on the transverse branches 51 of the support structure 5 so that it can rotate about the longitudinal axis Y, for example by means of a mechanical shaft 510 and a mechanical bearing 511 (shown in particular in FIG. 7 ).

[0049] An aircraft in a lifting state has a yaw axis Z and is intended to be subjected to a wind V. By convention, the longitudinal axis Y along which the cylinder 1 extends is the pitch axis. The yaw axis Z and the roll axis X are mutually orthogonal and extend in a plane orthogonal to the longitudinal axis Y (i.e. the pitch axis). When the pitch axis Y is horizontal, the yaw axis Z is vertical and the roll axis X is horizontal. As shown in FIG. 7, the pitch axis Y, the yaw axis Z and the roll axis X are mutually orthogonal.

[0050] The system advantageously comprises: a first branch 520 connected to the first cylinder 1; a second branch 521 connected to the second cylinder 1′; 10 and 11), where the first and second branches 520, 521 form a sweep angle adapted to stabilize the aircraft along the yaw axis Z as a function of the wind V.

[0051] According to an alternative embodiment, the system comprises a straight connecting element 53 (shown in figures 9 and 15) arranged to connect the first and second cylinders 1, 1'.

[0052] The aircraft may be equipped with propellers (not shown) disposed on the support structure 5 to facilitate take-off and landing of the aircraft. Rotatable elements

[0053] The rotatable element 2 is advantageously the drum of a winch, capable of converting a rotational movement into a linear movement of the connecting cable 4 and vice versa. By way of example, the linear velocity of the connecting cable 4 is 0 m.s -1 From 40m.s -1 The connecting cable 4 is advantageously wound around the drum of the winch.

[0054] According to an alternative embodiment, shown in figure 2, the system may comprise two pairs of rotatable elements 2, each of which is manufactured in the form of a return pulley. Each pair of rotatable elements 2 is arranged to clamp a connecting cable 4.

[0055] According to an alternative embodiment shown in FIG. 4a, the cylinder 1 can be provided with a transmission shaft 30 which rotates the cylinder 1 by means of a pulse, the transmission shaft 30 being mounted on the aircraft against the action of elastic return means 31, for example a spring. A connecting cable 4 connects the transmission shaft 30 to the rotatable element 2. The rotatable element 2 sends a pulse to the connecting cable 4 which pulls the transmission shaft 30 and causes the cylinder 1 to rotate about the longitudinal axis Y. The aircraft is advantageously provided with a horizontal stabilizer 82 (see paragraph "Tail device") arranged to compensate the torque generated by the elastic return means 31. Driving Means

[0056] The drive means 3 may comprise a motor, preferably an electric motor, arranged to drive the rotational movement of the rotatable elements 2. The drive means 3 may drive the rotatable elements 2 directly or indirectly. An example of an indirect drive is shown in FIG. 3, where a linear motor 3 pulls a connecting cable 4 and thereby rotates the rotatable elements 2. If the system comprises a pair of rotatable elements 2 (first and second rotatable elements 2) arranged away from the aircraft, the drive means is arranged to drive the rotational movement of the pair of rotatable elements 2. In other words, the drive means is arranged to drive the first and / or second rotatable elements 2 of the pair. The first and second rotatable elements may be independent in the sense that the first and second rotatable elements may have different rotational speeds (winding, unwinding, stopping). In other words, it is possible to introduce a difference in rotational speed between the first rotatable element 2 and the second rotatable element 2 of the pair.

[0057] The aircraft in the lift state is intended to be subjected to a wind V. The system advantageously comprises control means arranged to control the drive means as a function of the wind V. Thus, by varying the rotational speed of the rotatable element 2 it is possible to vary the lift of the aircraft and therefore the altitude of the aircraft.

[0058] The control means can control the rotational speed of the winch drum so that the tangential velocity at a certain point on the cylinder 1 is faster than the speed of the wind V blowing in the vicinity of this point on the cylinder 1 (apparent wind). Station

[0059] The system advantageously comprises a station, preferably a land or sea station, on which one or more rotatable elements 2 and drive means 3 are arranged. The station may be fixed to the Earth reference frame or movable relative to it. The mobile station may be manufactured in the form of a vehicle, such as a submarine.

[0060] According to an embodiment, not shown, the system may comprise means for correcting the direction (e.g. a return pulley) arranged to correct the direction of the connecting cable 4 between the station and the aircraft, which makes it possible, for example, to prevent the connecting cable 4 from coming into contact with obstacles present on the ground.

[0061] The station and the aircraft are advantageously provided with communication means, preferably wireless communication means, so that communication can be established between the station and the aircraft. Connection cable

[0062] The connecting cable 4 may be made of a dielectric material. The connecting cable 4 advantageously has a high tensile strength. The connecting cable 4 may be made of a polymeric material, for example high density polyethylene. The connecting cable 4 may be equipped with a gas duct arranged to supply pressurized gas to the cylinder 1.

[0063] As shown in Figures 1 and 12, the system may comprise an anchoring zone ZA located away from the aircraft, the connecting cable 4 being fixed to the anchoring zone ZA.

[0064] As shown in figure 4b, the connecting cable 4 may be connected to the reeving 40 so as to form a continuous loop. The drive means 3 may therefore be offset relative to the rotatable element 2.

[0065] According to an alternative embodiment shown in Figure 5, the connecting cable 4 may be connected to a set of rotatable elements 2 so as to form a continuous loop, the drive means 3 being offset relative to the rotatable elements 2. One of the two rotatable elements 2 shown in Figure 5 may be blocked in rotation to allow translational movement of the connecting cable 4 in order to rotate the cylinder 1 about the longitudinal axis Y. Transmission of rotational motion of a rotatable element to a cylinder

[0066] According to one embodiment, the connecting cable 4 is wound around the aircraft cylinder 1 such that the rotational movement of the rotatable element 2 driven by the drive means 3 is mechanically transmitted to the aircraft cylinder 1 by friction on the connecting cable 4, causing the cylinder 1 to rotate around the longitudinal axis Y.

[0067] If the system comprises a pair of rotatable elements 2 located away from the aircraft, the connecting cable 4 is wrapped around the aircraft cylinder 1 such that the rotational movement of the pair of rotatable elements 2 driven by the drive means 3 is mechanically transmitted by friction on the connecting cable 4 to the aircraft cylinder 1, causing the cylinder 1 to rotate about the longitudinal axis Y.

[0068] According to an alternative embodiment, the system comprises a transmission device 6 arranged to mechanically cooperate with the connecting cable 4 and the aircraft cylinder 1, such that a rotational movement of the rotatable element 2 driven by the drive means 3 is mechanically transmitted by the transmission device 6 to the aircraft cylinder 1 to rotate the cylinder 1 about the longitudinal axis Y. The transmission device 6 advantageously comprises an arrangement in which the mechanical transmission of the rotational movement of the rotatable element 2 to the cylinder 1 is interrupted, so that the cylinder 1 is free to rotate about the longitudinal axis Y. The transmission device 6 preferably comprises a freewheel or a clutch. The transmission device 6 is advantageously mounted on the first and second longitudinal ends 10, 11 of the cylinder 1, as shown in FIG. 9.

[0069] In case the system comprises a pair of rotatable elements 2 located remotely from the aircraft, the transmission device 6 is arranged to mechanically cooperate with the connecting cable 4 and the aircraft cylinder 1 such that a rotational movement of the pair of rotatable elements 2 driven by the drive means 3 is mechanically transmitted by the transmission device 6 to the aircraft cylinder 1 to rotate the cylinder 1 about its longitudinal axis Y. The transmission device 6 advantageously comprises an arrangement in which the mechanical transmission of the rotational movement of the pair of rotatable elements 2 to the cylinder 1 is interrupted, so that the cylinder 1 is free to rotate about its longitudinal axis Y. Guide Means

[0070] The aircraft advantageously comprises guide means arranged to guide the connecting cable 4 between two positions relative to the cylinder 1 defining a maximum roll angle. The guide means advantageously comprise rings 7 mounted on the support structure 5 of the aircraft and adapted to receive the connecting cable 4. The guide means advantageously comprise tubes 7 arranged on the support structure 5 of the aircraft. The two rings 7, each adapted to receive a connecting cable 4, are advantageously slidably mounted on the tubes 70, for example using sliders 700, so as to define a maximum roll angle. As an alternative embodiment, the guide means can be rolling elements (e.g. pulleys, rollers) for minimizing friction with the connecting cable 4.

[0071] The guiding means are advantageously arranged to guide the connecting cable 4 on the surface S of the cylinder 1. The system is advantageously configured to control the wrap angle of the connecting cable 4 on the surface S of the cylinder 1 (and therefore to control the transmitted power) as a function of the tension on the connecting cable 4 on both sides of the cylinder 1, for example by means of the Capstan formula (also called Eitelwein formula) known to the person skilled in the art. Mounting Cable

[0072] As an alternative embodiment of the guide means, the system may comprise a first and / or a second attachment cable CA fixed to the first and / or second longitudinal ends 10, 11, respectively, of the cylinder 1 and connected to the first and / or second winch 2', respectively. As shown in Fig. 14a, the system comprises an attachment cable CA fixed to the longitudinal ends 10, 11 of the cylinder 1. As shown in Fig. 14b, the system comprises two attachment cables CA, each attached to another longitudinal end 10, 11 of the cylinder 1.

[0073] As shown in FIG. 10, the system may comprise an attachment cable CA fixed to the elbow element 52 and connected to a winch 2' for controlling the pitch angle of the aircraft. An embodiment using a cylinder

[0074] According to a first embodiment, particularly illustrated in Figures 6 and 7, the system may comprise a pair of rotatable elements 2 arranged remotely from the aircraft, - drive means 3 are arranged to drive the rotational movement of the pair of rotatable elements 2; - the connecting cable 4 is arranged to connect the pair of rotatable elements 2 to the aircraft cylinder 1 such that a rotational movement of the pair of rotatable elements 2 driven by the drive means 3 is mechanically transmitted to the aircraft cylinder 1 to rotate the cylinder 1 about the longitudinal axis Y.

[0075] According to a second embodiment, not shown, the system comprises: an additional pair of rotatable elements 2 arranged away from the aircraft; and -Additional connection cables 4 and

[0033] - drive means 3 are arranged to drive the rotational movement of the additional pair of rotatable elements 2; -The additional connecting cable 4 is arranged to connect the additional pair of rotatable elements 2 to the aircraft cylinder 1 such that the rotational movement of the additional pair of rotatable elements 2 driven by the drive means 3 is mechanically transmitted to the aircraft cylinder 1 to rotate the cylinder 1 around the longitudinal axis Y. Two-cylinder embodiment

[0076] The aircraft may be provided with first and second cylinders 1, 1' extending along first and second longitudinal axes Y, Y', respectively, and the first and second cylinders 1, 1' are capable of rotating around the first and second longitudinal axes Y, Y', respectively.

[0077] According to a first embodiment, particularly as shown in Figs. 10 and 15, the system comprises: a pair of rotatable elements 2 and a further pair of rotatable elements 2, positioned away from the aircraft; - 4 connecting cables and 4 additional connecting cables It can be provided with:

[0078] The drive means 3 are arranged to drive the rotational movement of the pair of rotatable elements 2 and the further pair of rotatable elements 2 .

[0079] The connecting cable 4 is arranged to connect the pair of rotatable elements 2 to the first cylinder 1 of the aircraft such that the rotational movement of the pair of rotatable elements 2 driven by the drive means 3 is mechanically transmitted to the first cylinder 1 to rotate the first cylinder 1 about the first longitudinal axis Y.

[0080] The additional connecting cable 4 is arranged to connect the additional pair of rotatable elements 2 to the second cylinder 1' of the aircraft such that the rotational movement of the additional pair of rotatable elements 2 driven by the drive means 3 is mechanically transmitted to the second cylinder 1' of the aircraft to rotate the second cylinder 1' around the second longitudinal axis Y'.

[0081] According to a second embodiment, particularly as shown in Figs. 9 and 13, the system comprises: - two pairs of rotatable elements 2 arranged away from the aircraft; -Two connecting cables 4 and and a first and second assembly each comprising: - drive means 3 arranged to drive the rotational movement of the rotatable elements 2 of the first and second assemblies; each connecting cable 4 of the first assembly is arranged to connect a pair of rotatable elements 1 of the first assembly to a first cylinder 1 of the aircraft such that a rotational movement of the rotatable elements 2 of the first assembly driven by the drive means 3 is mechanically transmitted to the first cylinder 1 of the aircraft to rotate the first cylinder 1 about a first longitudinal axis Y; - each connecting cable 4 of the second assembly is arranged to connect a pair of rotatable elements 2 of the second assembly to a second cylinder 1' of the aircraft such that the rotational movement of the rotatable elements 2 of the second assembly driven by the drive means 3 is mechanically transmitted to the second cylinder 1' of the aircraft, causing the second cylinder 1' to rotate about the second longitudinal axis Y';

[0082] It is possible to envisage that there are more than two cylinders 1 , 1 ′, each cylinder 1 , 1 ′ being connected to at least one pair of rotatable elements 2 . Tail Device

[0083] The aircraft in a lifting state has a yaw axis Z and is intended to be subjected to a wind V. The system advantageously comprises a tail device 8 arranged to stabilize the aircraft along the yaw axis Z as a function of the wind V. The tail device 8 is mounted on a support structure 5 of the aircraft. More specifically, the tail device 8 may be mounted on a longitudinal branch 50 of the support structure 5 so as to be able to rotate about a first axis of the longitudinal branch 50.

[0084] The tail device 8 advantageously comprises an arm 80 extending along a longitudinal axis. The arm 80 has opposite first and second ends. The arm 80 is mounted on said longitudinal branch 50 of the structure of the support 5 in a pivotable manner around the first axis of the longitudinal branch 50, for example by means of an articulation mechanism 800. The tail device 8 advantageously comprises a first stabilizer 81, called vertical stabilizer, extending in a first direction perpendicular to the longitudinal axis of the arm 80. If the longitudinal axis of the arm 80 is horizontal, the first direction is vertical. The first stabilizer 81 is fixed to the first end of the arm 80. The tail device 8 advantageously comprises a second stabilizer 82, called horizontal stabilizer, extending in a second direction perpendicular to the first direction and to the longitudinal axis of the arm 80. If the longitudinal axis of the arm 80 is horizontal, the second direction is horizontal. A second stabilizer 82 is fixed to the first end of the arm 80. The second stabilizer 82 allows passive alignment of the tail device 8 with respect to the apparent wind V in order to maximize the stabilizing effect of the first stabilizer 81.

[0085] The first stabilizer 81 advantageously comprises two independent control surfaces 810 pivotally mounted about a first direction in which the first stabilizer 81 extends. As shown in Figures 17a and 17b, the pivot angles of the two control surfaces 810 relative to the first direction of the first stabilizer 81 are adapted to the wind direction V to generate a kinematic movement about the yaw axis Z. The position of the longitudinal axis of the arm 80 is parallel to the wind direction V.

[0086] As shown in Figures 6 and 7, the tail device 8 advantageously comprises a sensor module 83 mounted on the second end of the arm 80. By way of non-limiting example, the sensor module 83 may be adapted to measure the direction and speed of the wind V, the position, altitude, speed and acceleration of the aircraft. As an alternative embodiment, the sensor module 83 may be mounted on the support structure 5 of the aircraft, as shown in Figure 9. Energy Conversion Applications

[0087] The connecting cable 4 is advantageously arranged to connect the aircraft to the rotatable element 2 such that the lifting motion of the aircraft can be mechanically transmitted to the rotatable element 2 .

[0088] The system advantageously comprises a converter arranged to convert into energy the rotation of the rotatable element 2 obtained by mechanical transmission of the lifting motion of the aircraft.

[0089] According to an embodiment, the converter may comprise a generator arranged to convert the rotation of the rotatable element into electrical energy. If the rotatable element 2 is the drum of a winch, the drive means 3 consumes energy to wind up the connecting cable 4, while the lifting movement of the aircraft unwinds the connecting cable 4 and recovers the electrical energy. For example, the generator arranged in the station may be electrically connected via the electrical interconnection means 9 to an electrical network RE (shown in FIG. 9 ), or to an energy storage system. The electrical network RE may supply electrical power to the station, specifically to the drive means 3, via the electrical interconnection means 9.

[0090] According to the embodiment shown in figure 16, each rotatable element 2 is connected to a mechanical transmission TM. a first position in which the mechanical transmission TM is connected to a hydraulic (or pneumatic) generator G, such as a pump, or - in a second position, the mechanical transmission TM is connected to a hydraulic (or pneumatic) motor M has.

[0091] The hydraulic / pneumatic generator G belongs to a hydraulic / pneumatic circuit 90 which comprises a low pressure tank 900 and a high pressure tank 901. The hydraulic / pneumatic generator G pumps the fluid (e.g. oil or compressed air) of the hydraulic / pneumatic circuit 90 from the low pressure tank 900 (e.g. atmosphere in the case of the pneumatic circuit 90) to the high pressure tank 901. Thus, energy is stored by the pressure of the fluid in the high pressure tank 901.

[0092] When the connecting cable 4 needs to be unwound, the mechanical transmission TM switches from the first position to the second position. The flow of fluid from the high pressure tank 901 to the low pressure tank 900 consumes energy.

[0093] To produce electricity, the hydraulic / pneumatic circuit 90 is connected to an additional hydraulic / pneumatic motor M' which starts a generator G'. Thus, via this temporary storage system (of the order of a few hours), electricity production can be smoothed or adapted according to the requirements of the electricity consumption demand.

[0094] The present invention is not limited to the disclosed embodiments, and those skilled in the art can consider technically effective combinations of the disclosed embodiments and replace them with equivalents.

Claims

1. A remote control system for an aircraft, comprising: - a Magnus effect aircraft having a cylinder (1) extending along a longitudinal axis (Y), the cylinder (1) being rotatable about the longitudinal axis (Y); - a pair of rotatable elements (2) disposed remotely from the aircraft; - drive means (3) arranged to drive the rotational movement of the pair of rotatable elements (2); - a connecting cable (4) arranged to connect the pair of rotatable elements (2) to the cylinder (1) of the aircraft such that the rotational movement of the pair of rotatable elements (2) driven by the drive means (3) is mechanically transmitted to the cylinder (1) of the aircraft by friction on the connecting cable (4) to rotate the cylinder (1) about the longitudinal axis (Y). A remote control system.

2. The system according to claim 1, wherein the connecting cable (4) is wound around the cylinder (1) of the aircraft such that the rotational movement of the pair of rotatable elements (2) driven by the drive means (3) is mechanically transmitted to the cylinder (1) of the aircraft by friction on the connecting cable (4) to rotate the cylinder (1) about the longitudinal axis (Y).

3. The system according to claim 1, further comprising a transmission device (6) arranged to cooperate mechanically with the connecting cable (4) and the cylinder (1) of the aircraft such that the rotational movement of the pair of rotatable elements (2) driven by the drive means (3) is mechanically transmitted to the cylinder (1) of the aircraft by the transmission device (6) to rotate the cylinder (1) about the longitudinal axis (Y).

4. The system according to claim 3, wherein the transmission device (6) is configured such that mechanical transmission of the rotational movement of the pair of rotatable elements (2) to the cylinder (1) is interrupted, whereby the cylinder (1) is free to rotate about the longitudinal axis (Y), and the transmission device (6) preferably comprises a freewheel or a clutch.

5. The system according to claim 1, wherein the aircraft in a lift state is intended to receive wind (V), and the system comprises control means configured to control the drive means (3) as a function of the wind (V).

6. The system according to claim 1, wherein the aircraft comprises guide means (7) arranged to guide the connection cable (4) between two positions relative to the cylinder (1) defining the maximum roll angle.

7. The system according to claim 1, wherein the cylinder (1) has first and second longitudinal ends (10, 11), and the system comprises first and / or second attachment cables (CA) respectively fixed to the first and / or second longitudinal ends (10, 11) of the cylinder (1) and respectively connected to first and / or second winches (2').

8. - additional pairs of rotatable elements (2) arranged remote from the aircraft, - additional connection cables (4) comprising - the drive means (3) being arranged to drive the rotational movement of the additional pairs of rotatable elements (2), - the additional connection cable (4) being arranged to connect the additional pairs of rotatable elements (2) to the cylinder (1) of the aircraft such that the rotational movement of the additional pairs of rotatable elements (2) driven by the drive means (3) is mechanically transmitted to the cylinder (1) of the aircraft to rotate the cylinder (1) about the longitudinal axis (Y).

9. - the aircraft comprises first and second cylinders (1, 1') extending along first and second longitudinal axes (Y, Y') respectively, the first and second cylinders (1, 1') being rotatable about the first and second longitudinal axes (Y, Y') respectively, - the connection cable (4) being arranged to connect the pair of rotatable elements (2) to the first cylinder (1) of the aircraft such that the rotational movement of the pair of rotatable elements (2) driven by the drive means (3) is mechanically transmitted to the first cylinder (1) of the aircraft to rotate the first cylinder (1) about the first longitudinal axis (Y). - the additional connecting cable (4) is arranged such that the rotational movement of the additional pair of rotatable elements (2) driven by the drive means (3) is mechanically transmitted to the second cylinder (1') of the aircraft to rotate the second cylinder (1') about the second longitudinal axis (Y'), and the additional pair of rotatable elements (2) is connected to the second cylinder (1') of the aircraft, the system according to claim 8.

10. - two pairs of rotatable elements (2) arranged remote from the aircraft, - two connecting cables (4) and first and second assemblies each comprising, - the aircraft comprises first and second cylinders (1, 1') extending along first and second longitudinal axes (Y, Y') respectively, the first and second cylinders (1, 1') being rotatable about the first and second longitudinal axes (Y, Y') respectively, - the drive means (3) is arranged to drive the rotational movement of the rotatable elements (2) of the first and second assemblies, - each connecting cable (4) of the first assembly is arranged such that the rotational movement of the rotatable element (2) of the first assembly driven by the drive means (3) is mechanically transmitted to the first cylinder (1) of the aircraft to rotate the first cylinder (1) about the first longitudinal axis (Y), and one pair of rotatable elements (2) of the first assembly is connected to the first cylinder (1) of the aircraft, - each connecting cable (4) of the second assembly is arranged such that the rotational movement of the rotatable element (2) of the second assembly driven by the drive means (3) is mechanically transmitted to the second cylinder (1') of the aircraft to rotate the second cylinder (1') about the second longitudinal axis (Y'), and one pair of rotatable elements (2) of the second assembly is connected to the second cylinder (1') of the aircraft, the system according to claim 1.

11. The aircraft in a lift state has a yaw axis (Z) and is intended to receive wind (V), and the system has - a first branch (520) connected to the first cylinder (1), - a second branch (521) connected to the second cylinder (1') comprising an elbow element (52) having, the first and second branches (520, 521) forming a sweep angle adapted to stabilize the aircraft along the yaw axis (Z) as a function of the wind (V), the system according to claim 9.

12. The system according to claim 1, wherein the rotatable element (2) is a drum of a winch.

13. The system according to claim 1, wherein the connection cable (4) is arranged to connect the aircraft to the pair of rotatable elements (2) such that a lift movement of the aircraft can be mechanically transmitted to the rotatable element (2).

14. The system according to claim 13, comprising a converter arranged to convert the rotation of the pair of rotatable elements (2) obtained by the mechanical transmission (TM) of the lift movement of the aircraft into energy.

15. The aircraft in a lift state has a yaw axis (Z) and is intended to receive the wind (V), the system comprising a tail device (8) arranged to stabilize the aircraft along the yaw axis (Z) as a function of the wind (V), the system according to claim 1.

Images