• 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 present invention relates to a Drone (1) comprising a carrier structure (2), at least three propulsion and propulsion rotors (3-6) and a control system (7) for delivering at least one electrical power supply of at least three electric motors (8) respectively rotating said at least three rotors (3-6), said at least three rotors (3-6) being longitudinally and transversely spaced apart from one another, characterized in that said drone (1) comprises: • a wing (9) comprising two half-wings (10), symmetrical with respect to an anteroposterior plane of symmetry P of said drone (1), intended at least to increase the lift of said drone (1), each of said two half-wings (10) comprising at least one movable portion (11) able to move relative to said carrier structure (2) of said drone (1) according to at least a first degree of freedom in rotation along a first axis rotation parallel to a longitudinal direction X of said drone (1), • two first electric actuators for respectively moving said movable portion (11) respectively of one of said two half-wings (10).
    公开号:FR3050385A1
    申请号:FR1600688
    申请日:2016-04-26
    公开日:2017-10-27
    发明作者:Lionel Thomassey
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    Drone comprising at least three lift and propulsion rotors.
    The present invention relates to the field of aircraft without any pilot or crew on board. Such aircraft are commonly referred to by the term UAV or by the acronym UAV denoting in English the expression "Unmanned Aerial Vehicle".
    More particularly, the invention relates to a drone comprising at least three lift and propulsion rotors driven in rotation by at least three independent electric motors and controlled by a centralized control system.
    In addition, such drones can be either autonomous and then comprise automatic navigation and control means, either remotely controlled and in this case comprise at least control signal receiving means using a wireless communication protocol, for example radio frequencies. Such control signals then make it possible to remotely control the control system of the at least three rotors equipping this type of drone.
    Thus to achieve their propulsion and lift, such drones have a set of levitation formed by these at least three rotors. If such a lift set makes it possible to perform hovering phases, however, it consumes a lot of electrical energy, especially during the hovering phases, but also during cruising flight when the drones can reach a remote location.
    Such drones with at least three lift and propulsion rotors therefore do not have a high autonomy or endurance and / or can not perform missions over long distances.
    The present invention therefore aims to provide a drone comprising at least three lift and propulsion rotors to overcome the limitations mentioned above. Such a drone according to the invention thus makes it possible to reach places distant from a departure base located several tens of kilometers, or even several hundred kilometers, from the base of departure and, if necessary, to return to this base of departure. This increase in autonomy is obtained in particular by reducing the electrical energy consumption of the at least three rotors during a flight phase in advancing the drone. The invention therefore relates to a drone comprising a carrier structure, at least three lift and propulsion rotors and a control system for delivering at least one electrical power supply of at least three electric motors respectively rotating the at least three rotors. These at least three rotors are spaced longitudinally and transversely next to each other.
    This drone is remarkable in that, on the one hand, it comprises: • a wing comprising two half-wings, symmetrical with respect to a plane of anteroposterior symmetry of the drone, intended at least to increase the lift of the drone, each of the two half-wings comprising at least one movable portion adapted to move relative to the carrier structure of the drone according to at least a first degree of freedom in rotation along a first axis of rotation R parallel to a longitudinal direction X of the drone, each movable portion being able to move between a folded position in which each mobile portion forms a landing gear of the drone and a deployed position in which each mobile portion increases the lift of the drone, • first two electric actuators for respectively moving the movable portion respectively of each of the two half-wings, and secondly, the control system delivers at least one energy supply e electrical of the first two electric actuators to each perform a displacement of the movable portion of the two half-wings between the folded position and the deployed position and / or vice versa between the deployed position and the folded position.
    In other words, the movable portions of the two half-wings of the drone are arranged in a pivot-type connection relative to the support structure. These movable portions of the half-wings can then serve alternately landing gear or fixed wing to increase punctually in flight lift of the drone. In this way when the half-wings are deployed, it reduces the electrical energy consumption of the electric motors driving in rotation the at least three propulsion and lift rotors. These two half-wings are, of course, arranged symmetrically on either side of the carrier structure of the drone, their respective spans extending substantially perpendicular to the longitudinal direction X of the drone.
    The first two electric actuators thus make it possible to move the movable portion of each half-wing in at least a first direction in rotation between the folded position and the deployed position or vice versa between the deployed position and the folded position. The return to the initial position corresponding to the folded position or the deployed position can in turn be realized either by the first two electric actuators operating in a second direction opposite to the first direction in rotation, or by elastic return means such as at least one spring biased in tension, compression or torsion.
    In addition, the on-board control system on the drone makes it possible simultaneously to control the supply of electrical energy to the at least three electric motors respectively rotating the at least three rotors and the first two electric actuators to move the moving portions of the two half-wings.
    According to a first variant, the first electric actuators may for example be formed by jacks for performing a linear displacement between a point of each movable portion and a point of the carrier structure of the drone. These two points are also distant from the first axis of rotation R to allow the rotational displacement of each movable portion relative to the carrier structure of the drone.
    According to a second variant, the first electric actuators may for example be formed by reduction motors incorporating an encoder capable in particular of determining an angular position of the rotation of the movable portion relative to the carrier structure of the drone. This type of first actuator according to the second variant is then advantageously arranged at the first axis of rotation R.
    Advantageously, the at least one movable portion may be able to move relative to the carrier structure of the drone according to a second degree of freedom in rotation along a second axis of rotation R 'substantially parallel to a transverse direction Y of the drone when the portion mobile of the two half-wings is arranged in the deployed position.
    In other words, the movable portion of each half-wing can pivot about two axes of rotation R and R 'for example perpendicular to each other. Each movable portion is thus arranged according to a cardan type connection or finger ball joint with the carrier structure of the drone.
    In addition, each movable portion is pivotable independently of one another about the second axis of rotation R '. As a result, the angle of rotation corresponding to the angular position of a left mobile portion of the left half-wing of the drone with respect to the carrying structure may be different from the angle of rotation corresponding to the angular position of a moving right portion of the right half-wing of the drone relative to the supporting structure.
    Thus, when the angle of rotation corresponding to the angular position of a movable portion of a left half-wing relative to the support structure is modified in a direction opposite to the angle of rotation corresponding to the angular position of a movable portion of a right half-wing relative to the carrier structure, the control system can control the drone roll.
    On the other hand, when the angle of rotation corresponding to the angular position of a movable portion of a left half-wing relative to the supporting structure is modified simultaneously while remaining equal to the angle of rotation corresponding to the angular position of a movable portion of a right half-wing relative to the carrier structure, the control system can control the drone in pitch and ensures any change in altitude.
    In practice, each of the at least one movable portion may comprise: a spar having a proximal end at which at least two first bearings are arranged to form a pivot-type connection along the first axis of rotation R with the bearing structure of the drone, a distal end opposite the proximal end, • at least one aerodynamically profiled element covering the spar, • at least two second bearings to form a pivot-type connection along the second axis of rotation R 'between the spar and the spar. aerodynamically profiled element.
    In this way, the at least two first bearings make it possible to achieve the first degree of freedom in rotation along the first axis of rotation R between the spar and the carrier structure of the drone.
    Similarly, the at least two second bearings make it possible to form the second degree of freedom in rotation along the second axis of rotation R 'between the spar and the profiled element. These at least two second bearings are advantageously spaced apart to limit the overhang of the profiled element relative to the first two bearings. One of said second bearings is then arranged near the proximal end of the spar while the other of said second bearings is arranged near the distal end of the spar. In addition, the second axis of rotation R 'is substantially arranged according to the span of the spar.
    These first and second bearings may for example be formed by ball bearings, needle or roller bearings, by so-called self-lubricated bronze bearings or by plain bearings formed in a polymer material with a low coefficient of friction such that polytetrafluoroethylene, in particular.
    In addition, such an aerodynamically profiled element comprises an internal structure secured to the at least two second bearings and an outer covering having an extrados face and a lower face. The internal structure and the outer coating of the profiled element can then be formed by two disjoint structures secured together in connection with the type embedding or be a monolithic piece formed in the same material.
    Furthermore, the spar may be tubular.
    Thus, the spar is advantageously hollow throughout its length between its proximal end and its distal end. Such a hollow spar can then allow the passage of an electrical connection or any transmission member for rotating the profiled element relative to the spar along the second axis of rotation R ', substantially coinciding with the span of the spar.
    According to a first example, each of the movable portions may comprise a second electric actuator arranged at the distal end of the spar for controlling an angular orientation of the profiled element relative to the spar along the second axis of rotation R 'and the control system can be adapted to deliver an electrical power supply of two second electric actuators.
    In this case, an electrical connection passes through the tubular spar and makes it possible to supply electrical energy to each second electric actuator to control the rotation of each profiled element relative to the corresponding spar.
    Such a second actuator can be formed by a reduction motor and can then for example drive in rotation a toothed pinion integral with the motorized axis of the gear motor, this toothed gear cooperating with an internal gear wheel secured to the profiled element to drive into position. rotating the profiled element relative to the spar. According to an alternative, the gear motor can also rotate a link secured on the one hand with the profiled element and on the other hand with a motorized axis of the gear motor.
    According to a second example, the carrier structure may comprise two second electric actuators, each second electric actuator being arranged respectively close to a proximal end of a spar for controlling the respective angular orientation of a profiled element relative to the corresponding spar. along the second axis of rotation R '. The control system can thus be adapted to deliver an electric power supply of the two second electric actuators.
    Therefore, the two second electric actuators are not arranged in the movable portion of each half-wing and the tubular shape of the spar allows the free passage, or even the rotational guidance, of a transmission member for driving in rotation the profiled element relative to the spar along the second axis of rotation R '.
    Therefore according to a first embodiment of the invention according to the second example each of the movable portions may comprise: a transmission shaft guided in rotation inside the spar, the transmission shaft having a first end driven in rotation by the spindle; one of the two second electric actuators and a second end secured to the profiled element for transmitting a rotational movement of the transmission shaft to the profiled element, a transfer box comprising three bevel gears for transmitting a rotational movement generated by one of the at least two second electric actuators to the transmission shaft.
    In this case, each transmission shaft is then guided in rotation for example by means of ball bearings respectively with a bore of each tubular spar. Each transmission shaft is formed by a rigid axis capable of transmitting a motor torque to generate the rotational movement of each profiled element.
    Furthermore, each transfer box is arranged at the level of the first axis of rotation R of each of the half-wings and makes it possible to transmit the rotational movement of one of the at least two second electric actuators to one of the transmission shafts. whatever the angular position around the first axis of rotation R of the spar with respect to the supporting structure.
    According to a second embodiment of the invention according to the second example, the drone may comprise at least two flexible transmission members, each flexible transmission member having a first end driven in rotation by one of the at least two second electric actuators and a second end secured to one of the profiled elements for transmitting a rotational movement of the flexible transmission member to the profiled element.
    In this other case, the at least two flexible transmission members are also guided in rotation for example by means of ball bearings respectively with a bore of each tubular spar. Such flexible transmission members may for example be formed by a flexible sheath in which a blade is guided by two rows of balls free to rotate inside the sheath.
    Such a second embodiment of the invention is then advantageous compared to the first embodiment of the invention because it requires no transfer box and therefore has a lower mass.
    Moreover, each of the mobile portions may comprise in practice an absorption system for absorbing at least partially the kinetic energy of the drone during landing.
    Such an absorption system may for example comprise a hydraulic or pneumatic cylinder whose first end of rod comes into contact with the ground during a landing of the drone while a cylinder is secured to the movable portion of each half-wing . A second rod end then has a piston for moving a fluid inside the cylinder, the fluid can pass through an orifice in the piston.
    According to a particular embodiment of the invention, the at least three rotors may be formed at least by a left front rotor, a right front rotor, a left rear rotor and a right rear rotor with respect to the longitudinal direction of the drone, the bearing structure comprising an elongated shape in the longitudinal direction X, a longitudinal center distance L separating the axes of rotation of the front rotors and the rotational axes of the rear rotors being greater than a transverse center distance T between the rotational axes of the left rotors and the rotors; rotation axes of the right rotors. The wing can be implanted on the supporting structure in a median zone of the supporting structure in the longitudinal direction X.
    Such an arrangement of the carrier structure then makes it possible to position the half-wings in the median zone of the drone along the longitudinal direction X.
    In addition, the rotors may be of the same diameter 0d and the longitudinal center distance L separating the axes of rotation of the front rotors and the axes of rotation of the rear rotors may be greater than the sum of a diameter 0d of the rotors and a rope C of the half-wing measured near a connection zone of the half-wing with the supporting structure.
    In this way, the airflow generated by each of the rotors does not impact the two half-wings in the deployed position and the rope of each half-wing can be relatively large to provide maximum lift.
    Advantageously, each of the at least one movable portion may further comprise at least one propulsion rotor driven in rotation by at least one electric propulsion motor and the control system may be able to deliver an electric power supply of the at least one motor. electric propulsion.
    In other words, the half-wings may comprise additional propulsion rotors, notably enabling the drone to reach a greater level of plane travel speed than with only its at least three lift and propulsion rotors.
    Moreover, a flight at constant cruising speed can be performed with a horizontal attitude of the drone and no longer inclined as is the case with only the at least three propulsion and lift rotors. The axes of rotation of these propulsion rotors are in this case oriented substantially parallel to the longitudinal direction X of the drone while the axes of rotation of the at least three propulsion and lift rotors are oriented substantially in a direction in elevation Z perpendicular to the longitudinal direction X of the drone. The invention and its advantages will appear in more detail in the context of the following description with examples given by way of illustration with reference to the appended figures which represent: FIG. 1, a perspective view of a drone conforming to FIG. FIG. 2, a top view of a drone according to the invention, FIG. 3, a first front view of a drone according to the invention, FIG. partial face of a drone according to the invention, and - Figures 5 to 12, partial sectional views according to different variants of movable portions of half wings of a drone according to the invention.
    The elements present in several distinct figures can be assigned a single reference.
    As already mentioned, the invention relates to a UAV 1 provided with at least three propulsion and lift rotors.
    Note that three directions X, Y and Z orthogonal to each other are shown in Figures 1 to 3.
    The direction X is said to be longitudinal insofar as it extends from the rear to the front of a carrier structure 2 of the drone 1 having an elongate shape in this longitudinal direction X.
    Another direction Y is said transversal since it extends from the right zone to the left zone of the carrier structure 2 of the drone 1.
    Finally, a third direction Z is elevation and corresponds to the height dimensions of the drone 1. By way of non-limiting example and for the purpose of simplification of the detailed description of the invention, the drone 1 may comprise, as such FIG. 1 shows four rotors 3-6 arranged around the supporting structure 2. These four rotors are then constituted by a left front rotor 3, a right front rotor 4, a left rear rotor 5 and a right rear rotor 6 Each of these rotors 3-6 is rotated by electric motors 8 arranged coaxially respectively on an axis of rotation of each rotor 3-6.
    In addition, each electric motor 8 is supplied with electrical energy by a control system 7 for controlling the drone 1 remotely or to automatically drive it autonomously to perform a predetermined mission.
    Furthermore, such a drone 1 also comprises a wing 9 provided with two half-wings 10 symmetrical with respect to an anteroposterior plane of symmetry P parallel to the plane defined by the axes X and Z. Each half-wing 10 comprises a movable portion 11 relative to the carrier structure 2. Such half-wings 10 then allow to increase the lift of the UAV 1 in flight and thus limit the electrical energy consumption of the electric motors 8 to maintain the UAV 1 at a predetermined altitude.
    As represented in FIG. 2, the carrier structure 2 of the drone 1 comprises an elongate shape in the longitudinal direction X. Thus, a longitudinal center distance L between the rotational axes of the front rotors 3, 4 and the rotational axes of the rear rotors 5, 6 may be greater than a transverse center distance T between the axes of rotation of the left rotors 3, 5 and the axes of rotation of the right rotors 4, 6.
    In addition, such a carrier structure 2 comprises a median zone 16 in the longitudinal direction X from which emerges laterally the two half-wings 10 in a direction substantially parallel to the transverse direction Y.
    Moreover, the four rotors 3-6 may advantageously have the same diameter od.
    In addition, the longitudinal center distance L is greater than the sum of a diameter od of a rotor 3-6 and a rope C of the half-wings 10 measured near a connection zone 15 with the supporting structure 2.
    In this way, the flow of air generated substantially vertically downwards by the four rotors 3-6 is not disturbed by the half-wings 10.
    According to the invention, the movable portion 11 of each half-wing 10 is then free to pivot along a first axis of rotation R and a second axis of rotation R 'with respect to the supporting structure 2.
    The first axis of rotation R is arranged substantially parallel to the longitudinal direction X of the drone 1 while the second axis of rotation R 'is arranged substantially parallel to the transverse direction Y of the drone 1.
    As shown in FIG. 3, the movable portion 11 can then pivot about the first axis of rotation R between a folded position POS1 in which it serves as a landing gear for the drone 1 and a deployed position POS2 in which it increases the lift of the drone 1 in flight.
    The pivoting of this movable portion 11 around the first axis of rotation R is then obtained by means of a first electric actuator 25 supplied with electrical energy by the control system 7 via wire connections 13 which conduct electricity. Likewise, the electric motors 8 of the rotors 3-6 are supplied with electrical energy by the control system 7 via wire connections 12 that conduct electricity.
    As represented in FIG. 4, each movable portion 21 may be equipped with a propulsion rotor 22 rotated by an electric propulsion motor 23 associated and supplied with electrical energy by the control system 7 via conductive wire connections 14 electricity.
    Such a propulsion rotor 22 may advantageously be of the "EDF" type by the term "Electrical Ducted Fan" corresponding to a propeller or a keeled turbine powered by the electric propulsion motor 23.
    These propulsion rotors 22 then make it possible to increase the speed of movement of the drone 1 along its longitudinal direction X by maintaining the rotational speed of the rotors 3-6 at a minimum rotational speed or even by cutting the power supply of the electric motors 8 rotors 3-6.
    Moreover, by applying a differential thrust between the two propulsion rotors 22, it is possible, to a certain extent, to generate a control along a yaw trajectory of the drone 1.
    As represented in FIG. 5 according to a first variant, the first electric actuator 25 may be formed by a jack whose one of its ends is secured to the bearing structure 2 and the other end is secured to the movable portion 11 of the half-wing 10. At least, these ends of the cylinder are remote from the first axis of rotation R to transform the translation movement of the cylinder into a rotational movement of the movable portion 11 about the first axis of rotation R.
    As shown in FIG. 6 according to a second variant, the first electric actuator 26 may be formed by a gear motor arranged on the first axis of rotation R.
    Moreover, as represented in FIGS. 5 to 7, an absorption system 24 can equip the mobile portion 11, 31 to absorb all or part of the kinetic energy of the drone 1 during its landing on the ground or on a platform. Such an absorption system 24 thus comprises a movable member in translation and hydraulic or pneumatic means such as cylinders.
    As illustrated in Figure 7, the movable portion 31 comprises a spar 36 provided with two first bearings 34 at a proximal end 33 of the spar 36. These two first bearings 34 then allow to form the degree of freedom in rotation of the movable portion 31 relative to the supporting structure 2 around the first axis of rotation R.
    Such a spar 36 also has a distal end 35 opposite the proximal end 33. In addition, this spar 36 may be tubular. Furthermore, the absorption system 24 is here represented as comprising a spring 32 cooperating with a bore formed inside the distal end 35.
    The movable portion 31 also comprises a profiled element 37 aerodynamically and guided in rotation about the second axis of rotation R 'so as to be able to pivot freely relative to the spar 36. This guidance in rotation of the profiled element 37 is obtained by means of two second bearings 38 formed for example by ball bearings, needle or roller.
    Furthermore, the rotational drive of the movable portion along the second axis of rotation R 'can be achieved in different ways.
    According to a first example as represented in FIGS. 8 and 9, each movable portion 41, 51 may comprise respectively a second electric actuator 49, 59 making it possible to modify the angular orientation of each profiled element 47, 57 with respect to the spar 46 respectively, 56. In this case, the spar 46, 56 is therefore tubular in shape and makes it possible to route an electrical connection between the proximal end 43, 53 and the distal end 45, 55 of the spar 46, 56.
    As before, two first bearings 44, 54 respectively make it possible to guide the spar 46, 56 about the first axis of rotation R with respect to the supporting structure 2 in rotation. Likewise, two second bearings 48, 58 make it possible respectively to guide in rotation profiled element 47, 57 around the second axis of rotation R 'with respect to the spar 46, 56.
    According to FIG. 8, the second electric actuator 49 can rotate a toothed gear 80 cooperating with an internal gear wheel 81 integral with the profiled element 47.
    According to an alternative as shown in FIG. 9, the second electric actuator 59 can also rotate a motorized axis 83 cooperating with one end of a link 82, the other end of the link 82 cooperating with the profiled element 57 .
    Moreover according to a second example as represented in FIGS. 10 to 12, the second electric actuators 69, 79 can also be respectively arranged at the level of the supporting structure 2 near the proximal end 63, 73 respectively of each spar 66, 76.
    As before, two first bearings 64, 74 make it possible respectively to rotate the spar 66, 76 about the first axis of rotation R with respect to the supporting structure 2. Likewise, two second bearings 68, 78 make it possible to guide the rotation in rotation. profiled element 67, 77 around the second axis of rotation R 'with respect to the spar 66, 76, respectively.
    However in this case, the movable portion 61, 71 is not provided with a second actuator at the distal end 65, 75 of a spar 66, 76. Such a spar 66, 76 is however also of shape tubular and allows the passage of either a transmission shaft 90 or a flexible transmission member 101.
    Thus according to a first embodiment of the invention as shown in FIG. 10, bearings 95 may be housed inside the spar 66 and serve to guide in rotation with respect to the spar 66 a transmission shaft 90 for transmitting a movement. rotation to the profiled element 67.
    A first end 91 of the transmission shaft 90 cooperates with a transfer box 93 provided with three bevel gears 94. A second end 92 of the transmission shaft 90 is in turn secured to the profiled element 67 and allows the second electric actuator 69 to rotate the profiled element 67 around the second axis of rotation R '.
    According to a second embodiment of the invention as shown in FIGS. 11 and 12, guides 104 can also be housed inside the spar 76 and make it possible to hold the flexible transmission member 101 in position to transmit a rotational movement. to the profiled element 77. Such a flexible transmission member 101 is for example formed by a sheath within which a blade is guided by two rows of balls.
    A first end 102 of the sheath is then secured to the second electric actuator 79 and a second end 103 of the sheath is extended by a link 100 cooperating with the profiled element 77 of the movable portion 71.
    Such a flexible transmission member 101 then makes it possible to transmit the rotational movement of the second electric actuator 79 to the profiled element 77 around the second axis of rotation R ', regardless of the angular position of the spar 76 around the first axis. rotation R.
    Naturally, the present invention is subject to many variations as to its implementation. Although several embodiments have been described, it is well understood that it is not conceivable to exhaustively identify all the possible modes. It is of course conceivable to replace a means described by equivalent means without departing from the scope of the present invention.
    权利要求:
    Claims (12)
    [1" id="c-fr-0001]
    1. Drone (1) comprising a supporting structure (2), at least three lift and propulsion rotors (3-6) and a control system (7) for delivering at least one electric power supply of at least three electric motors (8) respectively rotating said at least three rotors (3-6), said at least three rotors (3-6) being longitudinally and transversely spaced apart from one another, characterized in that said drone (1 ) comprises: • a wing (9) comprising two half-wings (10), symmetrical with respect to an anteroposterior plane of symmetry P of said drone (1), intended at least to increase the lift of said drone (1), each of said two half-wings (10) comprising at least one movable portion (11, 21, 31, 41, 51, 61, 71) adapted to move relative to said carrier structure (2) of said drone (1) according to at least a first degree of freedom in rotation along a first axis of rotation R parallel to a longitudinal direction X of said drone (1), each movable portion (11, 21, 31, 41, 51, 61, 71) being able to move between a folded position (POS1) in which each movable portion (11, 21, 31 , 41, 51, 61, 71) forms a landing gear of said drone (1) and an extended position (POS2) in which each movable portion (11, 21, 31, 41, 51, 61, 71) increases the lift said drone (1), • two first electric actuators (25, 26) for respectively moving said movable portion (11, 21, 31, 41, 51, 61, 71) of each of said two half-wings (10), and in that said control system (7) delivers at least one electrical power supply of said first two electric actuators (25, 26) to each effect a displacement of the movable portion (11, 21, 31, 41, 51, 61 , 71) of said two half-wings (10) between said folded position (POS1) and said deployed position (POS2) and / or vice versa between said deployed position (POS2) and said folded position (POS1).
    [2" id="c-fr-0002]
    2. Drone according to claim 1, characterized in that said at least one movable portion (31, 41, 51, 61, 71) is able to move relative to said carrier structure (2) of said drone (1) according to a second degree of freedom in rotation along a second axis of rotation R 'substantially parallel to a transverse direction Y of said drone (1) when said movable portion (31, 41, 51, 61, 71) of said two half-wings (10) is arranged in the deployed position (POS2).
    [3" id="c-fr-0003]
    3. Drone according to claim 2, characterized in that each of said at least one movable portion (31, 41, 51, 61, 71) comprises: • a spar (36, 46, 56, 66, 76) having a proximal end (33, 43, 53, 63, 73) at which at least two first bearings (34, 44, 54, 64, 74) are arranged to form a pivot-type connection along said first axis of rotation R with said structure carrier (2) of said drone (1) and a distal end (35, 45, 55, 65, 75) opposite said proximal end (33, 43, 53, 63, 73), • at least one profiled element (37, 47, 57, 67, 77) aerodynamically covering said spar (36, 46, 56, 66, 76), • at least two second bearings (38, 48, 58, 68, 78) to form a pivot type connection in accordance with said second axis of rotation R 'between said spar (36, 46, 56, 66, 76) and said profiled member (37, 47, 57, 67, 77) aerodynamically.
    [4" id="c-fr-0004]
    4. Drone according to claim 3, characterized in that said spar (36, 46, 56, 66, 76) is tubular.
    [5" id="c-fr-0005]
    5. Drone according to claim 4, characterized in that each of said movable portions (41, 51) comprises a second electric actuator (49, 59) arranged at said distal end (45, 55) of the spar (46, 56). for controlling an angular orientation of said profiled element (47, 57) with respect to said spar (46, 56) along said second axis of rotation R 'and in that said control system (7) is capable of delivering a feed into electrical energy of two second electric actuators (49, 59).
    [6" id="c-fr-0006]
    6. Drone according to claim 4, characterized in that said carrier structure (2) comprises two second electric actuators (69, 79), each second electric actuator (69, 79) being arranged respectively close to a proximal end (63). , 73) of a spar (66, 76) for controlling the respective angular orientation of a profiled element (67, 77) relative to said spar (66, 76) corresponding to said second axis of rotation R 'and in that said control system (7) is adapted to deliver a power supply of said two second electric actuators (69, 79).
    [7" id="c-fr-0007]
    7. Drone according to claim 6, characterized in that each of said at least one movable portion (61) comprises: • a transmission shaft (90) guided in rotation inside said spar (66), said transmission shaft ( 90) having a first end (91) rotated by one of said two second electric actuators (69) and a second end (92) secured to said profiled member (67) for transmitting a rotational movement of said drive shaft ( 90) to said profiled member (67), • a transfer case (93) having three bevel gears (94) for transmitting rotational movement generated by one of said at least two second electric actuators (69) to said drive shaft (90).
    [8" id="c-fr-0008]
    8. Drone according to claim 6, characterized in that said drone (1) comprises at least two flexible transmission members (101), each flexible transmission member (101) having a first end (102) rotated by the one of said at least two second electric actuators (79) and a second end (103) integral with one of said profile members (77) for transmitting rotational movement of said flexible transmission member (94) to said shaped member (77) .
    [9" id="c-fr-0009]
    9. Drone according to any one of claims 1 to 8, characterized in that each of said at least one movable portion (11) comprises an absorption system (24) for absorbing at least partially the kinetic energy of said drone (1). ) during his landing.
    [10" id="c-fr-0010]
    10. Drone according to any one of claims 1 to 9, characterized in that said at least three rotors (3-6) are formed at least by a left front rotor (3), a right front rotor (4), a left rear rotor (5) and a right rear rotor (6) with respect to the longitudinal direction of movement of said drone (1), said supporting structure (2) having an elongate shape in said longitudinal direction X, a longitudinal center distance L separating the rotational axes of the front rotors (3, 4) and the rotational axes of the rear rotors (5, 6) being greater than a transverse center distance T between the rotational axes of the left (3, 5) and straight rotors (4, 6). ) and in that said flange (9) is implanted on the supporting structure (2) in a median zone (16) of said supporting structure (2) in said longitudinal direction X.
    [11" id="c-fr-0011]
    11. Drone according to claim 10, characterized in that said rotors (3-6) are of the same diameter od and in that said longitudinal center distance L separating the axes of rotation of the front rotors (3, 4) and the axes of rotation rear rotors (5, 6) is greater than the sum of a diameter 0d of said rotors (3-6) and a rope C of the half-wing (10) measured near a connecting zone (15). ) of said half-wing (10) with said carrier structure (2).
    [12" id="c-fr-0012]
    12. Drone according to any one of claims 1 to 11, characterized in that each of said at least one movable portion (21) comprises at least one propulsion rotor (22) rotated by at least one electric propulsion motor ( 23) and in that said control system (7) is able to deliver an electric power supply of said at least one electric propulsion motor (23).
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    同族专利:
    公开号 | 公开日
    EP3239049A1|2017-11-01|
    US10526065B2|2020-01-07|
    CN107310713A|2017-11-03|
    CN107310713B|2020-02-14|
    EP3239049B1|2018-11-07|
    FR3050385B1|2018-04-06|
    US20170305526A1|2017-10-26|
    PL3239049T3|2019-04-30|
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    法律状态:
    2017-04-19| PLFP| Fee payment|Year of fee payment: 2 |
    2017-10-27| PLSC| Publication of the preliminary search report|Effective date: 20171027 |
    2018-04-20| PLFP| Fee payment|Year of fee payment: 3 |
    2019-04-18| PLFP| Fee payment|Year of fee payment: 4 |
    2020-04-20| PLFP| Fee payment|Year of fee payment: 5 |
    2021-04-23| PLFP| Fee payment|Year of fee payment: 6 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1600688A|FR3050385B1|2016-04-26|2016-04-26|DRONE COMPRISING AT LEAST THREE ROTORS OF SUSTENTATION AND PROPULSION|
    FR1600688|2016-04-26|FR1600688A| FR3050385B1|2016-04-26|2016-04-26|DRONE COMPRISING AT LEAST THREE ROTORS OF SUSTENTATION AND PROPULSION|
    PL17160896T| PL3239049T3|2016-04-26|2017-03-14|A drone having at least three lift and propulsion rotors|
    EP17160896.1A| EP3239049B1|2016-04-26|2017-03-14|A drone having at least three lift and propulsion rotors|
    CN201710193132.4A| CN107310713B|2016-04-26|2017-03-28|Unmanned aerial vehicle with at least three lifting and propulsion rotors|
    US15/497,387| US10526065B2|2016-04-26|2017-04-26|Drone having at least three lift and propulsion rotors|
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