BE1024276B1 - AIRCRAFT WING COMPRISING A MOBILE FLYING LEFT SIDE DRIVEN BY A LINEAR ELECTRIC MOTOR - Google Patents

Abstract

The invention relates to an aircraft wing comprising a movable trailing edge flap (16), the wing comprising a device (50) for setting this flap in motion, the device being equipped with: - a beam (51 ) carrying a guide rail; a carriage (52a) movably mounted on the rail (20); - An articulated connection (40a) between the carriage (52a) and a fitting (30) integral with the shutter; - A tilting member (29) of the movable flap; - an articulated connection (40b) between the fitting (30) and the tilting member (29); and - an articulated connection (40c) between the tilting member (29) and the beam (51). According to the invention, the device (50) comprises a linear electric motor (22) comprising a primary assembly (52) equipped with the carriage (52a) which integrates coils (55), and a secondary assembly (54) comprising a magnetic path arranged on the rail (20).

Description

(30) Priority data:

(73) Holder (s):

SO N ACA SA 6041, GOSSELIES Belgium (72) Inventor (s):

LANGER Hugues

4000 LIEGE

Belgium

SCIARRABONE Steve 6060 GILLY Belgium

DEBAISIEUX Stéphane

1495 SART LADIES AVELINES

Belgium (54) AIRCRAFT WING COMPRISING A MOBILE LEAKING EDGE SHUTTER DRIVEN BY A LINEAR ELECTRIC MOTOR (57) The invention relates to an aircraft wing comprising a moving trailing edge shutter (16), the wing comprising a device (50) for setting in motion this shutter, the device being equipped with: a beam (51) carrying a guide rail; - a carriage (52a) mounted mobile on the rail (20); - an articulated connection (40a) between the carriage (52a) and a fitting (30) integral with the flap; - a tilting member (29) of the movable flap; - an articulated connection (40b) between the fitting (30) and the tilting member (29); and - an articulated connection (40c) between the tilting member (29) and the beam (51). According to the invention, the device (50) comprises a linear electric motor (22) comprising a primary assembly (52) equipped with the carriage (52a) which integrates coils (55), and a secondary assembly (54) comprising a magnetic path arranged on the rail (20).

30 52 40a

BELGIAN INVENTION PATENT

FPS Economy, SMEs, Middle Classes & Energy

Publication number: 1024276 Deposit number: BE2016 / 5823

Intellectual Property Office International Classification: B64C 9/16 Date of issue: 01/11/2018

The Minister of the Economy,

Having regard to the Paris Convention of March 20, 1883 for the Protection of Industrial Property;

Considering the law of March 28, 1984 on patents for invention, article 22, for patent applications introduced before September 22, 2014;

Given Title 1 “Patents for invention” of Book XI of the Code of Economic Law, article XI.24, for patent applications introduced from September 22, 2014;

Having regard to the Royal Decree of 2 December 1986 relating to the request, the issue and the maintenance in force of invention patents, article 28;

Considering the patent application received by the Intellectual Property Office on 04/11/2016.

Whereas for patent applications falling within the scope of Title 1, Book XI of the Code of Economic Law (hereinafter CDE), in accordance with article XI. 19, §4, paragraph 2, of the CDE, if the patent application has been the subject of a search report mentioning a lack of unity of invention within the meaning of §ler of article XI.19 cited above and in the event that the applicant does not limit or file a divisional application in accordance with the results of the search report, the granted patent will be limited to the claims for which the search report has been drawn up.

Stopped :

First article. - It is issued to

SONACASA, Route Nationale 5, 6041 GOSSELIES Belgium;

represented by

AHNER Philippe, Brevalex Rue d'Amsterdam 95, 75378, PARIS CEDEX 8;

a Belgian invention patent with a duration of 20 years, subject to payment of the annual fees referred to in article XI.48, §1 of the Code of Economic Law, for: AIRCRAFT WING INCLUDING AN ONBOARD MOBILE COMPONENT LEAKAGE DRIVEN BY A LINEAR ELECTRIC MOTOR.

INVENTOR (S):

LANGER Hugues, Boulevard Frère Orban 28/71, 4000, LIEGE;

SCIARRABONE Steve, Rue Didi 13, 6060, GILLY;

DEBAISIEUX Stéphane, Rue Cupis de Camargo 6, 1495, SART DAMES AVELINES;

PRIORITY (S):

DIVISION:

divided from the basic application: filing date of the basic application:

Article 2. - This patent is granted without prior examination of the patentability of the invention, without guarantee of the merit of the invention or of the accuracy of the description thereof and at the risk and peril of the applicant (s) ( s).

Brussels, 11/01/2018, By special delegation:

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AIRCRAFT WING COMPRISING A MOBILE LEAF OF EDGE TRAINED BY

A LINEAR ELECTRIC MOTOR

DESCRIPTION

TECHNICAL AREA

The present invention relates to the field of aircraft wings, of the type comprising a fixed central wing body carrying one or more movable trailing edge flaps, also called "flaps". The invention relates to all types of mobile trailing edge flaps, for example the so-called "single slot", "double slots", "fixed vane", etc.

It is noted that the invention applies to all types of aircraft, such as a flying wing, an airplane with a tail fuselage engine, a supersonic aircraft, etc.

STATE OF THE PRIOR ART

On aircraft, each of the two wings of the airfoil is generally equipped with high lift mobile flaps, mounted at the leading edge and at the trailing edge of the wing.

In known manner, the flaps are deployed for the landing and take-off phases in order to increase the lift at low or medium speed. Furthermore, in cruising flight at high speed, the movable flaps are retracted to limit the resistance to advancement of the aircraft. In addition, still in a manner known to those skilled in the art, the movement of each flap is carried out using means housed essentially in a front or rear part of a fixed central wing body, as is notably known from document EP 0 818 387.

These means make it possible to move each movable trailing edge flap along a desired path relative to the fixed central wing body, between a retracted position in which the flap substantially matches the fixed body, and a deployed position in which this flap is moved. rearward.

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More specifically, each movable trailing edge flap is equipped with a device ensuring its setting in motion. This device is generally based on complex kinematics, comprising a drive shaft extending along the span of the wing, and driving in rotation a connecting rod-crank system connected to a fitting secured to a movable trailing edge flap.

Although this configuration is very widespread on aircraft wings, the proposed design remains perfectible, in particular as regards the size of the movement setting device, but also its mass, its reliability as well as its precision.

STATEMENT OF THE INVENTION

The invention therefore aims to at least partially remedy the drawbacks mentioned above, relating to the embodiments of the prior art.

To do this, the invention firstly relates to an aircraft wing comprising a fixed central wing body, as well as at least one movable trailing edge flap intended to be moved relative to said fixed central body between a deployed position and a retracted position, the wing comprising a device for setting in motion the movable trailing edge flap, said device being equipped:

- A beam carrying a guide rail, the beam being secured to the fixed central wing body;

- a carriage mounted mobile on said guide rail;

- a first articulated connection between the carriage and a fitting secured to the movable trailing edge flap;

- a tilting member of the movable trailing edge flap;

- a second articulated connection between the fitting and the tilting member; and

- a third articulated connection between the tilting member and the beam.

According to the invention, said device for setting in motion also comprises a linear electric motor comprising:

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- A primary assembly equipped with said carriage which comprises coils, the primary assembly being movably mounted on the rail; and

- a secondary assembly comprising a magnetic path arranged on the guide rail.

The invention thus lies in the clever and innovative integration of a linear electric motor within the wing, in order to ensure the setting in motion of the movable flap of the trailing edge. The movement of the carriage is thus carried out directly, thanks to the judicious installation of the magnetic track on the guide rail and the installation of the coils in the carriage. This makes it possible to reduce the mass and the size of the device for setting in motion, while also reducing the geometric constraints of implantation of this device as well as the maintenance requirements. In addition, the elimination of mechanical transmission elements makes it possible to reduce the noise nuisance and reinforces the reliability and the lifespan of the device for setting in motion, which also offers excellent precision.

In addition, the invention offers the possibility of electronic control which provides additional operating flexibility compared to the embodiments of the prior art. In particular, a check can be carried out dynamically during the takeoff and landing flight phases, and possibly during the cruising phase, in combination with sensors and a system for controlling the quality of the aerodynamic flow around the surfaces. bearing. It is also possible to control the speed of movement of the flaps, with the positive consequence of a possible gain in aerodynamic performance. Also, the integration of the function for identifying the position of the carriage (s) in the electromagnetic system makes it possible in particular to detect possible cases of blockage.

In this regard, it is noted that this electronic control also makes it possible to remove the existing systems of control and correction of offset (from the English “skew sensor”), which contributes to the reduction of the overall mass of the setting device. moving.

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Finally, it is specified that the proposed design adapts perfectly to existing solutions, which can be modified accordingly to benefit from all the advantages offered by the invention.

Preferably, the tilting member is a connecting rod.

Preferably, the articulated connections have axes of articulation parallel to each other, and orthogonal to said guide rail.

Finally, the invention also relates to an aircraft comprising at least one wing as described above, this same wing preferably being equipped with several movable trailing edge flaps.

Other advantages and characteristics of the invention will appear in the detailed non-limiting description below.

BRIEF DESCRIPTION OF THE DRAWINGS

This description will be made with reference to the accompanying drawings, among which;

- Figure 1 shows a perspective view of an aircraft;

- Figure 2 shows a schematic and partial sectional view of an aircraft wing according to the present invention, provided with a movable trailing edge flap;

- Figure 3 shows a partial perspective view of the movable trailing edge flap shown in Figure 2; and

- Figure 4 shows an enlarged view of the previous one, showing more precisely the device for moving the movable flap of the trailing edge.

DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS

Referring firstly to FIG. 1, there is shown an aircraft 1 having a wing 2 made up of a plurality of wing elements, also called bearing aerodynamic surfaces.

In all the description which follows, the terms “front” and “rear” are to be considered in relation to a direction of advance of the aircraft

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BE2016 / 5823 encountered following the thrust exerted by the engines of the aircraft, this direction being represented schematically by arrow 3.

Among the wing elements of the aircraft 1, there are provided two main wings, called wings 4, a vertical fin 6, as well as two horizontal tail units 7 located at the rear of this aircraft.

As regards the wings 4, as mentioned above, these each comprise a fixed central wing body 8, also called the main central portion, this body constituting almost the entire wing, and being located in rear of a leading edge 10. In all the description which follows, by convention, X corresponds to the longitudinal direction of leading edge or again direction of span, Y corresponds to the direction oriented transversely with respect to the edge d attack 10, and the direction Z corresponds to the vertical direction, these three directions being orthogonal to one another.

As schematically shown in Figure 2, it is the trailing edge 11 of each of the two wings 4, opposite the leading edge, which can be equipped with at least one movable trailing edge flap 16, called "Flap " It can be any type of movable trailing edge flaps, for example the so-called “single slot”, “double slots”, “fixed vane” flaps, etc.

Each of these components 16 is intended to be connected to the body 8 by means which will be detailed below. In this FIG. 2, it is shown that the movable trailing edge flap 16 (shown diagrammatically) can occupy a retracted / retracted position in which it is flush with the front part of the fixed central body 8 of the wing 4.

In such a case, the movable flap 16 is in its most forward position. In addition, the movable flap 16 can occupy a fully deployed position where it is distant towards the rear of the fixed central body 8, this fully deployed position being adopted in particular during the landing and take-off phases in order to increase the lift at low or medium speed. This flap 16 is of course designed to be moved between these two extreme positions, for example so as to make it adopt an intermediate take-off position, known to those skilled in the art.

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As an indication, the movable flap 16 extends for example over substantially the entire length of the wing 4 concerned, of course along the span direction of this wing 4, or else only over only a portion of this wing, as this is most common on aircraft.

As can be seen in FIGS. 3 and 4, the flap 16 comprises an aerodynamic coating defining a lower surface portion 24 as well as an upper surface portion 26, the latter ending in a trailing edge 27 of the flap. Still with reference to FIGS. 3 and 4, the wing comprises a device for setting in motion the mobile trailing edge flap 16, this device 50 making it possible to move the latter relative to the body 8, backwards and downwards between the fully extended position, and the retracted position.

The movement setting device 50 firstly comprises a beam 51 extending substantially in the direction Y. This beam 51 is integral with the central body 8, for example by being fixed to the rear spar 32 of this central body in box form. . On the upper part, the beam 51 is equipped with a guide rail 20 arranged in a transverse plane of the flap, and extending in the same direction as the beam which supports it. In the preferred case where several fixed rails 20 are provided, these are then spaced from each other in the span direction X.

The rail 20, preferably straight, guides a carriage 52a which is an integral part of the movement device 50. One end of the carriage opposite to that guided by the rail 20 is mounted on a flap fitting 30, extending under the covering. lower surface, in direction Y. A first articulated connection 40a is arranged between the movable carriage 52a and the rear of the fitting 30, with a hinge axis substantially oriented in the direction X.

At the rear of the shutter fitting 30, a shutter tilting member 29 is provided, taking the form of a connecting rod oriented substantially in the direction Z when the movable shutter 16 occupies its retracted position. A second articulated link 40b is arranged between the rear end of the beam 30 and the upper end of the connecting rod 29, with an articulation axis which is also substantially oriented in the direction X.

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Finally, a third articulated link 40c is arranged between the lower end of the connecting rod 29 and a rear end of the beam 51, with an articulation axis which is also substantially oriented in the direction X. The three articulation axes are thus substantially parallel to each other, and orthogonal to the direction Y along which the guide rail 20 extends.

Thus, when the carriage 52a is moved rearward on the rail 20, the connecting rod 29 pivots around its lower end and drives downwards, via its upper end, the movable trailing edge flap 16.

One of the features of the invention resides in the means for setting in motion the carriage 52a, which are produced by a linear electric motor 22 directly driving this carriage 52a.

The linear electric motor 22 therefore forms an integral part of the movement setting device 50, comprising a movable primary assembly 52 secured to the movable flap 16 and equipped with the movable carriage 52a integrating coils 55. In addition, the motor 22 comprises a secondary assembly fixed 54 comprising a magnetic channel arranged on the guide rail 20. The permanent magnets 54a of this magnetic channel are thus spaced from one another along the rail 20 on which they are fixed.

It is noted that several guide rails 20, associated with the same flap 16, can be equipped with such a linear motor.

It is also noted that the maintenance of the device in the various deployed positions and in the retracted position is for example ensured either by the device 50 itself, or by additional devices with mechanical, electromechanical, electronic, magnetic, electromagnetic, etc. control.

Of course, various modifications can be made by those skilled in the art to the invention which has just been described, only by way of nonlimiting examples.

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Claims (7)

1. Aircraft wing (4) comprising a fixed central wing body (8), as well as at least one movable trailing edge flap (16) intended to be moved relative to said fixed central body between a deployed position and a retracted position, the wing comprising a device (50) for setting in motion the movable trailing edge flap, said device (50) being equipped: - A beam (51) carrying a guide rail, the beam being secured to the fixed central wing body (8); - a carriage (52a) mounted movably on said guide rail (20); - a first articulated connection (40a) between the carriage (52a) and a fitting (30) secured to the movable trailing edge flap; - a tilting member (29) of the movable trailing edge flap; - a second articulated connection (40b) between the fitting (30) and the tilting member (29); and - a third articulated link (40c) between the tilting member (29) and the beam (51), characterized in that said movement device (50) also comprises a linear electric motor (22) comprising: - A primary assembly (52) equipped with said carriage (52a) which incorporates coils (55), the primary assembly being movably mounted on the rail (20); and - A secondary assembly (54) comprising a magnetic path arranged on the guide rail (20). 2. Aircraft wing according to the preceding claim, characterized in that the tilting member (29) is a connecting rod. 3. Aircraft wing according to claim 1 or claim 2, characterized in that the articulated connections (40a-40c) have axes of articulation parallel to each other, and orthogonal to said guide rail (20). S61401 AP-P BE2016 / 5823 4. Aircraft (1) comprising at least one wing (4) according to any one of the preceding claims. S.61401 BE2016 / 5823 BE2016 / 5823 S61401 AP-P BE2016 / 5823 AIRCRAFT WING COMPRISING A MOBILE LEAF OF EDGE TRAINED BY A LINEAR ELECTRIC MOTOR 5 ABSTRACT DESCRIPTION The invention relates to an aircraft wing comprising a movable trailing edge flap (16), the wing comprising a device (50) for setting in motion this flap, ie device being equipped: 10 - a beam (51) carrying a guide rail; - a carriage (52a) mounted mobile on the rail (20); - an articulated connection (40a) between the carriage (52a) and a fitting (30) integral with the flap; - a tilting member (29) of the movable flap; 15 - an articulated connection (40b) between the fitting (30) and the tilting member (29); and - An articulated connection (40c) between the tilting member (29) and the beam (51). According to the invention, the device (50) comprises a linear electric motor (22) comprising a primary assembly (52) equipped with the carriage (52a) which integrates coils (55), and a secondary assembly (54) comprising a magnetic track arranged on the rail (20).