• 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 an aircraft (1) provided with a wing (10) and a winching device (20). The winching device (20) is provided with a lifting device (30) which comprises a storage drum and a motor member for winding a suspension member (40) around the storage drum (31) and unwinding said suspension member (40) outside the storage drum (31). The lifting device (30) is at least partially surrounded by a cowling (50) of this wing (10), said lifting device (30) being arranged in an inner volume (INT) of the wing (10) at least in one position called "aerodynamic position (POS1)".
    公开号:FR3051769A1
    申请号:FR1600842
    申请日:2016-05-25
    公开日:2017-12-01
    发明作者:Andre Barbieri
    申请人:Airbus Helicopters SAS；
    IPC主号:
    专利说明:

    Aircraft equipped with a winching device
    The present invention relates to an aircraft equipped with a winching device. The technical field of the invention is therefore the technical field of winching apparatus of an aircraft.
    Indeed, an aircraft and more particularly an aircraft that can fly at low speed can be equipped with a winching device for transporting external loads. As an illustration, a rotorcraft is sometimes equipped with such a winching device. A winching device may make it possible to hoist external loads in the aircraft, or it may make it possible to transfer external loads from the aircraft to the outside. The term "external load" applies not only to objects, but also to living things that can be carried by the winching device. A winching device is then used in particular for rescue missions or during commercial activities.
    Such a winching device may comprise a lifting device that can lower or mount a suspension member relative to the fuselage of the aircraft. Such a suspension member may comprise a suspension cable for example.
    Such a lifting device is commonly referred to as a "winch" by those skilled in the art. A lifting device conventionally comprises a motor rotating a storage drum around which is partially wound the suspension member. The term "partially wound" means that a portion of the hanger may be wrapped around the storage drum, with another portion of the hanger protruding from the elevator to be secured to an external load. The arrangement of a lifting device in an aircraft can pose difficulties.
    A lifting device can thus be arranged outside the fuselage of the aircraft, for example being carried by a sidewall of this aircraft. Optionally, the elevator device is carried by a movable beam.
    This type of arrangement can be however limiting because of the aerodynamic drag of the lifting device during the displacement of the aircraft.
    Alternatively, the elevator device can be arranged in the fuselage of the aircraft. The suspension member then winds in the fuselage to join the outside environment. The arrangement of the lifting device in the fuselage can, however, be difficult because of its size.
    EP 2 143 633 discloses a winching device and a recovery method of a rescue cradle
    This winching device includes a door movable in rotation supporting a lifting device. When the door is open, the lifting device is located outside the fuselage of an aircraft. Conversely, when the door is closed the elevator device is positioned in the fuselage.
    This system makes it possible to position the lifting device in the fuselage outside a recovery operation so as not to increase the aerodynamic drag of the aircraft. Nevertheless, the lifting device actually reduces the useful volume in the fuselage.
    US 2002/0020783 discloses a winching device. The winching device is provided with a removable lifting device and a fixed part arranged in a fuselage of fact at the expense of the useful volume.
    Document FR 2,966,802 describes a winching device. This winching device comprises a lifting device arranged in the fuselage of an aircraft and a guide beam of the suspension member of the lifting device.
    US 4,750,691 discloses a winching device. This winching device comprises a lifting device arranged in the fuselage of an aircraft and a guide beam. The guide beam is pivotable between an extended winching position and a retracted position.
    Such a guide beam may possibly obstruct access to a cabin in a retracted position.
    US 3,561,704 discloses a winching device of an aircraft. This winching device includes a door movable in rotation supporting a lifting device. The elevator device is slidable on a rail which extends partly on a ceiling of the fuselage and on the door.
    DE 3323513 discloses a winching device. This winching device includes a lifting device secured to a guide beam. The elevator device and the guide beam are movable in translation between a retracted arrangement position in a cab and an extended winching position.
    The document FR 1 577 830 describes a winching device. This winching device includes a lifting device. The lifting device is carried by a pivoting support, for pivoting between a retracted arrangement position in a cab and an extended winching position.
    FR 2 346 276 a winching device. This winching device includes a lifting device provided with a guide beam. The elevator device and the guide beam slide on a rail between a retracted position and an exit position.
    The document US 3,478,904 is far from the scope of the invention by describing a lift mechanism facilitating re-embarkation and landing in the cargo of an aircraft.
    The document FR 2,955,832 describes a removable support of a lifting device. In the mounting position, the removable support is disposed outside a fuselage at an access door inside this fuselage.
    GB 2,303,837 describes a winching device. This winching device includes a lifting device attached to the outside of a fuselage. In addition, the winching device comprises a removable baffle used to move the suspension cable of the lifting device of the landing gear of the aircraft. This deflector is either stored against a vertical skin of the fuselage of the aircraft, or slidably mounted under a floor of a cabin.
    US 4,566,659 discloses a winching device. This winching device includes a lifting device attached to the outside of a fuselage. The lifting device is mounted on a pivoting support which is fixed on a sidewall of the aircraft. The pivoting support makes it possible to move the lifting device to access an engine during its maintenance.
    US 2014/0090232 discloses a rotary system with screws for the angular inclination of a lifting device located outside a fuselage of the aircraft. This rotary system makes it possible to lower the lifting device to access the engine of the aircraft during its maintenance.
    GB 860,009 describes a lifting device fixed inside a door.
    US 5,190,250 discloses an elevator device integrated into a nacelle placed under a wing of a helicopter.
    The present invention therefore aims to provide a different winching device to avoid some of the aforementioned drawbacks. The invention therefore relates to an aircraft. This aircraft is provided with a wing extending longitudinally from an aerodynamic edge called "trailing edge" to an aerodynamic edge called "leading edge". This aircraft is provided with a winching device, this winching device being provided with a lifting device which comprises a storage drum. The winching device is also provided with a suspension member which extends from a first end to a second free end protruding from the lifting device, the lifting device comprising a driving member for winding the suspension member around the drum. storing and unrolling the suspension member outside the storage drum.
    The lifting device is at least partially surrounded by a cowling of this wing, the lifting device being arranged in an inner volume of the wing in a position called "aerodynamic position" reached by the lifting device and the cowling.
    The second end of the suspension member may be arranged outside the wing during winching operations, and in the wing in the absence of winching operation.
    Optionally, a hook attached to this second end may be permanently located at least partially outside the wing. Therefore, the suspension member can be tensioned in the absence of winching operation to prevent movement of the hook in flight, for example by blocking a stop of the hook against the wing or against the lifting device.
    The term "cowling" designates a wall in contact with a medium outside the aircraft. The expression "a motor member for winding said suspension member around the storage drum and unrolling said suspension member outside the storage drum" means that the motor member acts either on the suspension member or on the drum storage or alternatively on another member of the elevator device to be able to wind / unwind the suspension member around the storage drum. The motor member therefore comprises for this purpose at least one motor, such as an electric motor for example.
    Furthermore, the suspension member may comprise at least one cable and / or at least one chain for example. This suspension member is further partially wound around the storage drum, at least when the suspension member is not fully unrolled outside the storage drum.
    The lifting device can then be of a known type, comprising at least one motor and at least one storage drum. For example, the elevator device may be of the type known under the trade name Goodrich 44312.
    This lifting device is integrated in a wing being arranged in the wing, at least when the lifting device is in a position called "aerodynamic position". In this aerodynamic position, the cowling partially delimits the interior volume accommodating the lifting device. Optionally, the elevator device may be disposed outside the interior volume when the elevator device is in another position. Therefore, the lifting device is arranged within the wing itself at least during certain flight phase, and not in a nacelle fixed under the wing. Therefore, the elevator device is also distinguished from the devices arranged in a cabin and tending to restrict the useful volume of the cabin or to partially obstruct an access door of this cabin. The arrangement outside the cabin also tends to avoid the projection of lubricant for example in this cabin.
    In addition, by integrating the elevator device into the wing in its aerodynamic position, the aerodynamic drag of the winching device is optimized. This characteristic justifies the use of the expression "aerodynamic position" qualifying the position reached by the elevator device in this configuration.
    In addition, the cowling is a constituent element of the wing. As a result, the cowling serves as a means of protection of the lifting device and coating of the wing.
    Moreover, the second end of the suspension member always protrudes from the wing, at least during winching operations. This second end can be connected to a device for fixing a load, such as a hook for example. Thus, the winching device can carry for example an individual, a stretcher via pants or a device able to cross the foliage of trees in a forest. Such a device able to cross the foliage of trees is sometimes called "jungle penetrator" in English. The aircraft may further include one or more of the following features.
    Thus, according to one embodiment, the lifting device is arranged in one of the aerodynamic edges of the wing, the cowling being a part of the aerodynamic edge containing the lifting device.
    According to this first embodiment the lifting device is integrated in the leading edge or in the trailing edge of the wing. The cowling then represents part of a leading edge fairing or a trailing edge fairing.
    In addition, the wing may carry a propeller disposed longitudinally on one side of one of the aerodynamic edges. Therefore, the elevator device can be arranged in the other aerodynamic edge.
    For example, the propeller is carried by a mast protruding from the leading edge. Therefore, according to this alternative, the elevator device can be disposed in a cowling of the trailing edge. Conversely, if the propeller is carried by a mast projecting from the trailing edge, the lifting device can be arranged in a hood of the leading edge.
    This alternative aims to limit the risk of interference between a propeller and a hoisted load by the winching device.
    In addition, when the lifting device is disposed in an aerodynamic edge, the lifting device can extend mainly along a span of the wing in its aerodynamic position.
    The term "primarily" means that the largest dimension of the elevator device extends substantially in the associated direction.
    Furthermore, the aerodynamic edge containing the lifting device may comprise successively a root section, said cowling and an end section.
    The aerodynamic edge of the wing cooperating with the elevator device may thus comprise a root section, which does not belong to the hood of the winching device, to move the lifting device away from the fuselage. For example, this root section extends in span over a length of the order of 50 centimeters. Following the root section, the aerodynamic edge has the cowling. This cowling can be arranged in the continuity of the root section in the aerodynamic position, an outer surface of the cowling flush with an outer surface of the root section. For example, this cowling extends in span over a length of the order of one meter so that in forward flight the elevator device does not disturb the aerodynamic flow of air around the wing.
    Finally, following the rollover, the aerodynamic edge has the end portion. This end section may be arranged in the continuity of the cowling in the aerodynamic position, an outer surface of the cowling flush with an outer surface of the end section. In this position, the root section and the cowling and the end section together form a substantially continuous surface.
    According to a second embodiment, the cowling is a fairing said "karman fairing" of the wing.
    Such a karman fairing is usually used to prevent the formation of a swirling flow.
    For example, an aerodynamic edge and in particular a trailing edge may have insufficient thickness between its upper surface and its lower surface to accommodate the lifting device within it.
    This second embodiment proposes in particular to remedy this difficulty by arranging the lifting device in a karman fairing to ensure the aerodynamic continuity of the wing without deforming an aerodynamic edge.
    The karman fairing can have a thickness of the order of the maximum thickness of the wing, for example.
    According to this second embodiment, the lifting device may further extend mainly longitudinally in its aerodynamic position.
    In another aspect, the suspension member can pass through the cowling. The suspension member can thus extend outside the aircraft.
    In another aspect, the winching device may comprise a mobile arm carried by a hinge, the hinge conferring on the mobile arm at least one degree of freedom in rotation about an axis of rotation relative to the wing, the device elevator being carried by the movable arm, the movable arm and the cowling being jointly movable between the aerodynamic position and a position called "offset position".
    The term "articulation" designates a mechanical system provided with a stationary member with respect to the wing and the fuselage, this mechanical system conferring a degree of freedom in rotation between two elements.
    For example, the hinge includes a male yoke attached to the wing or fuselage, and a pin passing through the male yoke and a female yoke of the movable arm.
    The cowling can be attached to the elevator device and / or the movable arm using conventional mechanical connections, such as brackets for example.
    The movable arm and the lifting device and the cowling can then be jointly moved at least in rotation about the axis of rotation. This axis of rotation may be an axis extending in elevation namely substantially in a direction from the lower surface to the upper surface of the wing. Therefore, the elevator device can be moved to facilitate the operation of this elevator device, or to facilitate the loading of a load for example. In the remote position, the elevator device is for example closer to a cabin than in the aerodynamic position.
    According to another arrangement, in the aerodynamic position, the lifting device is for example closer to a cabin than in the remote position. For example, an individual is hoisted to the aircraft during an emergency mission, positioning the device elevator in the remote position. When the individual arrives at the level of the aircraft, the lifting device is positioned in the aerodynamic position to facilitate its boarding in the aircraft.
    Moreover, the cowling can close the interior volume in the aerodynamic position, the cowling opening the interior volume on a medium outside the aircraft in the remote position.
    The term "close" means that the hood then delimits the interior volume. The cowling comprises for this purpose an outer surface flush with an adjacent outer surface of the wing.
    In another aspect, the winching device may comprise a motorized system connected to the movable arm for moving in rotation the movable arm about the axis of rotation.
    The motorized system may comprise a motor, for example electric, or a jack capable of exerting a force on the movable arm to move it.
    In another aspect, the aircraft having a fuselage provided with at least one frame and a coating that is attached to the frame, the joint can be attached to the frame. The joint is installed on a frame of the fuselage, for example a frame located near a side door. A motionless organ of the joint is favorably installed at the junction of the frame of this door and a frame connected to a wing.
    A door frame requires a structural frame. The implantation of the wing also requires a structural frame. An immobile organ of the joint can then be located at the junction of these frames which represents a zone of fact reinforced structurally. The arrangement of the invention does not then require the addition of reinforcements that have a significant mass impact.
    According to another alternative, a stationary member of the joint is for example integral with a floor or a ceiling of the aircraft. In particular, a stationary member of the joint may be integral with the mechanical floor of the aircraft carrying the power plant of this aircraft.
    According to another alternative, the joint is attached to an element of the wing.
    An immovable member of the hinge may be attached to the fuselage, but may alternatively be fixed in the wing being for example fixed to a spar or a rib of the wing.
    According to another aspect, the root section comprises, where appropriate, at least one movable flap and a mobility system, the mobility system cooperating with the flap to move the flap between a closed position and an open position, the flap hindering the moving the movable arm in the closed position and not hindering said displacement in the open position.
    If there is a root section and a movable arm, the root section can be opened by moving at least one flap. The aerodynamic edge is cut in two-part elevation to present a notch in the open position so as not to hinder the movement of the movable arm.
    This system is all the more interesting if the movable arm crosses the root section to be articulated to a joint integral with the fuselage of the aircraft.
    Under the action of the movable arm, a lever is for example moved to allow vertical rotation of a flap. An engine or cylinder can also be used to move a flap.
    In another aspect, the wing may comprise at least one deflector to deflect a flow of air capable of impacting the winching device.
    A deflector may for example be added in front of a hook attached to the second end of the suspension member with respect to the direction of movement towards the front of the aircraft.
    In another aspect, the aircraft may be an aircraft capable of hovering.
    The lifting device may in particular be positioned under the center of thrust of the wing to optimize the centering of this aircraft. The aircraft may be a vertical take-off and landing aircraft, and / or an aircraft capable of remaining in a stationary position in flight. The aircraft may especially be a rotorcraft, and in particular a helicopter, for example. The aircraft can also be a drone-type unmanned aircraft. The arrangement of a lifting device in a wing of a drone makes it possible to optimize the useful volume of the fuselage of the drone, for example to arrange various equipment such as camera, battery, tank, etc.
    In another aspect, several winching devices according to the invention may be arranged in a wing, discontinuous or continuous, or in several wings.
    For example, a wing has two half-wings arranged transversely on either side of the fuselage, each half-wing comprising such a winching device. 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 front view of an aircraft according to FIG. FIG. 2 is a diagrammatic view showing a lifting device and a cowling; FIG. 3 is a side view of an aircraft according to the invention; FIG. 4 is a diagrammatic view showing a winching device arranged in a FIG. 5 is a diagrammatic view showing a winching device arranged in a karman fairing. - Figure 6, a view explaining the movement of a movable arm, - Figures 7 to 9, views having a winching device provided with a movable lifting device disposed in a karman fairing.
    The elements present in several separate figures are assigned a single reference.
    Note that three directions X, Y and Z orthogonal to each other are shown in some figures.
    The first direction X is called longitudinal. The terms "longitudinally" and "longitudinal" relate to any direction parallel to the first direction X
    The second direction Y is called transverse. The term "transverse" is relative to any direction parallel to the second direction Y.
    Finally, the third direction Z is said in elevation. The expression "in elevation" relates to any direction parallel to the third direction Z.
    Figure 1 shows an aircraft 1 according to the invention.
    This aircraft 1 can be an aircraft that can fly at low speed, or even stationary. In particular, the aircraft 1 may be an aircraft capable of performing a vertical takeoff or landing, or even a flight in a stationary position. Therefore, the aircraft 1 may be a rotorcraft provided at least during certain flight phases of a rotary wing. The aircraft 1 may comprise a cockpit, but may also be an unmanned drone.
    This aircraft 1 is provided with a fuselage 2 and at least one wing 10. Conventionally, the fuselage 2 comprises in particular structural frames not visible in Figure 1 and an outer coating 3. The wing 10 extends laterally at least one side of the fuselage 2. The wing 10 therefore comprises at least one aerodynamic section which typically extends in wingspan of the fuselage towards a free end. In addition, the wing 10 extends longitudinally from the rear to the front of an aerodynamic edge called "trailing edge 11" to an aerodynamic edge called "leading edge 12". The wing extends more in thickness from a lower surface 13 to an upper surface 14. The wing 10 comprises an outer covering and structural members disposed inside this coating. Thus, the wing comprises at least one spar, even ribs, stiffeners, filling means ....
    In addition, the aircraft 1 is provided with a winching device 20 for carrying a load.
    With reference to FIG. 2, the winching device 20 comprises a lifting device 30 carrying a suspension member 40.
    The lifting device 30 is integrated in the wing in the aerodynamic position POS1 illustrated in FIG. 2. Therefore, the lifting device is positioned in this aerodynamic position POS1 within an internal volume INT of the wing. This internal volume INT is delimited at least by a cowling 50. This cowling 50 forms part of the outer coating of the wing in the aerodynamic position POS1, and at least partially surrounds the elevator device 30.
    Referring to Figure 2, the elevator device 30 comprises at least one storage drum 31, at least one motor member 32 and a suspension member 40 can be partially surrounded around the storage drum. The suspension member 40 is an elongated member capable of carrying a load. This suspension member 40 extends from a first end 41 to a second end 42. For example, the first end 41 is fixed to the storage drum 31. On the contrary, the second end 42 protrudes from the lifting device 30 and of the wing. This second end 42 may comprise a fastening system 43, such as a hook for example. The drive member 32 then has the function of winding the suspension member, upstream of its second end, around the storage drum 31 to reduce on request the length of the suspension member 40 extending outside of the wing 10. In addition, the motor member 32 has the function of unwinding the suspension member outside the storage drum 31 to increase the length of the suspension member 40 extending outside the wing 10 on request. For this purpose, the motor member 32 comprises for example a motor adapted to rotate the storage drum 31 in a first direction to wind the suspension member 40, and in a second direction to unwind the suspension member 40 This motor member 32 may be controlled by conventional control means, such as a remote winching handle in a cabin of the fuselage for example.
    Furthermore, the lifting device 30 may comprise an outer casing 35. Such an outer casing 35 may comprise a main casing 36 in which the storage drum 31 and the motor member 32 are arranged. In addition, the outer casing may comprise a casing 30. perch 37 which is for example bent and secured to the main casing 36. The perch 37 is traversed by the suspension member 40. This suspension member 40 then leaves the pole to join the outer EXT medium to the wing, possibly in through an opening of the cowling 50.
    For example, the lifting device is a Goodrich type 44312 return winch.
    The shroud 50 may optionally be attached to the lifting device 30. For example, fastening tabs 38 mechanically fix the lifting device to a wall of the shroud 50.
    In another aspect, at least one deflector 85 is fixed to the wing 10 to deflect a flow of air capable of impacting the winching device, and for example a hook carried by the second end 42 of the suspension member . The deflector 85 may comprise at least one plate capable of deflecting such a flow of air, this plate being secured to the wing.
    Referring to Figure 3, the elevator device 30 may be arranged in one of the aerodynamic edges 11, 12 of the wing 10. The aerodynamic edge containing the lifting device is called for convenience "aerodynamic winching edge". Therefore, the cowling 50 represents part of the coating of this aerodynamic winching edge.
    The cowling may in particular represent a root portion of this aerodynamic winching edge to be disposed closer to the fuselage.
    According to another alternative, the cowling is not attached to the fuselage. Therefore, the aerodynamic winching edge comprises successively from the fuselage, a root section 81, the cowling 50 and an end section 82.
    Whatever the alternative and according to Figure 3, the winching device 20 may be arranged in the leading edge 12 of the wing.
    According to Figure 4, the winching device 20 may be arranged in the trailing edge 11 of the wing.
    The positioning choice of the winching device 20 in the trailing edge 11 or the leading edge 12 of the wing may depend on the thickness of the trailing edge 11 and the thickness of the leading edge 12, or still the position of the wing relative to a lateral access door of the aircraft.
    Similarly, the aircraft 1 may optionally comprise at least one propeller 90 carried by the wing 10. This propeller 90 is disposed longitudinally on one side of the wing 10, namely on the side of the trailing edge 11 or edge 12 of the wing according to Figure 4. The propeller is arranged in particular on the side of a given aerodynamic edge when the propeller 90 protrudes longitudinally from the given aerodynamic edge and / or when the shaft 91 rotating this propeller 1 protrudes longitudinally from this given aerodynamic edge. Therefore, the winching device 20 can be arranged on the aerodynamic edge which is arranged on the side of the propeller 90.
    According to the example of FIG. 4, the propeller 90 is therefore on the leading edge 12 side while the winching device 20 is disposed in the trailing edge 11.
    In another aspect, when the lifting device 30 is arranged in one of the aerodynamic edges of the wing 10, the lifting device 30 possibly extends mainly along the span of the wing 10.
    According to FIG. 5, the cowling 50 can take the form of a karman fairing 51 of the wing 10.
    For example, if the trailing edge has a reduced thickness, the wing can be provided with a karman fairing 51 accommodating the winching device.
    The elevator device 30 can then extend mainly longitudinally parallel to the longitudinal direction X, and no longer according to the wingspan.
    Whether the winching device is arranged in a karman fairing or in an aerodynamic edge of the wing, the cowling 50 and the lifting device 30 can be fixed in the mounting position, ie outside of maintenance operations. As a result, the elevator device is always in the aerodynamic position.
    However, the cowling 50 and the elevator device 30 may be movable in the mounting position to optimally position the winching device relative to the fuselage during the winching operation.
    FIG. 6 illustrates such a mobile winching device arranged in an aerodynamic edge, and in particular in the leading edge of the wing 10.
    Regardless of the arrangement of the winching device 20, the winching device 20 may then comprise a movable arm 60.
    The movable arm is articulated to the wing 10 or the fuselage 2 by a hinge 65. This hinge 65 allows a movement of the movable arm 60 relative to the wing 10 and the fuselage 2 at least about an axis of rotation AXROT . This axis of rotation AXROT extends mainly in elevation Z so that the winching device rotates in a possibly substantially horizontal plane in the aircraft reference system. The axis of rotation AXROT is for example substantially parallel to the axis of rotation of a lift rotor on a rotorcraft, and substantially parallel to the section of the projecting suspension member of the wing 10 in hovering and without wind .
    In the example of Figure 6, the hinge 65 is fixed to a frame 4 of the fuselage surrounding a lateral access to the inside of the fuselage. In particular, this hinge 65 comprises a yoke 66 attached to the fuselage 2, a yoke 67 integral with the movable arm 60 and at least one pin 68 passing through said yokes.
    For example, the hinge 65 comprises a male yoke 66 attached to a frame of the fuselage 2. A female yoke 67 is integral with the movable arm 60, the female yoke 67 comprising two cheeks arranged on either side of the male yoke. A spindle 68 passes successively through a first cheek of the female clevis, the male clevis then the second cheek of the female clevis.
    According to another variant not shown, the hinge comprises a member attached not to the fuselage but to a member of the wing, for example but not exclusively to the beam 16 visible in FIG.
    Whatever the variant, the lifting device 30 and the cowling 50 are integral in rotation with the movable arm about the axis of rotation AXROT. For example, the elevator device 30 and / or the cowling 50 are carried by the movable arm 60 by being fixed to this mobile arm by conventional fixing means.
    The movable arm 60 and the cowling 50 are thus jointly movable between the aerodynamic position POS1 and a position called "remote position".
    In the aerodynamic position POS1, the cowling 50 closes the internal volume INT. The wing then has a usual appearance since the lifting device is hidden inside the wing. Only the hook attached to the second end 42 of the suspension member projecting from the wing suggests the presence of such a lifting device.
    On the other hand, the cowling 50 opens the internal volume INT on the external medium EXT outside the aircraft 1 in the offset position POS2 illustrated in FIG.
    To move the movable arm 60, the winching device 20 may comprise a motorized system 70 for example connected to the movable arm 60. The motorized system then comprises a motor and a control member controlling the motor to move the movable arm 60 in rotation around AXROT axis of rotation.
    For example, the motor is fixed on the one hand to the movable arm 60 and, on the other hand, to a member of the wing or to the hinge 65 or to the fuselage.
    When the winching device is attached to an aerodynamic edge provided with a root portion 81, this root portion 81 may comprise at least one flap 83 movable relative to the other elements of the wing. According to the example shown in Figure 6, the root portion 81 may comprise two flaps 83 opening in "oyster".
    A mobility system is connected to at least one flap 83 to move this flap between a closed position POS3 and an open position POS4 visible in FIG. 6. This mobility system can comprise a motor 84, or a mechanical chain connected to the arm mobile for example.
    Indeed, when the movable arm is attached to the fuselage, the rotation of the movable arm can be hindered by a coating of the root section. Therefore, this optional feature allows to position the flap 83 in a closed position POS3 hindering the movement of the movable arm 60 when the movable arm is in the aerodynamic position POS1. The wing 10 is then in a configuration equivalent to the configuration of Figure 3. The flap 83 and the cowling together form a continuous coating of the aerodynamic edge.
    By cons, when the movable arm is rotated, each flap opens to reach the open position POS4 to not hinder the rotation of the movable arm.
    For example, each flap 83 and the movable arm 60 are respectively in the closed position POS3 and in the aerodynamic position POS1 outside the winching operations. The wing is then perfectly aerodynamic.
    During winching, the flap 83 and the movable arm 60 are for example respectively in the closed position POS3 and in the aerodynamic position POS1 when a load is mounted to the aircraft or lowered to the ground. On the other hand, the flap 83 and the movable arm 60 are positioned in the open position POS4 and in the offset position POS2 to bring the load closer to the fuselage during a loading operation of the load in the aircraft or of unloading the load. of the aircraft.
    Figures 7 to 9 illustrate a movable winching device disposed in a karman fairing.
    In particular, Figure 7 shows the elevator device 30 and the movable arm 60. The cowling has been removed to allow the clear display of the elevator device 30.
    In this configuration, the hinge 65 may for example be attached to a mechanical floor of the fuselage. For example, the hinge 65 comprises a rod 69 connected to the mechanical floor 200. As a result, the movable arm 60 comprises a male yoke disposed around the rod 69.
    According to FIG. 8, the fuselage 2 may comprise a fixed hood 75 attached to the cowling 50 in the aerodynamic position.
    In the aerodynamic POS1 position, the cowling 50 does not cover the fixed hood 75.
    Referring to Figure 9, when the cowling 50 and the movable arm 60 and the elevator device 30 rotate ROT to reach the offset position POS2, the rollover slides on the skin of the fixed hood 75, and partially covers the fixed hood 75.
    During winching, the cowling 50 as well as the movable arm 60 and the lifting device 30 are for example in the offset POS2 position of Figure 9 when a load is mounted to the aircraft or down to the ground. On the other hand, the cowling 50 as well as the mobile arm 60 and the lifting device 30 are positioned in the aerodynamic position POS1 of FIG. 8 to bring the load closer to the fuselage during a loading operation of the load in the aircraft or of landing. the load off the aircraft.
    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 (16)
    [1" id="c-fr-0001]
    1. Aircraft (1) provided with a wing (10) extending longitudinally from an aerodynamic edge called "trailing edge (11)" towards an aerodynamic edge known as "leading edge (12)", said aircraft being provided with a winching device (20), said winching device (20) being provided with a lifting device (30) having a storage drum (31), said winching device (20) being provided with a suspension member (40) extending from a first end to a second free end protruding from said lifting device (30), said lifting device (30) having a driving member (32) for winding said suspension member (40) around the storage drum (31) and unrolling said suspension member (40) out of the storage drum (31). characterized in that said lifting device (30) is at least partially surrounded by a cowling (50) of said wing (10), said lifting device (30) being arranged in an inner volume (INT) of the wing (10) in a position called "aerodynamic position (POS1)".
    [2" id="c-fr-0002]
    2. Aircraft according to claim 1, characterized in that said cowling (50) is a karman fairing (51) of said wing (10).
    [3" id="c-fr-0003]
    3. Aircraft according to claim 2, characterized in that said lifting device (30) extends mainly longitudinally (X) in its aerodynamic position.
    [4" id="c-fr-0004]
    4. Aircraft according to claim 1, characterized in that said elevator device (30) being arranged in one of said aerodynamic edges of the wing (10), said cowling (50) is a part of the aerodynamic edge containing said elevator device (30). ).
    [5" id="c-fr-0005]
    5. Aircraft according to claim 4, characterized in that said wing (10) carrying a propeller (90) disposed longitudinally on one side of one of said aerodynamic edges (12), said lifting device (30) is arranged in the other aerodynamic edge (11).
    [6" id="c-fr-0006]
    6. Aircraft according to any one of claims 4 to 5, characterized in that said lifting device (30) extends mainly along a span of the wing (10) in its aerodynamic position.
    [7" id="c-fr-0007]
    7. Aircraft according to any one of claims 4 to 6, characterized in that said aerodynamic edge containing said lifting device (30) comprises successively a root section (81), said cowling (50) and an end section (82).
    [8" id="c-fr-0008]
    8. Aircraft according to any one of claims 1 to 7, characterized in that said suspension member (40) passes through said cowling (50).
    [9" id="c-fr-0009]
    9. Aircraft according to any one of claims 1 to 8, characterized in that said winching device (20) comprises a movable arm (60) carried by a hinge (65), said hinge (65) imparting to the movable arm ( 60) at least one degree of freedom in rotation about an axis of rotation (AXROT) relative to the wing (10), said lifting device (30) being carried by said movable arm (60), said movable arm ( 60) and said cowling (50) being jointly movable between the aerodynamic position (POS1) and a position called "remote position (POS2)".
    [10" id="c-fr-0010]
    10. Aircraft according to claim 9, characterized in that said cowling (50) closes the inner volume (INT) in said aerodynamic position (POS1), said cowling (50) opening the inner volume (INT) on a medium (EXT) outside the aircraft (1) in the remote position (POS2).
    [11" id="c-fr-0011]
    11. Aircraft according to any one of claims 9 to 10, characterized in that said winching device (20) comprises a motorized system (70) connected to the movable arm (60) for moving in rotation said movable arm (60) around of the axis of rotation (AXROT).
    [12" id="c-fr-0012]
    12. Aircraft according to any one of claims 9 to 11, characterized in that said aircraft (1) comprising a fuselage (2) provided with at least one frame (4) and a coating (3) attached to the frame (4), said hinge (65) is fixed to the frame (4).
    [13" id="c-fr-0013]
    13. Aircraft according to any one of claims 9 to 11. characterized in that said hinge (65) is attached to a member (16) of said wing.
    [14" id="c-fr-0014]
    14. Aircraft according to claim 7 and any one of claims 9 to 13, characterized in that said root section (81) comprises at least one movable flap (83) and a mobility system (84), said system movable (84) cooperating with said flap (83) to move the flap between a closed position (POS3) and an open position (POS4), said flap (83) hindering the movement of the movable arm (60) in the closed position ( POS3) and does not interfere with said displacement in the open position (POS4).
    [15" id="c-fr-0015]
    15. Aircraft according to any one of claims 1 to 14, characterized in that said flange (10) comprises at least one deflector (85) for deflecting a flow of air capable of impacting the winching device.
    [16" id="c-fr-0016]
    16. Aircraft according to any one of claims 1 to 15. characterized in that said aircraft (1) is an aircraft capable of hovering.
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    BE384123A|
    同族专利:
    公开号 | 公开日
    EP3248871A1|2017-11-29|
    FR3051769B1|2019-07-19|
    US10479502B2|2019-11-19|
    US20170341748A1|2017-11-30|
    EP3248871B1|2018-08-01|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    GB297156A|1927-06-20|1928-09-20|Supermarine Aviat Works Ltd|Improvements in or relating to load carrying devices on aircraft|
    US2380290A|1941-09-06|1945-07-10|V J Burnelli Airplanes Inc|Cargo carrying airplane|
    GB755965A|1953-11-19|1956-08-29|Fairey Aviat Co Ltd|Improvements relating to rotary wing aircraft|
    US3204890A|1963-12-05|1965-09-07|John R Lehn|Helicopter and towed vehicle therefor|
    DE3323513A1|1983-06-30|1985-01-10|Licentia Patent-Verwaltungs-Gmbh, 6000 Frankfurt|Winch for aircraft|
    US4750691A|1987-06-08|1988-06-14|Kaman Aerospace Corporation|Retractable aircraft hoist|
    US5190250A|1991-09-04|1993-03-02|United Technologies Corporation|Autonomous, heliborne-mobile construction/emergency pod system|
    US20160340038A1|2015-03-26|2016-11-24|Bell Helicopter Textron Inc.|Integrated aircraft hoist|
    GB860009A|1958-08-22|1961-02-01|Charles Thomas Dennehy Hosegoo|Device for embarking and landing from hovering aircraft|
    US3478904A|1967-05-17|1969-11-18|Boeing Co|Cargo loading mechanism|
    US3561704A|1967-07-14|1971-02-09|Carsten Schulze|Arrangement of the openings to loading compartments in vertical take off and landing air vehicles|
    GB1233364A|1967-09-01|1971-05-26|
    US3494595A|1968-06-26|1970-02-10|United Aircraft Corp|Cable-to-hoist drum attachment mechanism|
    US4013270A|1976-03-29|1977-03-22|Breeze Corporations, Inc.|Combined winch and boom assembly|
    US4566659A|1984-10-18|1986-01-28|The United States Of America As Represented By The Secretary Of The Navy|Pivotable support rescue hoist|
    GB2303837A|1995-08-02|1997-03-05|Kenneth George Barnes|Winch cable deflector|
    US6334590B1|1999-04-09|2002-01-01|Bell Helicopter Textron Inc.|Removable hoist for aircraft|
    EP2143633B1|2008-07-10|2010-12-01|Agusta S.p.A.|Aircraft and method of retrieving a rescue cradle into the aircraft fuselage|
    FR2955832B1|2010-01-29|2012-03-30|Eurocopter France|REMOVABLE SUPPORT FOR AN EXTERNAL OPTIONAL EQUIPMENT OF AN AIRCRAFT AND AN AIRCRAFT PROVIDED WITH SUCH A SUPPORT|
    US8590841B1|2010-02-23|2013-11-26|WestWind Technologies, Inc.|Hoisting systems and methods|
    FR2966802A1|2010-10-27|2012-05-04|Eurocopter France|AIRCRAFT PROVIDED WITH A MEANS OF HELITREUILLAGE, AND ASSOCIATED METHOD.|US10549854B2|2015-03-26|2020-02-04|Bell Helicopter Textron Inc.|Integrated aircraft hoist|
    EP3650341B1|2018-11-07|2021-03-24|AIRBUS HELICOPTERS DEUTSCHLAND GmbH|A compound helicopter with a fixed wing arrangement|
    US20220048621A1|2019-11-15|2022-02-17|Rakuten Group Inc.|Unmanned aircraft system, control device and control method|
    法律状态:
    2017-05-23| PLFP| Fee payment|Year of fee payment: 2 |
    2017-12-01| PLSC| Publication of the preliminary search report|Effective date: 20171201 |
    2018-05-22| PLFP| Fee payment|Year of fee payment: 3 |
    2019-05-23| PLFP| Fee payment|Year of fee payment: 4 |
    2021-02-12| ST| Notification of lapse|Effective date: 20210105 |
    优先权:
    申请号 | 申请日 | 专利标题
    FR1600842A|FR3051769B1|2016-05-25|2016-05-25|AIRCRAFT PROVIDED WITH A WINCHING DEVICE|
    FR1600842|2016-05-25|FR1600842A| FR3051769B1|2016-05-25|2016-05-25|AIRCRAFT PROVIDED WITH A WINCHING DEVICE|
    EP17171246.6A| EP3248871B1|2016-05-25|2017-05-16|An aircraft provided with a winch device|
    US15/603,909| US10479502B2|2016-05-25|2017-05-24|Aircraft provided with a winch device|
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