阅读说明：本技术 设置有横向气流控制系统的空气动力学元件 (Aerodynamic element provided with a lateral air flow control system ) 是由 M·法鲁兹-富凯 于 2020-02-14 设计创作，主要内容包括：本发明涉及设置有横向气流控制系统的空气动力学元件。空气动力学元件(1)包括电离系统(14)和控制系统(15),所述电离系统使在所述空气动力学元件(1)的顶面(12)上流动的气流(24B)电离,所述控制系统产生与电流和磁场相关联的至少一个电磁力,所述至少一个电磁力沿与已电离的所述气流(24B)的流动方向相反的方向定向,使得所述电磁力减少所述气流(24B)的流动的不稳定性。(The invention relates to an aerodynamic element provided with a lateral air flow control system. The aerodynamic element (1) comprises an ionization system (14) that ionizes a flow of air (24B) flowing on a top surface (12) of the aerodynamic element (1), and a control system (15) that generates at least one electromagnetic force associated with an electric current and a magnetic field, said at least one electromagnetic force being oriented in a direction opposite to a flow direction of the ionized flow of air (24B), such that the electromagnetic force reduces instability of the flow of air (24B).)

1. An aerodynamic element, said aerodynamic element (1) comprising a first face (12) on which an air flow flows and a second face (13) opposite to said first face (12), characterized in that said aerodynamic element (1) comprises an ionization system (14) configured to ionize said air flow propagating on said first face (12) and a control system (15) configured to generate, in a direction opposite to the direction of said air flow, at least one electromagnetic force (F) capable of modifying the flow of said air flow ionized by said ionization system (14), each said at least one electromagnetic force (F) being generated by a current (J1, J2) associated with a magnetic field (B1, B2).

2. The aerodynamic element of claim 1,

characterized in that said control system (15) comprises:

-a series of current conducting elements (16) arranged parallel to each other on the first face (12), each conducting element of the series of conducting elements (16A) representing a cathode (C) or an anode (a), the series of conducting elements (16) forming alternating cathodes (C) and anodes (a), the series of conducting elements (16) being configured to circulate a plurality of currents (J1, J2), each current of the currents (J1, J2) circulating from a cathode (C) to an adjacent anode (a); and

-a series of magnetic elements (18) arranged parallel to each other on said second face (13), said series of magnetic elements (18) being configured to generate a magnetic field (B1, B2) in a so-called radial direction to each interface (19) between two consecutive magnetic elements (18A), said series of magnetic fields (B1, B2) being formed by an alternating magnetic field (B1) directed towards said first face (12) and a magnetic field (B2) directed towards said second face (13).

3. The aerodynamic element of claim 2,

characterized in that each of said magnetic elements (18A) is a magnet (23) formed in two parts, each part being associated with a north pole (N) or a south pole (S), each magnetic field (B1, B2) being radially generated by bringing into contact the parts of two adjacent magnets (23) associated with the same pole (N, S), the magnetic fields (B1, B2) being oriented towards said first face (12) if said part in contact is associated with a north pole (N) or towards said second face (13) if said part in contact is associated with a south pole (S).

4. The aerodynamic element of claim 3,

characterized in that each of said magnets (23) is produced from one of the following materials: samarium cobalt, neodymium iron boron.

5. Aerodynamic element according to one of claims 1 and 2,

characterized in that each of the magnetic elements (18A) is a superconductor arranged in a sheath.

6. Aerodynamic element according to one of the preceding claims,

characterized in that said ionization system (14) comprises an electromagnetic wave generator and a plurality of waveguides (20) arranged between said first face (12) and said second face (13), each of said waveguides (20) being configured to propagate an electromagnetic wave generated by said electromagnetic wave generator, each of said waveguides (20) being provided with a plurality of holes (21), each of said holes (21) being configured to diffuse a portion of said electromagnetic wave, said portion of said electromagnetic wave diffused through each of said holes (21) ionizing said airflow flowing on said first face (12).

7. Aerodynamic element according to one of the preceding claims,

characterized in that said aerodynamic element comprises a dielectric material (22).

8. The aerodynamic element of claim 7,

characterized in that said dielectric material (22) is one of the following materials: polymeric materials, silicone or ceramic materials.

9. An aircraft is provided, which is provided with a plurality of flying wheels,

characterized in that the aircraft comprises at least one aerodynamic element (1) according to any one of claims 1 to 8.

Technical Field

The invention relates to an aerodynamic element for an aircraft, comprising an airflow ionization system and a system for controlling the flow of the ionized airflow.

Background

The aerodynamic element may correspond, although not exclusively, to a wing of an aircraft, such as a transport aircraft. As specified below, the aerodynamic element may also be another aerodynamic element (or surface) of the aircraft (tail unit, flap, etc.).

Especially in the case of so-called laminar wings of an aircraft (that is to say wings which can maintain laminar flow over a considerable distance), it is known that it is generally not possible for the sweep angle of the wing to increase by more than 20 ° (at the leading edge of the wing).

Indeed, an airfoil sweep angle at the leading edge exceeding 20 ° can generate transverse flow instabilities, in particular for laminar wings in which the pressure gradient remains low, i.e. less than or equal to 0, over a long portion of the chord of the wing. This lateral flow instability is a major limitation in increasing the sweep angle of the wing. This phenomenon is characterized by the presence of transverse air flow along the span, accompanied by vortices that move along the span. This prevents the maintenance of laminar flow. Now, an increase in the sweep angle will make it possible to increase the cruising flight speed of the aircraft without increasing drag and fuel consumption.

The aim of the invention is to improve the flow conditions on aerodynamic elements of an aircraft, such as a wing, in order to prevent significantly the occurrence of lateral flow instabilities, even with high sweep angles of the wing, in particular in the case of laminar flow wings.

Disclosure of Invention

To this end, the invention relates to an aerodynamic element comprising a first face on which an air flow flows and a second face opposite to the first face.

According to the invention, the aerodynamic element comprises an ionization system configured to ionize the gas flow propagating on the first face and a control system configured to generate at least one electromagnetic force capable of modifying the flow of the gas flow ionized by the ionization system, each of said at least one electromagnetic force being generated by an electric current associated with a magnetic field.

Thus, by means of the invention, an aerodynamic element is obtained which is capable of generating one or more electromagnetic forces and of making the flow of the air flow sensitive to this or these electromagnetic forces. Further, as specified below, the one or more electromagnetic forces generated are directed in a direction opposite to the cross-flow of air. Thus, flow instabilities of the airflow may be reduced, which contributes to improving laminar flow conditions over the aerodynamic element.

Advantageously, the control system comprises:

-a series of current conducting elements arranged parallel to each other on the first face, each of the conducting elements representing a cathode or an anode, the series of conducting elements forming alternating cathodes and anodes, the series of conducting elements being configured to circulate a plurality of currents, each of the currents circulating from a cathode to an adjacent anode; and

-a series of magnetic elements arranged parallel to each other on said second face, said series of magnetic elements being configured to generate a magnetic field in a direction so-called radial to each interface between two successive magnetic elements, said series of magnetic fields being formed by alternating magnetic fields oriented towards said first face and magnetic fields oriented towards said second face.

Furthermore, in the first embodiment, each of said magnetic elements is a magnet formed in two parts, each part being associated with a north or south pole, each magnetic field being generated radially by bringing into contact the parts of two adjacent magnets associated with the same pole, the magnetic field being oriented towards said first face if said part in contact is associated with a north pole or towards said second face if said part in contact is associated with a south pole.

Preferably, in this first embodiment, each of the magnets is produced from one of the following materials: samarium cobalt, neodymium iron boron.

Furthermore, in a second embodiment, each of the magnetic elements is a superconductor arranged in a sheath filled with nitrogen.

Furthermore, advantageously, the ionization system comprises an electromagnetic wave generator and a plurality of waveguides arranged between the first face and the second face, each of the waveguides being configured to propagate an electromagnetic wave generated by the electromagnetic wave generator, each of the waveguides being provided with a plurality of holes, each of the holes being configured to diffuse a portion of the electromagnetic wave, the portion of the electromagnetic wave diffused through each of the holes ionizing the gas flow flowing on the first face.

Furthermore, advantageously, said aerodynamic element comprises a dielectric material.

Preferably, the dielectric material is one of the following materials: polymeric materials, silicone or ceramic materials.

The invention also relates to an aircraft, in particular a transport aircraft, comprising at least one aerodynamic element as described above.

Drawings

The drawings will give a good understanding of how the invention may be made. In the drawings, like reference numerals designate similar elements.

Fig. 1 is a schematic perspective view of an aircraft to which the invention is applied.

Fig. 2 schematically illustrates a part of a wing of an aircraft, in which part an aerodynamic element according to a particular embodiment of the invention may be arranged.

Fig. 3 is a perspective view of a portion of an aerodynamic element according to a particular embodiment of the invention.

Figure 4A shows a first perspective view of an ionization system and a control system of an aerodynamic element according to a particular embodiment of the present invention.

Figure 4B shows a second perspective view of an ionization system and a control system of an aerodynamic element according to a particular embodiment of the present invention.

Figure 4C shows a third perspective view of an ionization system and a control system of an aerodynamic element according to a particular embodiment of the present invention.

Detailed Description

Fig. 1 schematically shows an aircraft AC, in particular a transport aircraft, which is provided with at least one aerodynamic element 1 (not specifically shown) such as that represented in fig. 3.

In the context of the present invention, the aerodynamic element 1 may correspond to at least a part of one of the following elements of the aircraft:

-wings 2, 3;

a vertical tail unit 4;

-horizontal tail units 5, 6;

-a portion of the fuselage 7;

nacelles 8, 9 of engines 10, 11; or

A flap (not shown).

By way of non-limiting illustration, the aerodynamic element 1 considered in the remainder of the description corresponds to a portion (or section) of one of the wings 2, 3 of the aircraft AC. In the example shown in fig. 2, the aerodynamic element 1 is arranged along a so-called transverse axis W-W.

Airfoils with sweep angles greater than 20 ° create airflow flow instabilities. As represented in fig. 1 and 2, the airflow 24 then includes a laminar airflow 24A flowing from the leading edge 25 to the trailing edge 26 in the direction of arrow G and a transverse airflow 24B flowing along the transverse axis W-W in the direction of arrow H in the transverse direction.

As represented in fig. 3, the aerodynamic element 1 is provided with a first face (called top face 12) on which the air flow 24 flows and a second face (called bottom face 13). As an example, the thickness of the aerodynamic element 1 between the top surface 12 and the bottom surface 13 is about 10 mm.

In the context of the present invention, the adjectives "bottom" and "top" are defined towards the inside of the aerodynamic element 1 and towards the outside of the aerodynamic element 1, respectively, according to a radial direction with respect to the transversal axis W-W.

According to the invention, the aerodynamic element 1 comprises an ionization system 14 configured to ionize an airflow 24 flowing on the top surface 12 and a control system 15 configured to generate one or more electromagnetic forces F (fig. 2) in a direction opposite to the arrow H. The electromagnetic force or forces F can alter the flow of the gas stream 24 ionized by the ionization system 14. The electromagnetic force F is generated by an electric current associated with a magnetic field.

In a preferred embodiment, as represented in fig. 3, the control system 15 includes a series of current conducting elements 16A (hereinafter "conducting elements") 16 configured to circulate currents J1, J2 (fig. 4A).

As represented in fig. 3, the conductive elements 16A are metal plates having an elongated shape in the lateral direction. As an example, in the case of the wings 2, 3, the length of each conductive element 16A (in the transverse direction) may represent the total length of the leading edge 25 of the wings 2, 3 of the aircraft AC. Furthermore, the series 16 of conductive elements 16A may extend (in the longitudinal direction) over a distance which may represent up to 20% of the distance between the leading edge 25 and the trailing edge 26 of the wings 2, 3 of the aircraft AC.

Furthermore, the conducting elements 16A are arranged parallel to each other in the longitudinal direction on the top face 12 of the aerodynamic element 1. As represented in fig. 4A, the conductive elements 16A are spaced apart from each other by a certain spacing 17. As an example, the spacing 17 is between 1 and 5 millimeters. Each conductive element 16A has a width of between 1 mm and 5 mm.

In a preferred embodiment, each conductive element 16A is either a cathode C or an anode a, as represented in fig. 4A. The conductive elements 16A are arranged to form alternating cathodes C and anodes a.

In addition, each conductive element 16A is connected to a negative terminal if it is a cathode C or to a positive terminal of a direct current generator (not shown) if it is an anode a. In a particular embodiment, this direct current generator corresponds to a current generator with which the engines 10, 11 of the aircraft AC are equipped. The direct current generator subjects each cathode C and each anode a adjacent thereto to a voltage. This voltage generates currents J1, J2 that circulate from the cathode C to the adjacent anode a, as represented in fig. 4A. As an example, the voltage is of the order of several kilovolts.

As represented in fig. 4A, the series of cathode C and anode a in the direction of arrow G causes current J2 to circulate in the longitudinal direction in the direction of arrow G. The series of anodes a and cathodes C in the direction of arrow G causes the current J1 to circulate in the longitudinal direction in the opposite direction to arrow G.

Thus, the series 16 of conductive elements 16A is configured to cycle the currents J1, J2 alternately in opposite directions.

In addition, the control system 15 includes a series 18 of magnetic elements 18A. As shown in fig. 3 and 4B, the magnetic element 18A has an elongated shape in the lateral direction. The magnetic elements 18A are arranged on the bottom surface 13 in parallel to each other in the longitudinal direction. Further, the magnetic elements 18A are in contact with each other. Each magnetic element 18A is located below the conductive element 16A in the radial direction. The width of the magnetic element 18A (in the longitudinal direction) is greater than the width of the conductive element 16A so that the interface 19 between two magnetic elements 18A in contact is located below the space 17 between two conductive elements 16A.

Successive magnetic elements 18A are configured to generate magnetic fields B1, B2 in a direction radial to each interface 19 between two magnetic elements 18A. A series of magnetic fields B1, B2 in the longitudinal direction correspond to alternating magnetic fields B1 directed towards the top surface 12 and B2 directed towards the bottom surface 13.

Thus, the series 16 of conducting elements 16A associated with the series 18 of magnetic elements 18A generates an electromagnetic force F, which is oriented transversely in a direction opposite to the flow of the transverse air flow 24B according to arrow H.

In the first preferred embodiment, the magnetic element 18A is a magnet 23 provided with a north pole N and a south pole S. By way of example, these magnets 23 are produced from samarium cobalt alloy. These magnets may also be produced from neodymium-iron-boron alloys.

In addition, as shown in fig. 4B, each magnet 23 is formed of a front portion and a rear portion. Each pole N, S corresponds to either the front or the back of a magnet.

In the context of the present invention, the adjectives "front" and "rear" are defined in the longitudinal direction, with respect to the aerodynamic element 1, respectively in the direction of the arrow G and in the direction opposite to the direction of the arrow G.

As represented in fig. 4B, the magnet 23 disposed below the cathode C is formed of a north pole N at the rear thereof and a south pole S at the front thereof. The magnet 23 arranged below the anode a is formed by a south pole S at its rear and a north pole N at its front.

In addition, the magnets 23 are arranged parallel to each other in the longitudinal direction such that the front portion of one magnet 23 provided with the south pole S (or the north pole N) is in contact with the rear portion of one magnet 23 provided with the south pole S (or the north pole N). The contact of the front of a magnet 23 with the rear of an adjacent magnet 23 (provided with the same pole N, S) generates a magnetic field B1, B2 in the radial direction at the interface 19 between the magnets 23. As represented in FIG. 4B, if the portion in contact is associated with a North Pole N, then the magnetic field B1 generated at interface 19 is oriented toward top surface 12. If the contacted portion is associated with a south pole S, the magnetic field B2 generated at the interface is directed toward the bottom surface 13. The interface 19 between the two magnets 23 is located below the space 17 between the two conductive elements 16A. Thus, each magnetic field B1, B2 generated traverses radially across the space 17 between the two conductive elements 16A regardless of its orientation.

As represented in fig. 4C, a magnetic field B1 oriented radially toward top surface 12 is associated with a current J1 circulating in space 17 in a direction opposite to the direction of arrow G, which generates an electromagnetic force F oriented in a direction opposite to the direction of arrow H.

The magnetic field B2, oriented radially towards the bottom surface 13, is associated with a current J2 circulating in the direction of arrow G in the space 17, which generates an electromagnetic force F oriented in the direction opposite to the direction of arrow H.

In a variant, the magnetic element 18A is produced from a high critical temperature superconducting material (not shown). These high critical temperature superconducting materials (hereinafter referred to as "superconductors") exhibit specific magnetic properties at temperatures below the critical temperature. By way of example, the critical temperature of a copper-acid salt type superconductor is about-135 degrees Celsius.

The superconductor is elongated in shape in the transverse direction and is arranged in a sheath (not shown). Each jacket is filled with liquid nitrogen to maintain the superconductor at a temperature below its critical temperature. The superconductor, at a temperature below its critical temperature, is able to generate, at each interface between the two sheaths, an alternating magnetic field B1 directed towards the top face 12 and a magnetic field B2 directed towards the bottom face 13.

In a preferred embodiment, the ionization system 14 includes an electromagnetic wave generator (not shown). As an example, the electromagnetic wave generated by the electromagnetic wave generator is a microwave. These microwaves have a frequency of about 2.45 gigahertz.

In addition, the ionization system 14 also includes a plurality of waveguides 20 configured to propagate the electromagnetic waves generated by the electromagnetic wave generator in a lateral direction. These waveguides 20 are formed by tubes which are elongate in the transverse direction and are arranged parallel to one another in the longitudinal direction. In a preferred embodiment, waveguide 20 has a rectangular cross-section, as represented in FIG. 4C. In a variant, the waveguide has a square cross-section.

Further, each waveguide 20 is disposed between the conducting element 16A and the magnetic element 18A. The width of each waveguide 20 in the longitudinal direction is substantially equal to the width of the conductive element 16A.

In a preferred embodiment, the waveguide 20 is provided with a plurality of holes 21. The holes 21 are arranged (in the transverse direction) along the faces 27 of the waveguide 20, which extend in the transverse direction and in the radial direction. Each aperture 21 is configured to diffuse a portion of the electromagnetic wave between the waveguides 20. The diffusion portion of the electromagnetic wave (hereinafter referred to as "diffusion portion") is capable of propagating in all directions, in particular, in the radial direction across the space 17 between the two conductive elements 16A. The gas flow 24 flowing over the top surface 12 is ionized when it comes into contact with the diffusion section. The ionized gas stream 24 includes cations, which are elements that carry positive charges, and anions, which are elements that carry negative charges. These cations and anions are sensitive to the electromagnetic force F.

In a preferred embodiment, the aerodynamic element 1, where the control system 15 and the ionization system 14 are arranged, comprises a dielectric material 22. This dielectric material 22 is configured to electrically insulate the waveguide 20 from the magnetic element 18A and the conductive element 16A. Thus, dielectric material 22 is present between each waveguide 20. The dielectric material may be one of the following materials: polymer material, ceramic material, silicone.

An example of the operation of the aerodynamic element 1 is presented below with reference to fig. 4C.

The air flow 24 flowing over the top surface 12 of the aerodynamic element 1 comprises a laminar air flow 24A flowing longitudinally in the direction of the arrow G, and a transverse air flow 24B. This cross air flow 24B corresponds to a vortex moving in the direction of arrow H in the cross direction. The cross-flow 24B may become unstable and create turbulent eddies. Notably, these turbulent eddies may result in loss of attachment of the airflow to the wings 2, 3.

The electromagnetic wave generator generates microwaves having a frequency of 2.45 gigahertz. The microwave propagates in the waveguide 20 in a transverse direction. A portion of the microwaves is diffused through the holes 21 arranged on the lateral face 27 of the waveguide 20. The holes 21 are distributed over the entire length of the waveguide 20 in the transverse direction so that the portion of the microwave is diffused over the entire length of the aerodynamic element 1. The diffusion section may propagate through the space 17 in all directions, in particular in a radial direction.

Then, the diffuser portion is brought into contact with the laminar flow 24A and the cross flow 24B existing at the interval. The laminar airflow 24A and the cross airflow 24B are then ionized. Once ionized, they are formed from anions (i.e., elements whose charge is negative) and cations (i.e., elements whose charge is positive).

The spatial configuration of the control system 15 is such that only the ionized cross-directional airflow 24B is sensitive to the generated electromagnetic force or forces. Accordingly, the cations or anions forming the cross-flow 24B are displaced in the direction of arrow H, and also to the closest anode a or cathode C.

As represented in fig. 4C, the cations of the cross-flow 24B are directed towards the anode a by following a current J1 directed in the opposite direction to arrow G, while the anions are directed towards the cathode C by following the opposite direction to current J1. Thus, the cations and anions are deflected in opposite directions.

The cations or anions are subjected to a magnetic field B1 that deflects their trajectories radially towards the top surface 12 or the bottom surface 13. Although the current J1 and the magnetic field B1 deflect the positive and negative ions of the ionized transverse airflow 24B in opposite directions, their association creates an electromagnetic force F. This electromagnetic force F is directed in a direction opposite to the flow of cations and anions of the cross-gas flow 24B such that the cations and anions are no longer capable of being displaced.

The cations of the transverse gas flow 24B may also be directed towards the anode a by following a current J2 directed in the direction of arrow G. The anions of the transverse gas flow 24B may be directed towards the cathode C by following a direction opposite to the current J2. Thus, the cations are deflected in the direction of arrow G, while the anions are deflected in the opposite direction to arrow G. The magnetic field B2 experienced by the cations or anions also deflects their trajectories in the direction of the bottom surface 13 or in the direction of the top surface 12. Thus, current J2 and magnetic field B2 deflect cations and anions in opposite directions. The association of current J2 and magnetic field B2 generates an electromagnetic force F that is directed in a direction opposite to the flow of cations and anions of cross-air flow 24B.

The ionized transverse air flow 24B is completely subjected to the electromagnetic force F. These electromagnetic forces F act in a direction opposite to the flow direction of the cross air flow 24B, so that the cross air flow disappears.

As mentioned above, the aerodynamic element 1 offers a number of advantages. In particular:

the aerodynamic element makes it possible to maintain laminar flow on the top of the wing 2, 3, the sweep of the leading edge 25 of which(FIG. 2) greater than 20 °;

the aerodynamic element allows a higher cruising speed of the aircraft AC;

the aerodynamic element makes it possible to provide laminar flow over the wings 2, 3 of the long-haul aircraft;

the aerodynamic element allows to reduce the drag even at mach numbers greater than 0.77, thus allowing to reduce the fuel consumption;

the aerodynamic element can prevent the formation of ice on its surface;

the aerodynamic element may house one or more other systems in its internal volume; and is

The aerodynamic element generates substantially no additional weight.