Classifications

• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C27/00—Rotorcraft; Rotors peculiar thereto
  • B64C27/32—Rotors
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C27/00—Rotorcraft; Rotors peculiar thereto
  • B64C27/04—Helicopters
  • B64C27/08—Helicopters with two or more rotors
  • B64C27/10—Helicopters with two or more rotors arranged coaxially
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C27/00—Rotorcraft; Rotors peculiar thereto
  • B64C27/20—Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C27/00—Rotorcraft; Rotors peculiar thereto
  • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C27/00—Rotorcraft; Rotors peculiar thereto
  • B64C27/32—Rotors
  • B64C27/46—Blades
  • B64C27/467—Aerodynamic features
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
  • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
  • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
  • B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C39/00—Aircraft not otherwise provided for
  • B64C39/06—Aircraft not otherwise provided for having disc- or ring-shaped wings
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
  • B64U10/00—Type of UAV
  • B64U10/20—Vertical take-off and landing [VTOL] aircraft
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
  • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
  • B64U30/10—Wings
  • B64U30/12—Variable or detachable wings, e.g. wings with adjustable sweep
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
  • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
  • B64U30/20—Rotors; Rotor supports
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
  • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
  • B64U30/20—Rotors; Rotor supports
  • B64U30/26—Ducted or shrouded rotors
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
  • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
  • B64U30/20—Rotors; Rotor supports
  • B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
  • B64U50/00—Propulsion; Power supply
  • B64U50/10—Propulsion
  • B64U50/13—Propulsion using external fans or propellers
  • B64U50/14—Propulsion using external fans or propellers ducted or shrouded
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C27/00—Rotorcraft; Rotors peculiar thereto
  • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
  • B64C27/72—Means acting on blades
  • B64C2027/7205—Means acting on blades on each blade individually, e.g. individual blade control [IBC]
  • B64C2027/7261—Means acting on blades on each blade individually, e.g. individual blade control [IBC] with flaps
• • B—PERFORMING OPERATIONS; TRANSPORTING
  • B64—AIRCRAFT; AVIATION; COSMONAUTICS
  • B64C—AEROPLANES; HELICOPTERS
  • B64C27/00—Rotorcraft; Rotors peculiar thereto
  • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
  • B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
  • B64C2027/8281—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like comprising horizontal tail planes
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/30—Wing lift efficiency

Definitions

• the present invention relates to a wing in the field of aircraft, and more particularly a rotary wing in particular for drones, helicopters, and airplanes.
• Document US 7510 377 describes a rotor plane, comprising a pair of blades driven in rotation by the setting in rotation of a rotational central housing, comprising two portions linked together.
• Document EP 0 680 876 also discloses a faired anti-torque multi-blade rotor with floating blades, for rotary-wing aircraft, in particular helicopters.
• the rotary airfoil according to the invention seeks to resolve the problem of lift in horizontal displacement of known devices.
• the effective part of a rotor is therefore constituted by the end of its blades.
• the rotary airfoil according to the invention is characterized in that it comprises, at least, a central part consisting of an aerodynamic shape and of revolution with respect to an axis, blades arranged at the periphery of said central part and extending radially with respect to said axis, and a shaft coaxial with said axis and ensuring the rotational movement of the assembly consisting of said central part and said blades.
• the geometry of the blades is limited to their effective part, to allow the use of the central part which consists of an aerodynamic volume bearing during the horizontal movement of the aircraft.
• the central part has a lenticular shape, with a curvature of the upper part greater than that of the lower part, to respectively form an upper surface and a lower surface and the lenticular central part forms an aerodynamic volume wearing.
• the blades can be provided with flaps for
• the central part has a significant thickness in its center to allow the curvature of the upper surface, this creates a volume which can be used judiciously to place a motor within it, which can create the rotational movement.
• the central part is load-bearing in horizontal flight, this lift can be increased by the incidence of this central part.
• said blades may each be provided with a partially or fully retractable camber flap depending on the flight situations, to increase their efficiency.
• said central part has a generally triangular geometry, each of the vertices of which is extended by a blade, and, in each of the transition zones between a blade and said central part, its peripheral edge presents a generally curved profile.
• the rotary airfoil further comprises a peripheral hooping of the blades.
• the rotary airfoil can advantageously have the geometry of an axial turbine, the peripheral hooping and the blades extending the lenticular shape of said rotary airfoil, by having an internal shape capable of positively guiding the flow of air passing through it, and a peripheral outer shape capable of constituting the outer edge of the rotary airfoil in the form of a lens.
• the invention also relates to a double rotor comprising an upper rotary airfoil and a lower rotary airfoil associated with each other, said two rotary airfoils each comprising a central part on which are fixed the circled blades a peripheral hooping, the upper part of said double rotor being of greater curvature than that of its lower part in order to form an upper surface and an lower surface respectively, said double rotor being of lenticular shape.
• Said two rotary wings can preferably be associated with one another through a central support having an annular portion from which extends a plate, said annular portion being sandwiched between the two wings rotating, a drive shaft being integrally positioned substantially in the center of the annular portion, and being connected to motor means, for the rotation of said two rotary wings.
• the setting in horizontal speed can be induced by a means
• FIG.1 shows a schematic plan view of a first mode of
• FIG.2 shows a side view of the same rotary airfoil
• FIG.2 is a schematic perspective view of a low horizontal speed vehicle equipped with four rotary wings according to the first embodiment, as illustrated in Figures 1 and 2;
• FIG.4a] and FIG.4b] each represent a schematic perspective view of a medium horizontal speed vehicle each equipped with four rotary wings as illustrated in Figures 1 and 2, while Figure 4c shows a detail of Figure 4b;
• FIG.5a shows a schematic front view of a large vehicle
• FIG.5b] and FIG.5c] each show a detail of said vehicle according to a
• FIG.6a shows a schematic perspective view of a second particular embodiment of a rotary airfoil according to the invention, comprising blades equipped with camber flaps, while
• FIG.6b illustrates a sectional view of the rotary airfoil of Figure 6a, the central part of the rotary airfoil incorporating a motor; [0036] [Fig.6c] and [Fig.6d] illustrating a detail of the rotary wing of Figure 6a, namely a blade equipped with a camber flap, the latter being in the retracted position during take-off ([Fig.6d]) and in the deployed position in a flight situation ([Fig.6c]);
• FIG.7 schematically illustrates an aircraft equipped with three rotary wings according to the second embodiment of Figure 6a;
• FIG.8a], FIG.8b] and [Fig.8c] illustrate, schematically, various views of a third embodiment of the rotary airfoil of the invention, the central part of which has a globally triangular shape, the points of the triangle each converging towards a blade;
• FIG.9 shows, schematically and in perspective, a fourth embodiment of a rotary airfoil according to the invention.
• FIG.10 shows, schematically and in perspective, a fifth embodiment of a rotary airfoil according to the invention
• FIG.1 1 shows, schematically and in perspective, a sixth embodiment of a rotary airfoil according to the invention
• FIG.12a] and FIG.12b schematically illustrate, respectively, an exploded perspective view and a side view, of a seventh embodiment of a rotary airfoil according to the invention.
• Figures 1 and 2 can be seen a first embodiment, no
• This rotary airfoil 100 comprises a central part 1 of the shape
• Lenticular and generally circular having, visible in Figure 2, an upper face 10, or extrados, of greater curvature than that of its lower face 11, or intrados.
• the central part 1 is mounted at the end of a drive shaft 2, visible in Figure 2, of axis XX ’constituting the axis of revolution of the solid form formed by the central part 1.
• the central part 1 of the rotary airfoil 100 protrude radially from the axis XX ', the blades 3, the number of which is advantageously between three and ten depending on the design and the embodiment of said rotary airfoil.
• the central part 1 of the rotary airfoil 100 of the invention thus preferably has a significant thickness at its center to allow the curvature of the upper surface 10, thus creating a sufficient volume to be able to be used judiciously in order to positioning, within it, a motor M, illustrated in particular in FIG. 6b in the context of a second embodiment of the invention.
• This motor M is capable of creating the rotational movement of the rotary airfoil 100 of the invention through the drive shaft 2.
• the present invention also relates to an aircraft comprising at least one rotary wing 100 according to this first embodiment of the invention.
• the invention also relates to an aircraft at low horizontal speed 200, of the drone type, advantageously incorporating a plurality of such rotary wings 100 illustrated in the figures 1 and 2.
• said low horizontal speed aircraft 200 comprises four rotary wings 100, as well as, optionally, additional means for inducing horizontal speeding, such as at least one traction propeller 4 or a propeller.
• the rotary wings 100 of the invention here provide control over roll, yaw and angle of attack.
• the invention also relates to an aircraft at medium horizontal speed 201 a, 201 b comprising, preferably, several rotary wings 100 according to the invention, for example four rotary wings 100, as well that, advantageously, at least one traction propeller 41 a, 41 b, respectively, or a propulsion propeller, not shown.
• the rotary wings 100 control the roll and yaw while the incidence is adjusted by horizontal movement of said rotary wings 100 around the 'Y axis.
• the rotary wings 100 ensure control of the roll and the angle of attack is adjusted by movement of flaps 61, 62, 63, 64, in particular a flap fin 64 in a fin 6. It is also possible to consider integrating roll flaps 61, 62 and an incidence flap 63 in the horizontal plane of a tail 5.
• the present invention also relates to an aircraft at high horizontal speed, 202a, 202b, equipped with a fin 7.
• the high-speed aircraft As with the previous examples, the high-speed aircraft
• horizontal 202a, 202b advantageously comprises four rotary wings 100 according to the first embodiment of the present invention, two rotary wings 100 at the front and two rotary wings 100 at the rear.
• Flaps 81, 82, 83 are preferably integrated to control the roll, and the blades 3 can be retractable.
• Figures 6a to 6d illustrate a second embodiment
• this rotary airfoil 101 is similar to those of the rotary airfoil 100 described above, in particular with regard to the presence of a central part 1 of lenticular and generally circular shape at the periphery of which are positioned blades 3, while a shaft 2 makes it possible to drive said rotary airfoil 101 in rotation by the action of a motor M, visible in FIG. 6b.
• the blades 3 are provided with camber flaps 31, in order to increase the efficiency of said blades at different rotational speeds.
• camber flaps 31 are partially or totally retractable, and this depending on the flight situations.
• camber flap 31 of a blade 3 may be in
• Figure 7 shows an aircraft 203 equipped with a plurality of such rotary wings 101, in this case three rotary wings 101, as well
• the blades 3 of said rotary wings 101 each being provided with a camber flap 31.
• FIG. 8a A third embodiment of the rotary airfoil according to the invention is illustrated in Figures 8a to 8c.
• the rotary airfoil 102 has a particularly optimized shape, based on:
• the rotary airfoil 102 of FIGS. 8a to 8c has a lens of generally triangular shape, the points of the triangle of which each converge towards a blade 3 of said airfoil 102.
• the transition between the central lens 1 and the blades 3 is done continuously; in other words, the perimeter of the triangular central part 1 of the rotary airfoil 102 is extended, without interruption or discontinuities, at the points of the triangle towards three blades 3, in order to optimize the aerodynamic flows for all the use case.
• the blades 3 not provided with camber flaps are shown.
• the rotary airfoil 102 of substantially triangular shape comprises blades 3 similar to those of the rotary airfoil 101 and illustrated in FIGS. 6a to 6d, that is to say each provided with a camber flap 31.
• the fourth embodiment of the rotary airfoil 103 of the invention, illustrated in Figure 9, is of particular interest in predominantly vertical use, in a drone-type aircraft, where the lenticular central part 1 simply serves in pushing the blades 3 back to a diameter where they are really effective.
• the blade root 32 is integral with the central part 1
• the resistance of the central part 1 of the rotary airfoil 103, associated with the large perimeter of said central part 1, allows a multiplication of the blades on the periphery thereof, which correspondingly increases the lift of the rotary airfoil 103 thus constituted.
• the rotary airfoil 104 comprises a peripheral hoop 12 of the blades 3.
• this peripheral strapping 12 allows an increase in the
• said strapping 12 results in a limitation of the transverse flow between the lower surface and the upper surface of the blades 3, which resulted in a decrease in
• Figure 10 is shown a rotary airfoil similar to that of the fourth embodiment and illustrated in Figure 9, with the difference that the rotary airfoil 104 of FIG. 10 is completed by a peripheral hooping.
• the airfoils it is also conceivable that the airfoils
• turntables 100, 101, 102 of the first, second and third embodiments, respectively, are equipped with a peripheral strapping.
• peripheral 13 is used to extend the lenticular shape of the rotary airfoil 105, by having an internal shape capable of guiding
• peripheral rim 13, as well as the blades 3 participate in the lenticular shape and said blades 3 are integrated into the lens in the form of a rotor having the geometry of an axial turbine, particularly effective to generate the air flow necessary for the lift by rotation of the rotary airfoil 105, and whose general lenticular shape is suitable for allowing horizontal hovering flight.
• Said two rotary wings 106a and 106b are associated with one another through a central support 14 having an annular-shaped portion 141 from which extends a plate 142, said annular portion 141 being taken in. sandwich between the two rotary wings 106a and 106b.
• the plate 142 makes it possible to make the connection between the annular portion 141 and the structure of the aircraft which is capable of being fitted with the double rotor 106.
• a drive shaft 143 for the rotation, through motor means, of the upper 106a and lower 106b rotary airfoils.
• said motor means are capable of imposing reverse rotational movements on each of the two upper 106a and lower 106b rotary airfoils.
• the upper surface is of greater curvature than that of its lower surface, or lower surface, as is more particularly visible in the attached FIG. 12b.
• lower rotary 106b preferably each driven by an independent motor means, secures an aircraft equipped with double rotors 106, in the event of failure of one of the rotary wings 106a, 106b.
• the second non-defective rotary wing of the double rotor continues to operate.
• the peripheral straps 13a, 13b of the upper 106a and lower 106 rotary airfoils, as well as the shape of the support 14, makes it possible to materialize an overall lenticular shape to allow horizontal lift.
• the flow allowing the vertical lift is guided by a cylindrical pipe formed by the interior shapes of the peripheral straps 13a, 13b and of the support 14.
• the integration of the rotors or rotary wings of the invention on an aircraft advantageously makes it possible to combine the functions of a drone and those of an airplane, by allowing vertical take-off by the lift effect of the blades, then a setting in horizontal speed which makes it possible to give, through the central part 1 of said rotor, lift to the aircraft, or even a cancellation of the speed of rotation of the rotary airfoil so as not to use, at a certain horizontal speed , that the lift effect of said central part.
• the horizontal speed setting may optionally be induced by at least one additional means such as a propeller or traction propeller.

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• Engineering & Computer Science (AREA)
• Aviation & Aerospace Engineering (AREA)
• Mechanical Engineering (AREA)
• Chemical & Material Sciences (AREA)
• Combustion & Propulsion (AREA)
• Physics & Mathematics (AREA)
• Fluid Mechanics (AREA)
• Remote Sensing (AREA)
• Toys (AREA)

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• 2020
  • 2020-04-06 EP EP20715104.4A patent/EP3953252A1/de not_active Withdrawn
  • 2020-04-06 WO PCT/EP2020/059732 patent/WO2020207955A1/fr unknown

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