WO2019197733A1

WO2019197733A1 - Flying craft having a rotary wing comprising an orientation system integrated into a fairing and method for controlling said flying craft

Info

Publication number: WO2019197733A1
Application number: PCT/FR2018/050893
Authority: WO
Inventors: Jad Rouhana; Bachir Rouhana
Original assignee: Jad Rouhana; Bachir Rouhana
Priority date: 2018-04-10
Filing date: 2018-04-10
Publication date: 2019-10-17

Abstract

The invention concerns a flying craft having a rotary wing comprising: at least one rotor (12) equipped with blades (16) and configured to pivot about an axis of rotation (A12), a stator (14) comprising a tubular pipe (15) coaxial to the axis of rotation (A12) and in which the rotor or rotors (12, 12') are positioned, and an orientation system (80) that comprises several radial wing members (70), arranged inside the pipe (15), which divide the pipe (15) into several sectors that each have a passage cross section, each wing member (70) comprising at least one pivoting portion (74) configured to pivot about a radial pivot axis in such a way as to be able to reduce the passage cross section of one of the two sectors adjacent to the wing member (70).

Description

ROTARY FLYWHEEL ENGINE COMPRISING AN INTEGRATED ORIENTATION SYSTEM IN A FITTING AND METHOD OF CONTROLLING SAID STEERING ENGINE

The present application relates to a flying vehicle with a rotating car comprising an orientation system integrated in a fairing and a method of driving said flying machine.

For the present application, helicopter means a rotary wing aircraft which comprises at least one rotor equipped with blades and rotated about a substantially vertical axis of rotation by a motor to ensure the lift of the aircraft. The term helicopter encompasses both large aircraft intended for example for the transport of passengers or freight as drones or mini-drones.

In order not to turn on itself, according to a first embodiment, a helicopter comprises a main rotor with a vertical axis of rotation and an anti-torque rotor.

According to a second embodiment, it comprises two coaxial main rotors rotating in opposite directions. In this case, all the energy produced by the engine is intended for the lift of the aircraft, which contributes to improving the fuel efficiency of the helicopter.

Whatever the embodiment, the helicopter has certain disadvantages.

According to a first drawback, the slightest impact on the rotating blades has the effect of damaging them and causing loss of control of the helicopter. In addition, in the case of drones, the high-speed rotation of the blades presents a risk of danger to people in the event of a fall of the aircraft. To overcome this drawback, EP-661.206 proposes to position the rotor inside a tube-shaped fairing coaxial with the axis of rotation of the rotor. To direct it, the flying machine described in this document comprises a plurality of adjustable flaps, positioned at the outlet of the fairing, which make it possible to modify the orientation of the jet leaving the fairing. According to this embodiment, there are still moving elements, namely the flaps, outside the fairing. According to another disadvantage, when the rotor rotates, the ends of the blades rise above the horizontal and the blades form a cone, which tends to reduce the lift due to the reduction of the effective surface of the disc formed by the rotation of the blades.

To limit the deformation of the blades, one solution is to stiffen them. However, this solution generally leads to increase the weight of the blades which affects the performance of the helicopter.

The present invention aims to overcome the disadvantages of the prior art.

For this purpose, the subject of the invention is a flying-wing aircraft comprising:

at least one rotor equipped with blades and configured to pivot about an axis of rotation,

a stator comprising a tubular duct coaxial with the axis of rotation and in which is positioned the rotor (s), and

an orientation system.

According to the invention, the orientation system comprises a plurality of radial wings, arranged inside the duct, which divide the duct into several sectors which each have a passage section, each wing comprising at least one pivoting part configured to pivot around a radial pivot axis so as to reduce the passage section of one of the two sectors adjacent to the wing.

Thus, the orientation system being positioned inside the conduit, all constituent parts are protected.

The invention also relates to a steering method of a flying machine characterized in that it consists in pivoting the pivoting parts each of a given inclination angle so as to reduce the cross section of the sectors based a direction of lateral displacement of the desired flying machine.

Other features and advantages will become apparent from the following description of the invention, a description given by way of example only, with reference to the appended drawings in which:

FIG. 1 is a top view of a helicopter illustrating an embodiment of the invention,

FIG. 2 is an exploded view of the various elements of the helicopter visible in FIG. 1, FIG. 3 is a longitudinal section of the helicopter visible in FIG. 1,

FIG. 4 is a longitudinal section of a system for guiding the ends of the blades,

FIG. 5 is a diagram which illustrates the positioning of the electromagnetic elements integral with the stator,

FIG. 6 is a diagram illustrating the positioning of the electromagnetic elements present at the end of a blade,

FIGS. 7A to 10A are diagrammatic representations in plan view which illustrate the different successive positions of a blade,

FIGS. 7B to 10B are diagrammatic representations which illustrate the relative positioning of the electromagnetic elements of the stator and the blade during the various successive positions of the blade visible in FIGS. 7A to 10A,

FIG. 11 is a longitudinal section of a helicopter illustrating another embodiment,

FIGS. 12A, 12B and 12C are sections of an air flow orientation system which illustrate an embodiment, said air flow orientation system being respectively in the rest position, in the activated position on the right and in the activated position on the left,

FIGS. 13A, 13B and 13C are sections of an air flow orientation system which illustrate another embodiment, said air flow orientation system being respectively in a rest position, in a position activated on the right and in the activated position on the left,

FIGS. 14A, 14B and 14C are sections of an air flow orientation system which illustrate another embodiment, said air flow orientation system being respectively in the rest position, in the position activated on the right and in the activated position on the left, and

Figures 15A to 151 are schematic representations of the top of the flying machine that illustrate its operation.

In Figures 1 to 3, there is shown a flying machine flying wing, such as a helicopter 10, which comprises at least one rotor 12 with a substantially vertical axis of rotation A12. For the rest of the description, a longitudinal direction is parallel to the axis of rotation A12. A transverse plane is a plane perpendicular to the axis of rotation A12 and a radial direction is perpendicular to the axis of rotation A12. A radial plane passes through the axis of rotation A12.

For example, the helicopter 10 visible in Figures 1 to 3 is a drone that includes only a lift system. Of course, the invention is not limited to this application. Thus, the helicopter may include other elements, such as a cabin.

The helicopter 10 further comprises the rotor 12, a stator 14 which comprises a tubular conduit 15 whose axis is coaxial with the axis of rotation A12.

The rotor 12 comprises blades 16 oriented in a plurality of radial directions regularly distributed about the axis of rotation A12. The geometry and number of blades may vary from helicopter to helicopter. Therefore, the profile of the blades is not more detailed. By way of example and without limitation, the rotor 12 of Figure 2 comprises 8 blades. Each blade comprises a first end close to the axis of rotation A12, a second end remote from the axis of rotation A12 and a median zone interposed between the first and second ends.

Preferably, the rotor 12 comprises at least one stiffener 18. Each stiffener 18 comprises a circle or a ring coaxial with the axis of rotation which connects the blades 16 to each other. The fact of providing one or more stiffeners makes it possible to limit the deformation of the blades, the vibrations and the risk of shocks between the blades in the presence of two counter-rotating superimposed rotors.

According to the embodiment of FIG. 2, the rotor comprises a first stiffener 18 which connects the first ends of the blades 16, a second stiffener 18 'which connects the second ends of the blades 16 and a third stiffener 18' which connects the median zones. Of course, the invention is not limited to this embodiment, so that the rotor may comprise no stiffener 18.

According to a first characteristic of the invention, the conduit 15 of the stator 14 comprises a guide system of the first ends 20 of the blades 16. Thus, for each blade 16, the first end 20 is guided in a peripheral groove 22 which extends over the entire periphery of the conduit 15 of the stator 14 and which is configured to maintain the first end 20 between two transverse planes slightly spaced so as to limit the movement of the first end 20 of the blades in the longitudinal direction. Thus, the peripheral groove 22 comprises an upper face 24 positioned in a first transverse plane, a lower face 26 positioned in a second transverse plane and a bottom 28 connecting the upper 24 and lower 26 faces.

At least a portion of the first end 20 is interposed between the upper face 24 and the lower face 26 and comprises an upper zone 30 facing the upper face 24, a lower zone 32 opposite the lower face 26 and a terminal zone 34 opposite the merits 28.

The portion of the first end 20 between the upper and lower faces 26 has a thickness which corresponds to the distance between the upper zone 30 and the lower zone 32. The height of the peripheral groove 22 which corresponds to the distance separating the face upper 24 and the lower face 26 is equal to the thickness of the first end 20 of the blades 16 increased by one operating clearance.

Thus, there is a clearance between the upper face 24 and the upper zone 30, between the lower face 26 and the lower zone 32 and between the bottom 28 and the end zone 34.

According to a simplified variant, the end of each blade is interposed between an upper face 24 and a lower face 26, shifted in the longitudinal direction.

This first feature prevents blades 16 from deforming cone and reduce lift.

According to one configuration, the peripheral groove 22 has a constant section over the entire periphery of the conduit 15 of the stator 14. In parallel, the first stiffener 18 which connects the first ends of the blades 16 corresponds to the part of the first ends of the blades which cooperates with the peripheral groove 22. The first stiffener 18 has a constant section over its entire circumference.

The guidance system is preferably magnetic to limit the friction between the blades 16 and the peripheral groove 22. According to a configuration, the upper face 24 of the peripheral groove 22 comprises a succession of upper magnetic elements 36 with a first polarity and, for each blade, the upper zone 30 of the blades 16 comprises at least one upper magnetic element 38 with a polarity identical to the first polarity to generate a repulsion phenomenon between the upper zone 30 and the In the same way, the lower face 26 of the peripheral groove 22 comprises a succession of lower magnetic elements 40 with a second polarity and, for each blade, the lower zone 32 of the blades 16 comprises at least one magnetic element. lower 42 with a polarity identical to the second polarity to generate a repulsion phenomenon between the lower zone 32 and the lower face 26. The first and second polarities are determined so as to balance the repulsion phenomena and that the first end 20 each blade is approximately centered between the upper 24 and lower 26 faces of the peripheral groove 22.

According to another characteristic, the first end 20 of each blade 16 and the peripheral groove 22 have shapes which cooperate so as to prevent the first end 20 of the blades 16 from coming out of the peripheral groove 22. According to one embodiment, the part the first end 20 interposed between the upper faces 24 and lower 26 has a thickness greater than the remainder of the blade 16 and the peripheral groove 22 has a mouth 44 narrowed with a height less than the enlarged portion of the first end 20. In the presence a first stiffener 18 connecting the first ends of the blades, said first stiffener has a height greater than that of the mouth 44 of the peripheral groove 22.

To prevent the blades from bending out of the peripheral grooves 22, each blade 16 is tensioned. For this purpose, the peripheral groove 22 comprises on either side of the mouth 44 of the inner faces 46 arranged facing internal zones 48 provided at the end 20 of each blade 16. The inner faces 46 comprise a plurality of magnetic elements 46 'with a third polarity and the inner regions 48 of the blades each comprise at least one magnetic element 48' with a polarity identical to the third polarity to generate a repulsion phenomenon between the inner zones 48 and the lower faces 46 and get a tensioning of the blades. This arrangement makes it possible to keep the blades stretched and to limit their deformation in the form of a cone.

The helicopter 10 comprises at least one motor for rotating the blades. According to a first variant, the motorization is said to be mechanical and the blades 16 are connected to a shaft driven in rotation by the motorization which is positioned at the axis of rotation A12. According to a second variant visible in FIGS. 7A to 10A and 7B to 10B, the helicopter comprises at least one electromagnetic motor.

According to one embodiment, the stator 14 comprises a fixed central shaft 50 and the second stiffener 18 'which connects the second ends of the blades 16 forms a hub pivotally mounted around said central shaft 50.

The end zone 34 of each blade comprises at least one electromagnetic element 52 with fixed polarity (which does not change over time), arranged facing the bottom 28 of the peripheral groove 22. According to one configuration, the end zone 34 comprises three electromagnetic elements with fixed polarity 52.1 to 52.3 juxtaposed, two electromagnetic elements 52.1 and 52.3 with a first polarity and an electromagnetic element 52.2 arranged between the electromagnetic elements 52.1 and 52.3 with a second polarity opposite to the first polarity. These three electromagnetic elements 52.1 to 52.3 are aligned and arranged in a transverse plane. Insofar as they are connected to the blades 16, these first electromagnetic elements 52.1 to 52.3 are movable.

In addition, the bottom 28 of the circumferential groove comprises a succession of electromagnetic elements 54.1 to 54. n juxtaposed, alternating polarity, regularly distributed over the entire circumference of the peripheral groove 22. These electromagnetic elements 54.1 to 54. n polarity alternative have not all, at a given moment, the same polarity but alternating polarities, a first electromagnetic element with a first polarity followed by an electromagnetic element with a second polarity opposite the first polarity and so on all the circumference, as illustrated in FIGS. 5, 7B to 10B. These second electromagnetic elements 54.1 to 54. n are connected to the stator 14, they are therefore fixed.

The second electromagnetic elements 54.1 to 54. n are configured to simultaneously change polarity, respecting at all times the alternation of the polarities over the entire circumference of the peripheral groove 22 (north polarity, south polarity, without magnetization). Thus, as illustrated in FIGS. 7B and 10B, which represent four successive instants, the electromagnetic element 54.1 has a first polarity at a given instant as illustrated in FIG. 7B, a second polarity opposite the first polarity at a second instant following the moment, as illustrated in FIG. 8B, again the first polarity to a third instant following the second instant, as illustrated in FIG. 9B and again the second polarity at a fourth instant following the third instant as illustrated in FIG. 10B.

The fixed polarity electromagnetic elements 52.1 to 52.3 of the blades 16 are all the same width (dimension taken circumferentially) and are positioned with a given pitch. The electromagnetic elements with alternating polarity 54.1 to 54.n of the stator all have the same width equal to that of the electromagnetic elements with fixed polarity 52.1 to 52.3 of the blades 16 and are distributed with the same pitch as the electromagnetic elements with fixed polarity 52.1 to 52.3 blades 16.

The electromagnetic actuator comprises a control for controlling the polarity change of the electromagnetic elements with alternative polarity, the rotation speed being a function of the frequency of change of polarities.

FIGS. 7A to 10A and 7B to 10B illustrate the operation of the electromagnetic motor.

FIGS. 7A and 7B show the position of a blade at a first instant, FIGS. 8A and 8B its position at a second instant following the first instant, FIGS. 9A and 9B its position at a third instant following the second instant and FIGS. Figures 10A and 10B its position at a fourth instant after the third moment.

At the first moment, the electromagnetic elements with fixed polarity 52.1, 52.2, 52.3 of the blade are respectively positioned upstream and attracted by the alternating polarity electromagnetic elements 54.1, 54.2, 54.3 of the stator. These attraction forces cause a rotational movement of the blade which moves to a second position at a second instant, as illustrated in FIG. 8B.

The polarities of the electromagnetic elements with alternating polarity of the stator are reversed, as illustrated in FIG. 8B, so that the electromagnetic elements with fixed polarity 52.1, 52.2, 52.3 of the blade are respectively positioned upstream and attracted by the electromagnetic elements with alternative polarity. 54.2, 54.3, 54.4 of the stator. These attractive forces cause a rotational movement of the blade which moves to a third position at a third instant as shown in FIG. 9B.

The polarities of the electromagnetic elements with alternating polarity of the stator are reversed, as illustrated in FIG. 9B, so that the electromagnetic elements with fixed polarity 52.1, 52.2, 52.3 of the blade are respectively positioned upstream and attracted by the alternating polarity electromagnetic elements 54.3, 54.4, 54.5 of the stator causing a rotational movement of the blade which moves to a fourth position at a fourth instant as shown in Figure 10B.

The polarities of the electromagnetic elements with alternating polarity of the stator are reversed as illustrated in FIG. 10B so that the electromagnetic elements with fixed polarity 52.1, 52.2, 52.3 of the blade are respectively positioned upstream and attracted by the alternating polarity electromagnetic elements 54.4 , 54.5, 54.6.

By continuing the change of polarity of the alternating polarity electromagnetic elements of the stator 54.1 to 54. n, the rotation of the blade around the axis of rotation A12 is obtained.

According to a third variant, the helicopter may comprise a mechanical motor and a magnetic motor, the hub of the rotor 12 being connected by a coupling system to an output shaft of the mechanical motor positioned in the central shaft 50.

According to one configuration, the helicopter 10 comprises at least two rotors 12 and 12 'coaxial, superimposed along the axis of rotation A12. The rotors 12 and 12 'may be identical. As illustrated in Figure 3, the stator 14 comprises for each rotor a guide system of the first ends 20 of the blades 16. Thus, the stator 14 comprises for each rotor 12, 12 'a peripheral groove 22, 22'.

Both rotors have counter-rotating rotational movements.

According to another characteristic, the duct 15 of the stator 14 has a nozzle shape and comprises a cylindrical upper portion 56 at which the rotor (s) 12, 12 'and a conical bottom portion 58 configured to form a rotor are positioned. convergent positioned under the rotor (s) 12, 12 '. This configuration makes it possible to accelerate the speed of ejection of the air flow.

To improve aerodynamics, the duct comprises a leading edge 59 which extends over the entire circumference of the duct 15 and which has a convex semicircular radial section and a trailing edge 60 which extends over the entire circumference of the duct 15 and which has a tapered section. As illustrated in FIG. 3, the combination of the tapered shape of the trailing edge 60 and the convergent shape of the duct 15 makes it possible to generate a vacuum outside the duct 15, just above the trailing edge 60. depression makes it possible to generate a return of the flow F coming out of the duct 15, which tends to improve the lift and to increase the stability.

The duct 15 isolates the rotors from the outside environment. Thus, the blades of the rotors are no longer exposed to side winds and are protected, which limits the risk of collision with an object. In addition, the duct 15 also reduces noise.

According to an embodiment visible in FIG. 11, the duct 15 has a torus shape, with a D-shaped section. According to this configuration, the helicopter could be reversible by adapting the configuration of the blades.

The central shaft 50 of the stator 14 comprises a cylindrical central portion 62, an upper portion 64 in the form of a half-sphere and a lower portion 66 conical.

According to the embodiment shown in Figure 11, the helicopter 10 comprises two rotors 12, 12 'coaxial and superimposed, each rotor 12, 12' being rotated by a motor M12, M12 'positioned in the central portion. To limit the spacing between the two rotors 12, 12 ', the motor M12 of the lower rotor 12 is positioned below the lower rotor 12 and the motor M12' of the upper rotor 12 'is positioned above the upper rotor 12' .

The stator 14 comprises in the upper part upper wings 68 arranged in radial planes connecting the conduit 15 and the central shaft 50, positioned above the rotor (s). These upper wings 68 are oriented radially and regularly distributed about the axis of rotation A12. According to an embodiment visible in FIG. 2, the stator 14 comprises four upper wings 68. These upper wings 68 reinforce the structure of the stator 14 and make it possible to structure the flow of air that enters the duct 15.

The stator 14 comprises in the lower part of the lower wings 70 arranged in radial planes connecting the conduit 15 and the central shaft 50, positioned below the rotor (s). These lower wings 70 are oriented radially and evenly distributed around the axis of rotation A12. According to an embodiment visible in FIG. 2, the stator 14 comprises four lower wings 70. These lower wings 70 reinforce the structure of the stator 14. According to another characteristic, the stator 12 comprises at least two diametrically opposed upper flanges 68 and / or lower flanges 70 which comprise at least one pivoting portion about a radially oriented pivot axis.

According to an embodiment visible in FIG. 11, the upper and lower wings 68 can pivot about a radially oriented pivot axis.

According to an embodiment visible in Figures 2 and 3, only the lower wings 70 comprise at least one pivoting part. Thus, each lower wing 70 comprises at the trailing edge 72 a flap 74 whose upper edge is connected to the remainder of the wing by a hinge 76 allowing the flap 74 to pivot about its upper edge. According to a configuration visible in FIGS. 2 and 3, the stator 14 comprises four lower wings 70 forming between them 90 ° angles, whose trailing edges 72 are positioned in the same plane as the trailing edge 60 of the duct 15. Each lower flange 70 comprises a rectangular cutout extending from the trailing edge 72 and in which is positioned a flap 74 whose trailing edge 78 is disposed in the extension of the trailing edge 72. Each flap 74 is connected to the rest of the lower wing 70 by a hinge 76 allowing it to pivot about a pivot axis parallel to the trailing edges 72, 78. Each flap 74 can pivot on both sides of the wing at an angle included between + 45 ° and - 45 °.

The helicopter includes a control for controlling the pivotal movement of each wing 68, 70 or each pivoting wing portion to control the direction of the helicopter.

Regardless of the embodiment, the rotary wing aircraft comprises an orientation system 80 for controlling its flight movement which has a plurality of pivoting radial wings which divide the duct 15 into a plurality of sectors, as illustrated in FIGS. 14C. According to one characteristic of the invention, the wings are disposed inside the duct 15 and are not used to deflect an air flow exiting the duct 15. Thus, all the parts of the wings are positioned between the upper and lower planes. lower duct which respectively contain the leading edge of the duct 15 and the trailing edge of the duct.

According to the embodiment, the orientation system 80 comprises four wings 82 distributed regularly, which divide the duct 15 into four sectors A, B, C and D. Of course, the invention is not limited to this number of wings and sectors.

As illustrated in FIG. 12A for example, each flange 82 has an airfoil with a rounded leading edge 82.1 and a tapered fluid edge 82.2. In a longitudinal plane (containing the axis of rotation A12), the flange 82 is substantially rectangular. Each wing extends from the axis of rotation A12 (or the central shaft 50) to the tubular duct 15.

At least some wings 82 each comprise a pivoting portion 84 configured to pivot about a radial pivot axis A84 (perpendicular to the axis A12).

According to an embodiment visible in FIG. 11, the wing 68, 70 is entirely pivoting, comprises only a pivoting part and extends from the central shaft 50 to the tubular duct 15.

According to other embodiments, each flange 82 comprises a fixed portion 86 and a pivoting portion 84. The pivoting and fixed portions 84, 86 are generally approximately rectangular.

According to one configuration, each flange 82 comprises, in the direction of flow of the air flow in the duct 15, a fixed portion 86 positioned above a pivoting portion 84.

According to another embodiment, when the wing comprises a fixed part and a pivoting part, the fixed and pivoting parts have the same length and extend from the central shaft 50 to the duct 15. According to another embodiment of FIG. embodiment illustrated in Figures 2 to 3, the pivoting portion 74 of the wing (also called flap) has a length less than that of the fixed part. In this case, the fixed part comprises a cutout in which the pivoting part 74 is positioned.

The pivoting portion 84 of at least one flange 82 has a first edge 84.1 adjacent to the fixed portion 86 and a second edge 84.2 forming a trailing edge.

According to a first configuration visible in FIGS. 12A to 12C, the pivot axis A84 of the pivoting portion 84 is positioned at the first edge 84.1. According to this first configuration, the pivoting portion 84 is configured to occupy:

a rest position, visible in Figure 12A, wherein it is disposed in the same plane as the fixed portion 86, substantially vertical, and deviates none of the first and second flow Fl and F2 flowing on either side of the wing 82, a position activated on the right (or in a first direction), visible in Figure 12B, in which the pivoting portion 84 is inclined to the right and forms a non-zero angle Q with the fixed portion 86 or the vertical direction, and deviates the first stream Fl,

a position activated on the left (or in a second direction), visible in FIG. 12C, in which the pivoting part 84 is inclined to the left and forms a non-zero angle Q 'with the fixed part 86 or the vertical direction, and deviates the second stream F2. According to a second configuration visible in FIGS. 13A to 13C, the pivot axis A84 of the pivoting portion 84 is spaced apart from the first and second edges 84.1, 84.2 and positioned approximately between the first and second edges 84.1, 84.2. According to this second configuration, the pivoting portion 84 is configured to occupy:

a rest position, visible in Figure 13A, in which it is disposed in the same plane as the fixed portion 86, substantially vertical, and deviates none of the first and second flow Fl and F2 flowing respectively from a first side and of a second side of wing 82,

a position activated on the right (in a first direction), visible in Figure 13B, in which the pivoting portion 84 is inclined to the right and forms a non-zero angle Q with the fixed portion 86 or the vertical direction, captures a portion of the second stream F2 flowing from the second side of the wing 82 and deflects it towards the first side of the wing 82 and deflects the first stream F1 flowing from the first side of the wing 82,

a position activated on the left (in a second direction), visible in Figure 13C, in which the pivoting portion 84 is inclined to the left and forms a non-zero angle Q 'with the fixed part 86 or the vertical direction, captures a part of the first stream F1 flowing from the first side of the wing 82 and deflects it towards the second side of the wing 82 and deflects the second stream F2 flowing from the second side of the wing 82.

According to a third configuration visible in FIGS. 14A to 14C, the pivot axis A84 of the pivoting portion 84 is positioned at the second edge, 84.2. According to this third configuration, the pivoting portion 84 is configured to occupy:

a rest position, visible in FIG. 14A, in which it is disposed in the same plane as the fixed part 86, substantially vertical, and does not deviate any of the first and second flows Fl and F2 flowing respectively from a first side and of a second side of wing 82, a position activated on the right (in a first direction), visible in FIG. 14B, in which the pivoting part 84 is inclined to the right and forms a non-zero angle Q with the fixed part 86 or the vertical direction, captures a part of the second stream fl flowing from the second side of the flange 82 and deviates to the first side of the flange 82, a position activated to the left (in a second direction), visible in Figure 14C, in which the pivoting part 84 is inclined to the left and forms a non-zero angle Q 'with the fixed portion 86 or the vertical direction, captures a portion of the first flow F2 flowing from the first side of the flange 82 and deflects it to the second side of the wing 82. For all three configurations, the angle of inclination to the right or to the left q, Q 'varies according to the desired orientation for the flying machine.

The flying machine comprises actuators and at least one control for controlling the angle of inclination to the right or left q, Q 'of each pivoting part.

The flying machine comprises at least one set of wings 82 whose pivot axes A84 are approximately coplanar and arranged in a plane perpendicular to the axis of rotation A12.

According to one configuration, the flying machine comprises two sets of wings, a first set of wings 82 positioned above the rotor or rotor (s) and a second set of wings 82 positioned below the rotor (s) ( s).

According to one configuration, the first and second sets of wings comprise the same number of wings and the wings of the first game are arranged vertically above the wings of the second game.

According to one embodiment, each set of wings comprises two pairs of wings, for each pair of wings, the wings being diametrically opposed.

Generally, the wings of the same pair of wings can have identical and synchronized movements and deflect the air flows to the same half of the duct 15. Alternatively, the wings of the same pair of wings can have different and unsynchronized movements.

According to one configuration, the flying machine comprises a first set of wings positioned above the rotor (s) having wings 82 as illustrated in FIGS. 12A to 12C, whose pivoting axes A84 of the pivoting portions 84 are disposed at the upper edge and a second set of wings positioned below the rotor (s) having wings 82 as illustrated in FIGS. 13A to 13C, whose pivoting axes A84 of the pivoting portions 84 are spaced apart from the upper edge.

The movements of the wings of the first and second games can be identical and synchronized.

Whatever the embodiment, the duct 15 is divided around the axis of rotation A12 of the rotor (s) in sectors, two adjacent sectors being separated by at least one flange 82 which has at least one pivoting portion 84 .

The principle of operation of the flying machine is described with reference to FIGS. 15A to 151. According to one configuration, the conduit 15 is divided into four identical sectors A, B, C, D. The adjacent sectors A and B are separated by less a wing 82ab which has at least one pivoting part. The adjacent sectors B and C are separated by at least one wing 82bc which has at least one pivoting part. The adjacent sectors C and D are separated by at least one wing 82cd which has at least one pivoting part. The adjacent sectors D and A are separated by at least one wing 82da which has at least one pivoting part.

When all the pivoting parts of the wings are in the rest position, the and the rotor (s) generate (s), in the tubular duct 15, air flows respectively in the four sectors A, B, C and D which are identical as shown in FIG. 15A. As a result, the flying vehicle moves vertically or remains stationary.

When the pivoting portions of the wings 84ab and 84cd are in the activated position and inclined in a first direction (to the right in FIG. 15B), this causes a decrease in the passage sections of the sectors B and C and, if the pivoting parts are configured according to FIGS. 13A to 13C, a deflection of a part of the flow flowing in sector A towards sector B and of a part of the flow flowing in sector D towards sector C. Consequently, the flows circulating in sectors B and C have an ejection speed at the outlet of the duct 15 or a pressure greater than those of the flows circulating in the sectors A and D which causes a lateral displacement of the flying machine towards a second direction in the direction opposite of the first direction.

When the pivoting portions of the wings 84ab and 84cd are in the activated position and inclined in one direction (to the left in FIG. 15C), this causes a decrease in the passage sections of the sectors A and D and, if the pivoting parts are configured according to FIGS. 13A to 13C, a deflection of a part of the flow flowing in sector B towards the sector A and a portion of the flow flowing in sector C to sector D. Therefore, the flows flowing in sectors A and D have an ejection speed at the outlet of duct 15 or a pressure greater than those flows flowing in sectors B and C which causes a lateral displacement of the flying machine to the first direction, in the opposite direction of the second direction.

When the pivoting portions of the wings 84bc and 84da are in the activated position and inclined in a third direction (downwards in FIG. 15D), this causes a decrease in the passage sections of the sectors D and C and, if the pivoting parts are configured according to FIGS. 13A to 13C, a deflection of a part of the flow flowing in sector A towards sector D and of a part of the flow flowing in sector B towards sector C. Consequently, the flows circulating in the sectors C and D have an ejection speed at the outlet of the duct 15 or a pressure greater than those of the flows circulating in the sectors A and B which causes a lateral displacement of the flying machine towards a fourth direction, in opposite direction of the third direction.

When the pivoting portions of the wings 84bc and 84da are in the activated position and inclined in the fourth direction (upwards in FIG. 15E), this causes a decrease in the passage sections of the sectors A and B and, if the pivoting parts are configured according to FIGS. 13A to 13C, a deflection of a part of the flow flowing in sector D towards sector A and of a part of the flow flowing in sector C towards sector B. Consequently, the flows circulating in the sectors A and B have an ejection speed at the outlet of the duct 15 or a pressure greater than those of the flows circulating in the sectors C and D, which causes a lateral displacement of the flying machine towards the third direction, opposite direction of the fourth direction.

When the pivoting portions of the wings 84bc and 84da are in the activated position and inclined in the third direction (downwards in FIG. 15F) and the pivoting portions of the wings 84ab and 84cd are in the activated position and inclined in the second direction (towards the left in FIG. 15F), the flow flowing in sector D has an ejection speed at the outlet of duct 15 or a pressure greater than that of the flow circulating in sector B, which causes a lateral displacement of the flying machine towards a fifth direction, opposed to a combination of the second and third directions that is a function of the angle inclination of the pivoting portions of the wings 84bc and 84da and the angle of inclination of the pivoting portions of the wings 84ab and 84cd.

When the pivoting portions of the wings 84bc and 84da are in the activated position and inclined in the third direction (downwards in FIG. 15G) and the pivoting portions of the wings 84ab and 84cd are in the activated position and inclined in the first direction (towards the right in FIG. 15G), the flow flowing in sector C has an ejection speed at the outlet of duct 15 or a pressure greater than that of the flow circulating in sector A, which causes a lateral displacement of the flying machine towards a sixth direction, opposed to a combination of the first and third directions which is a function of the angle of inclination of the pivoting portions of the wings 84bc and 84da and the angle of inclination of the pivoting portions of the wings 84ab and 84cd.

When the pivoting portions of the wings 84bc and 84da are in the activated position and inclined in the fourth direction (upwards in FIG. 15H) and the pivoting portions of the wings 84ab and 84cd are in the activated position and inclined in the second direction (towards the left in FIG. 15H), the flow flowing in sector A has an ejection speed at the outlet of duct 15 or a pressure greater than that of the flow circulating in sector C, which causes a lateral displacement of the flying machine towards a seventh direction, opposed to a combination of the second and fourth directions which is a function of the angle of inclination of the pivoting portions of the wings 84bc and 84da and the angle of inclination of the pivoting portions of the wings 84ab and 84cd.

When the pivoting portions of the wings 84bc and 84da are in the activated position and inclined in the fourth direction (upwards in Figure 151) and the pivoting portions of the wings 84ab and 84cd are in the activated position and inclined in the first direction (to the right in FIG. 151), the flow flowing in sector B has an ejection speed at the outlet of duct 15 or a pressure greater than that of the flow circulating in sector D, which causes a lateral displacement of the flying machine towards an eighth direction, opposed to a combination of the first and fourth directions which is a function of the angle of inclination of the pivoting portions of the wings 84bc and 84da and the angle of inclination of the pivoting portions of the wings 84ab and 84cd.

Consequently, the direction of lateral displacement of the flying machine is a function of the relationships between the passage sections of the different sectors, said passage sections. being a function of the angle of inclination of the swivel parts of the wings 84bc and 84da and the angle of inclination of the swivel parts of the wings 84ab and 84cd

Claims

1. A flying wing engine comprising:

at least one rotor (12) equipped with blades (16) and configured to pivot about an axis of rotation (A12),

a stator (14) comprising a tubular duct (15) coaxial with the axis of rotation (A12) and in which is positioned the rotor (s) (12, 12 '), and

an orientation system (80),

characterized in that the orientation system (80) comprises a plurality of radial flanges (70, 82) disposed within the duct (15) which divide the duct (15) into a plurality of sectors (A, B, C, D) each having a passage section, each wing (70, 82) having at least one pivoting portion (74, 84) configured to pivot about a radial pivot axis (A84) so as to reduce the cross-section passing one of the two sectors adjacent to the wing (70, 82).

2. A rotary wing engine according to claim 1, characterized in that each wing (82) comprises, in the direction of flow of the air flow in the conduit (15), a fixed portion (86) positioned a pivoting portion (84) having a first edge (84.1) adjacent to the fixed portion (86) and a second edge (84.2) forming a trailing edge.

Rotary wing engine according to claim 2, characterized in that and in that the pivot axis (A84) of the pivoting part (84) of at least one wing (82) is positioned at the first edge (84.1), the pivoting portion (84) being configured to occupy:

a rest position, in which the pivoting part (84) is arranged in the same plane as the fixed part (86) and does not deviate any of the first and second flows (F1, F2) flowing on either side of the wing (82),

a position activated in a first direction, in which the pivoting part (84) is inclined in the first direction and forms a non-zero angle (Q) with the fixed part (86) and deflects the first stream (F1),

a position activated in a second direction, wherein the pivoting portion (84) is inclined in the second direction and forms a non-zero angle (q ') with the fixed portion (86) and deflects the second flow (F2).

Rotary wing engine according to claim 2, characterized in that and in that the pivot axis (A84) of the pivoting part (84) of at least one wing (82) is positioned away from the first and second edges (84.1, 84.2), the pivoting portion (84) being configured to occupy:

a rest position, wherein the pivoting portion (84) is disposed in the same plane as the fixed portion (86) and does not deviate any of the first and second streams (F1, F2) flowing respectively from a first side and a a second side of the wing (82), a position activated in a first direction, in which the pivoting part (84) is inclined in the first direction and forms a non-zero angle (Q) with the fixed part (86) , captures a portion of the second stream (F2) flowing from the second side of the wing (82) and deflects it to the first side of the wing (82) and deflects the first stream (Fl) flowing from the first side of the wing (82),

a position activated in a second direction, in which the pivoting part (84) is inclined in the second direction and forms a non-zero angle (q ') with the fixed part (86), captures a part of the first stream (F1) s flowing from the first side of the wing (82) and deflects it to the second side of the wing (82) and deflects the second stream (F2) flowing from the second side of the wing (82).

Rotary wing engine according to claim 2, characterized in that and in that the pivot axis (A84) of the pivoting part (84) of at least one wing (82) is positioned at the second edge (84.2), the pivoting portion (84) being configured to occupy:

a rest position, wherein the pivoting portion (84) is disposed in the same plane as the fixed portion (86) and does not deviate any of the first and second streams (F1, F2) flowing respectively from a first side and a a second side of the wing (82), a position activated in a first direction, in which the pivoting part (84) is inclined in the first direction and forms a non-zero angle (Q) with the fixed part (86) , captures a portion of the second stream (F2) flowing from the second side of the wing (82) and deflects it to the first side of the wing (82),

a position activated in a second direction, in which the pivoting part (84) is inclined in the second direction and forms a non-zero angle (q ') with the fixed part (86), captures a portion of the first stream (Fl) flowing from the first side of the wing (82) and deflects it to the second side of the wing (82).

6. A flywheel gear according to one of claims 2 to 5, characterized in that it comprises at least one set of wings (82) whose pivot axes (A84) are approximately coplanar and arranged in a plane perpendicular to the axis of rotation (A12).

7. A flywheel machine according to the preceding claim, characterized in that it comprises two sets of wings, a first set of wings (82) positioned above the rotor (s) and a second set of wings. wings (82) positioned below the rotor (s).

8. A rotary wing flying machine according to the preceding claim, characterized in that the first and second set of wings comprise the same number of wings and the wings of the first set are disposed vertically above the wings of the second set.

9. A flywheel machine according to the preceding claim, characterized in that the first set of wings positioned above the rotor or rotor (s) has wings (82) whose pivot axes (A84) pivoting parts (84) are arranged at the first edge of the pivoting parts (84) and in that the second set of wings positioned below the rotor (s) has wings (82) whose pivot axes (A84 ) pivoting portions (84) are spaced apart from the first edge of the pivoting portions (84).

10. A flywheel machine according to one of claims 6 to 9, characterized in that each set of wings comprises two pairs of wings, for each pair of wings, the wings being diametrically opposed and having identical movements. and synchronized.

Rotary wing engine according to one of the preceding claims, characterized in that the stator (14) comprises an upper face (24) positioned in a first transverse plane, a lower face (26) positioned in a second transverse plane. and in that each blade (16) of the rotor comprises a first end (20) interposed between the upper face (24) and the lower face (26), said first end (20) comprising an upper zone (30) opposite the upper face (24), a lower zone (32) opposite the lower face (26), the distance between the upper face (24) and the lower face (26) being equal to the thickness of the first end ( 20) blades (16) increased by a running clearance

Rotary wing engine according to the preceding claim, characterized in that the upper face (24) has a first polarity and the upper zone (30) of the blades (16) has a polarity identical to the first polarity to generate a phenomenon. repulsion between the upper zone (30) and the upper face (24) and in that the lower face (26) has a second polarity and the lower zone (32) of the blades (16) has a polarity identical to the second polarity to generate a repulsion phenomenon between the lower zone (32) and the lower face (26).

Rotary wing engine according to claim 11 or 12, characterized in that the stator comprises a peripheral groove (22, 22 ') delimited by the upper face (24), the lower face (26) and a bottom (28). ) connecting the upper (24) and lower (26) faces and that the first end (20) of each blade (16) and the peripheral groove (22) have shapes that cooperate to prevent the first end (20) from ) blades (16) out of the peripheral groove (22).

14. A rotary wing engine according to one of the preceding claims, characterized in that the first ends (20) of the blades (16) of the rotor (12) are connected by a first stiffener (18) in the form of a circle or a ring coaxial with the axis of rotation (A12).

15. A method of controlling a flying machine according to one of the preceding claims, the flying machine comprising:

an orientation system (80),

characterized in that it consists in splitting the duct (15) into several sectors (A, B, C, D) each having a passage section, two adjacent sectors being separated by at least one radial flange (82) having at least one pivoting portion (84) configured to pivot about a radial pivot axis (A84) and pivoting the pivoting portions each by a given inclination angle so as to reduce the cross section of the sectors (A, B, C, D) according to a direction of lateral displacement of the desired flying vehicle.