CA3042316A1 - Aircraft wing comprising a movable trailing-edge flap driven by a linear electric motor - Google Patents
Aircraft wing comprising a movable trailing-edge flap driven by a linear electric motor Download PDFInfo
- Publication number
- CA3042316A1 CA3042316A1 CA3042316A CA3042316A CA3042316A1 CA 3042316 A1 CA3042316 A1 CA 3042316A1 CA 3042316 A CA3042316 A CA 3042316A CA 3042316 A CA3042316 A CA 3042316A CA 3042316 A1 CA3042316 A1 CA 3042316A1
- Authority
- CA
- Canada
- Prior art keywords
- wing
- flap
- trailing edge
- carriage
- edge flap
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 230000008901 benefit Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 238000005253 cladding Methods 0.000 description 2
- 230000010354 integration Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000009347 mechanical transmission Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K41/00—Propulsion systems in which a rigid body is moved along a path due to dynamo-electric interaction between the body and a magnetic field travelling along the path
- H02K41/02—Linear motors; Sectional motors
- H02K41/03—Synchronous motors; Motors moving step by step; Reluctance motors
- H02K41/031—Synchronous motors; Motors moving step by step; Reluctance motors of the permanent magnet type
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K7/00—Arrangements for handling mechanical energy structurally associated with dynamo-electric machines, e.g. structural association with mechanical driving motors or auxiliary dynamo-electric machines
- H02K7/14—Structural association with mechanical loads, e.g. with hand-held machine tools or fans
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Electromagnetism (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
- Linear Motors (AREA)
Abstract
The invention relates to an aircraft wing comprising a mobile trailing edge flap (16), the wing comprising a device (50) for moving said flap, the device being provided with: a beam (51) supporting a guide rail; a carriage (52a) movably mounted on the rail (20); a rotary joint (40a) between the carriage (52a) and a bracket (30) rigidly connected to the flap; a tilt member (29) for tilting the mobile flap; a rotary joint (40b) between the bracket (30) and the tilt member (29); and a rotary joint (40c) between the tilt member (29) and the beam (51). According to the invention, the device (50) comprises a linear electric motor (22) including: a primary assembly (52) provided with the carriage (52a), which includes coils (55); and a secondary assembly (54) including a magnetic track arranged on the rail (20).
Description
I I
AIRCRAFT WING COMPRISING A MOVABLE TRAILING-EDGE FLAP DRIVEN BY A LINEAR
ELECTRIC MOTOR
DESCRIPTION
TECHNICAL FIELD
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.
The invention relates to all types of movable trailing edge flaps, for example the so-called "single slot", "double slot", "fixed vane", flaps, etc.
It should be noted that the invention applies to all types of aircraft, such as flying-wing aircraft, aft-engined aeroplanes, a supersonic aircraft, etc.
PRIOR ART
On aircraft, each of the two wings of the wing unit is generally equipped with lift-increasing movable flaps, mounted at the leading edge and at the trailing edge of the wing.
In a known fashion, the flaps are deployed for the landing and takeoff phases in order to increase the lift at low or medium speed. Moreover, in cruising flight at high speed, the movable flaps are retracted in order to limit the resistance to the forward travel of the aircraft. In addition, so as known to persons skilled in the art, each flap is moved using means housed mainly in a front or rear part of the fixed central wing body, as is in particular known from the document EP 0 818 387.
These means make it possible to move each movable trailing edge flap on a required path with respect to the central fixed wing body, between a retracted position in which the flap substantially follows the shape of the fixed body, and a deployed position in which this flap is moved towards the rear.
More precisely, each movable trailing edge flap is equipped with a device for moving it. This device is generally based on a complex kinematics, comprising a drive shaft extending along the breadth of the wing, and rotating a rod/crank system connected to a brace secured to the movable trailing edge flap.
AIRCRAFT WING COMPRISING A MOVABLE TRAILING-EDGE FLAP DRIVEN BY A LINEAR
ELECTRIC MOTOR
DESCRIPTION
TECHNICAL FIELD
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.
The invention relates to all types of movable trailing edge flaps, for example the so-called "single slot", "double slot", "fixed vane", flaps, etc.
It should be noted that the invention applies to all types of aircraft, such as flying-wing aircraft, aft-engined aeroplanes, a supersonic aircraft, etc.
PRIOR ART
On aircraft, each of the two wings of the wing unit is generally equipped with lift-increasing movable flaps, mounted at the leading edge and at the trailing edge of the wing.
In a known fashion, the flaps are deployed for the landing and takeoff phases in order to increase the lift at low or medium speed. Moreover, in cruising flight at high speed, the movable flaps are retracted in order to limit the resistance to the forward travel of the aircraft. In addition, so as known to persons skilled in the art, each flap is moved using means housed mainly in a front or rear part of the fixed central wing body, as is in particular known from the document EP 0 818 387.
These means make it possible to move each movable trailing edge flap on a required path with respect to the central fixed wing body, between a retracted position in which the flap substantially follows the shape of the fixed body, and a deployed position in which this flap is moved towards the rear.
More precisely, each movable trailing edge flap is equipped with a device for moving it. This device is generally based on a complex kinematics, comprising a drive shaft extending along the breadth of the wing, and rotating a rod/crank system connected to a brace secured to the movable trailing edge flap.
2 Although this configuration is very widespread on aircraft wings, the design proposed can still be improved, in particular with regard to the size of the movement device, but also its weight, reliability and precision.
DISCLOSURE OF THE INVENTION
The aim of the invention is therefore to at least partially remedy the drawbacks mentioned above, relating to the embodiments of the prior art.
To do this, the subject matter of the invention is first of all an aircraft wing comprising a central fixed wing body, and at least one movable trailing edge flap intended to be moved in relation to said central fixed body between a deployed position and a retracted position, the wing comprising a device for moving the movable trailing edge flap, said device being equipped with:
- a beam carrying a guide rail, the beam being secured to the central fixed wing body;
- a carriage mounted so as to move on said guide rail;
- a first articulated connection between the carriage and a brace secured to the movable trailing edge flap;
- a member for tilting the movable trailing edge flap;
- a second articulated connection between the brace and the tilting member; and - a third articulated connection between the tilting member and the beam.
According to the invention, said movement device also comprises a linear electric motor comprising:
- a primary assembly equipped with said carriage that comprises coils, the primary assembly being mounted so as to move on the rail; and - a secondary assembly comprising a magnetic track arranged on the guide rail.
The invention thus lies in the clever and innovative integration of a linear electric motor in the wing, in order to provide the movement of the movable trailing edge flap. The carriage is thus moved in a direct manner, by virtue of the clever installation of
DISCLOSURE OF THE INVENTION
The aim of the invention is therefore to at least partially remedy the drawbacks mentioned above, relating to the embodiments of the prior art.
To do this, the subject matter of the invention is first of all an aircraft wing comprising a central fixed wing body, and at least one movable trailing edge flap intended to be moved in relation to said central fixed body between a deployed position and a retracted position, the wing comprising a device for moving the movable trailing edge flap, said device being equipped with:
- a beam carrying a guide rail, the beam being secured to the central fixed wing body;
- a carriage mounted so as to move on said guide rail;
- a first articulated connection between the carriage and a brace secured to the movable trailing edge flap;
- a member for tilting the movable trailing edge flap;
- a second articulated connection between the brace and the tilting member; and - a third articulated connection between the tilting member and the beam.
According to the invention, said movement device also comprises a linear electric motor comprising:
- a primary assembly equipped with said carriage that comprises coils, the primary assembly being mounted so as to move on the rail; and - a secondary assembly comprising a magnetic track arranged on the guide rail.
The invention thus lies in the clever and innovative integration of a linear electric motor in the wing, in order to provide the movement of the movable trailing edge flap. The carriage is thus moved in a direct manner, by virtue of the clever installation of
3 the magnetic track on the guide rail and the installation of the coils in the carriage. This makes it possible to reduce the weight and size of the movement device, while also reducing the geometric constraints of installation of this device as well as the maintenance requirements. In addition, the omission of mechanical transmission elements reduces the noise nuisances and reinforces the reliability and service life of the movement device, which moreover offers excellent precision.
Furthermore, the invention offers the possibility of electronic control that procures additional flexibility in functioning compared with the embodiments of the prior art. In particular, control may be carried out dynamically during takeoff and landing flight phases, and optionally in cruising phase, in association with sensors and a system for controlling the quality of the aerodynamic flow around the lift surfaces.
The speed of movement of the flaps can also be controlled with the positive consequence of a possible gain in aerodynamic performance. Equally, integrating the function of identification of the position of the carriage or carriages in the electromagnetic system makes it possible in particular to detect any cases of blockage.
In this regard, it should be noted that this electronic control also makes it possible to eliminate the existing skew control and correction (skew sensor) systems, which helps to reduce the overall weight of the movement device.
Finally, it is stated that the design proposed adapts perfectly to the existing solutions, which can be modified accordingly in order to benefit from all the advantages offered by the invention.
Preferably, the tilting member is a connecting rod.
Preferably, the articulated connections have articulation axes parallel to each other, and orthogonal to said guide rail.
Finally, another subject matter of the invention is an aircraft comprising at least one wing as described above, the same wing preferentially being equipped with a plurality of movable trailing edge flaps.
Other advantages and features of the invention will emerge from the following non-limitative detailed description.
Furthermore, the invention offers the possibility of electronic control that procures additional flexibility in functioning compared with the embodiments of the prior art. In particular, control may be carried out dynamically during takeoff and landing flight phases, and optionally in cruising phase, in association with sensors and a system for controlling the quality of the aerodynamic flow around the lift surfaces.
The speed of movement of the flaps can also be controlled with the positive consequence of a possible gain in aerodynamic performance. Equally, integrating the function of identification of the position of the carriage or carriages in the electromagnetic system makes it possible in particular to detect any cases of blockage.
In this regard, it should be noted that this electronic control also makes it possible to eliminate the existing skew control and correction (skew sensor) systems, which helps to reduce the overall weight of the movement device.
Finally, it is stated that the design proposed adapts perfectly to the existing solutions, which can be modified accordingly in order to benefit from all the advantages offered by the invention.
Preferably, the tilting member is a connecting rod.
Preferably, the articulated connections have articulation axes parallel to each other, and orthogonal to said guide rail.
Finally, another subject matter of the invention is an aircraft comprising at least one wing as described above, the same wing preferentially being equipped with a plurality of movable trailing edge flaps.
Other advantages and features of the invention will emerge from the following non-limitative detailed description.
4 BRIEF DESCRIPTION OF THE DRAWINGS
This description will be given with regard to the accompanying drawings, among which:
- figure 1 shows a perspective view of aircraft;
- figure 2 shows a schematic partial view in cross-section 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 above, showing more precisely the device for moving the movable trailing edge flap.
DETAILED DISCLOSURE OF PREFERRED EMBODIMENTS
With reference first of all to figure 1, an aircraft 1 is shown, having a wing unit 2 consisting of a plurality of wing elements, also referred to as lift-providing aerodynamic surfaces.
Throughout the following description, the terms "front" and "rear" are to be considered with respect to a direction of forward travel of the aircraft encountered following the thrust exerted by the aircraft engines, this direction being represented schematically by the arrow 3.
Among the wing elements of the aircraft 1, there are provided two main wings, referred to as wings 4, a vertical rudder 6, and two horizontal tail units 7 situated at the rear of this aircraft.
With regard to the wings 4, as mentioned above, these each comprise a fixed central wing body 8, also referred to as the main central portion, this body constituting almost the whole of the wing, and being situated at the rear of a leading edge 10. Throughout the following description, by convention, X corresponds to the longitudinal leading edge direction or span direction, Y corresponds to the direction oriented transversely with respect to the leading edge 10, and the direction Z
corresponds to the vertical direction, these three directions being orthogonal to each other.
As shown schematically in figure 2, it is the trailing edge 11 of each of these wings 4, opposite to the leading edge, that can be equipped with at least one I I
movable trailing edge flap 16. This may be any type of movable trailing edge flap, for example flaps known as "single slot", "double slot", "fixed vane", etc.
Each of these flaps 16 is intended to be connected to the body 8 by means that will be detailed below. In this figure 2, it is shown that the movable trailing
This description will be given with regard to the accompanying drawings, among which:
- figure 1 shows a perspective view of aircraft;
- figure 2 shows a schematic partial view in cross-section 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 above, showing more precisely the device for moving the movable trailing edge flap.
DETAILED DISCLOSURE OF PREFERRED EMBODIMENTS
With reference first of all to figure 1, an aircraft 1 is shown, having a wing unit 2 consisting of a plurality of wing elements, also referred to as lift-providing aerodynamic surfaces.
Throughout the following description, the terms "front" and "rear" are to be considered with respect to a direction of forward travel of the aircraft encountered following the thrust exerted by the aircraft engines, this direction being represented schematically by the arrow 3.
Among the wing elements of the aircraft 1, there are provided two main wings, referred to as wings 4, a vertical rudder 6, and two horizontal tail units 7 situated at the rear of this aircraft.
With regard to the wings 4, as mentioned above, these each comprise a fixed central wing body 8, also referred to as the main central portion, this body constituting almost the whole of the wing, and being situated at the rear of a leading edge 10. Throughout the following description, by convention, X corresponds to the longitudinal leading edge direction or span direction, Y corresponds to the direction oriented transversely with respect to the leading edge 10, and the direction Z
corresponds to the vertical direction, these three directions being orthogonal to each other.
As shown schematically in figure 2, it is the trailing edge 11 of each of these wings 4, opposite to the leading edge, that can be equipped with at least one I I
movable trailing edge flap 16. This may be any type of movable trailing edge flap, for example flaps known as "single slot", "double slot", "fixed vane", etc.
Each of these flaps 16 is intended to be connected to the body 8 by means that will be detailed below. In this figure 2, it is shown that the movable trailing
5 edge flap 16 (shown schematically) can occupy a retracted/withdrawn position in which it fits flush with the front part of the fixed central body 8 of the wing 4.
In such a case, the movable flap 16 is situated in its furthermost forward position. Likewise, the movable flap 16 can occupy a fully deployed position in which it is at a distance toward the rear of the fixed central body 8, this fully-deployed position being adopted in particular during the landing and takeoff phases in order to increase the lift and at low or medium speed. This flap 16 is of course designed so as to be moved between these two extreme positions, for example so as to cause it to adopt an intermediate takeoff position, known to persons skilled in the art.
By way of indication, the movable flap 16 extends for example over substantially the entire height of the wing 4 concerned, naturally in the span direction of this wing 4, or solely over only a portion of this wing, as is most usual on aircraft.
As can be seen in figures 3 and 4, the flap 16 comprises an aerodynamic cladding defining a lower-face portion 24 and an upper-face portion 26, the latter terminating in a trailing edge 27 of the flap. Still with reference to figures 3 and 4, the wing comprises a device for moving the movable trailing edge flap 16, this device 50 making it possible to move said flap with respect to the body 8, towards the rear and downwards between the fully deployed position and the retracted position.
The movement device 50 comprises first of all the beam 51 extending substantially in the direction Y. This beam 51 is secured to the central body 8, for example by being fixed to the rear longitudinal member 32 of this central body in the form of a box. On the top 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 that supports it. In the preferred case where a plurality of fixed rails 20 are provided, these are then spaced apart from each other in the span direction X.
The rail 20, preferably straight, guides a carriage 52a forming an integral part of the movement device 50. One end of the carriage opposite to the one guided by
In such a case, the movable flap 16 is situated in its furthermost forward position. Likewise, the movable flap 16 can occupy a fully deployed position in which it is at a distance toward the rear of the fixed central body 8, this fully-deployed position being adopted in particular during the landing and takeoff phases in order to increase the lift and at low or medium speed. This flap 16 is of course designed so as to be moved between these two extreme positions, for example so as to cause it to adopt an intermediate takeoff position, known to persons skilled in the art.
By way of indication, the movable flap 16 extends for example over substantially the entire height of the wing 4 concerned, naturally in the span direction of this wing 4, or solely over only a portion of this wing, as is most usual on aircraft.
As can be seen in figures 3 and 4, the flap 16 comprises an aerodynamic cladding defining a lower-face portion 24 and an upper-face portion 26, the latter terminating in a trailing edge 27 of the flap. Still with reference to figures 3 and 4, the wing comprises a device for moving the movable trailing edge flap 16, this device 50 making it possible to move said flap with respect to the body 8, towards the rear and downwards between the fully deployed position and the retracted position.
The movement device 50 comprises first of all the beam 51 extending substantially in the direction Y. This beam 51 is secured to the central body 8, for example by being fixed to the rear longitudinal member 32 of this central body in the form of a box. On the top 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 that supports it. In the preferred case where a plurality of fixed rails 20 are provided, these are then spaced apart from each other in the span direction X.
The rail 20, preferably straight, guides a carriage 52a forming an integral part of the movement device 50. One end of the carriage opposite to the one guided by
6 the rail 20 is mounted on a flap brace 30, extending under the lower-face cladding, in the direction Y. A first articulated connection 40a is arranged between the movable carriage 52a and the rear of the brace 30, with an articulation axis substantially oriented in the direction X.
At the rear of the flap brace 30, a member 29 for tilting the flap is provided, taking the form of a connecting rod oriented substantially in the direction Z
when the movable flap 16 is occupying its retracted position. A second articulated connection 40b is arranged between the rear end of the beam 30 and the top end of the connecting rod 29, with an articulation axis that is also substantially oriented in the direction X.
Finally, a third articulated connection 40c is arranged between the bottom end of the connecting rod 29 and a rear end of the beam 51, with an articulation axis that 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 in which the guide rail 20 extends.
Thus, when the carriage 52a is moved towards the rear on the rail 20, the connecting rod 29 pivots about its bottom end and, via its top end, drives the moving trailing edge flap 16 downwards.
One of the particularities of the invention lies in the means for moving the carriage 52a, which are implemented by a linear electric motor 22 directly driving this carriage 52a.
The linear electric motor 22 therefore forms an integral part of the movement device 50, comprising a primary movable 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 fixed secondary assembly 54 comprising a magnetic track arranged on the guide rail 20. The permanent magnets 54a of this magnetic track are thus spaced apart from each other along the rail 20 on which they are fixed.
It should be noted that a plurality of guide rails 20, associated with the same flap 16, can be equipped with such a linear motor.
It should also be noted that the holding of the device at the various deployed positions and in the retracted position is for example provided either by the I I
At the rear of the flap brace 30, a member 29 for tilting the flap is provided, taking the form of a connecting rod oriented substantially in the direction Z
when the movable flap 16 is occupying its retracted position. A second articulated connection 40b is arranged between the rear end of the beam 30 and the top end of the connecting rod 29, with an articulation axis that is also substantially oriented in the direction X.
Finally, a third articulated connection 40c is arranged between the bottom end of the connecting rod 29 and a rear end of the beam 51, with an articulation axis that 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 in which the guide rail 20 extends.
Thus, when the carriage 52a is moved towards the rear on the rail 20, the connecting rod 29 pivots about its bottom end and, via its top end, drives the moving trailing edge flap 16 downwards.
One of the particularities of the invention lies in the means for moving the carriage 52a, which are implemented by a linear electric motor 22 directly driving this carriage 52a.
The linear electric motor 22 therefore forms an integral part of the movement device 50, comprising a primary movable 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 fixed secondary assembly 54 comprising a magnetic track arranged on the guide rail 20. The permanent magnets 54a of this magnetic track are thus spaced apart from each other along the rail 20 on which they are fixed.
It should be noted that a plurality of guide rails 20, associated with the same flap 16, can be equipped with such a linear motor.
It should also be noted that the holding of the device at the various deployed positions and in the retracted position is for example provided either by the I I
7 device 50 itself, or by additional devices with mechanical, electromechanical, electronic, magnetic, electromagnetic, etc control.
Naturally, various modifications can be made by a person skilled in the art to the invention that has just been described, solely by way of non-limitative examples.
Naturally, various modifications can be made by a person skilled in the art to the invention that has just been described, solely by way of non-limitative examples.
Claims (4)
1. Aircraft wing (4) comprising a central fixed wing body (8), and at least one movable trailing edge flap (16) intended to be moved in relation to said central fixed body between a deployed position and a retracted position, the wing comprising a device (50) for moving the movable trailing edge flap, said device (50) being equipped with:
- a beam (51) carrying a guide rail, the beam being secured to the central fixed wing body (8);
- a carriage (52a) mounted so as to move on said guide rail (20);
- a first articulated connection (40a) between the carriage (52a) and a brace (30) secured to the movable trailing edge flap;
- a member (29) for tilting the movable trailing edge flap;
- a second articulated connection (40b) between the brace (30) and the tilting member (29); and - a third articulated connection (40c) between the tilting member (29) and the beam (51).
characterised in that said movement device (50) also comprises a linear electric motor (22) comprising:
- a primary assembly (52) equipped with said carriage (52a) that includes coils (55), the primary assembly being mounted so as to move on the rail (20);
and - a secondary assembly (54) comprising a magnetic track arranged on the guide rail (20).
- a beam (51) carrying a guide rail, the beam being secured to the central fixed wing body (8);
- a carriage (52a) mounted so as to move on said guide rail (20);
- a first articulated connection (40a) between the carriage (52a) and a brace (30) secured to the movable trailing edge flap;
- a member (29) for tilting the movable trailing edge flap;
- a second articulated connection (40b) between the brace (30) and the tilting member (29); and - a third articulated connection (40c) between the tilting member (29) and the beam (51).
characterised in that said movement device (50) also comprises a linear electric motor (22) comprising:
- a primary assembly (52) equipped with said carriage (52a) that includes coils (55), the primary assembly being mounted so as to move on the rail (20);
and - a secondary assembly (54) comprising a magnetic track arranged on the guide rail (20).
2. Aircraft wing according to the preceding claim, characterised in that the tilting member (29) is a connecting rod.
3. Aircraft wing according to claim 1 or claim 2, characterised in that the articulated connections (40a-40c) have articulation axes parallel to each other and orthogonal to said guide rail (20).
4. Aircraft (1) comprising at least one wing (4) according to any of the preceding claims.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| BE2016/5823A BE1024276B1 (en) | 2016-11-04 | 2016-11-04 | AIRCRAFT WING COMPRISING A MOBILE FLYING LEFT SIDE DRIVEN BY A LINEAR ELECTRIC MOTOR |
| BE2016/5823 | 2016-11-04 | ||
| PCT/EP2017/078003 WO2018083145A1 (en) | 2016-11-04 | 2017-11-02 | Aircraft wing comprising a mobile trailing edge flap driven by a linear electric motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA3042316A1 true CA3042316A1 (en) | 2018-05-11 |
Family
ID=57326131
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA3042316A Pending CA3042316A1 (en) | 2016-11-04 | 2017-11-02 | Aircraft wing comprising a movable trailing-edge flap driven by a linear electric motor |
Country Status (3)
| Country | Link |
|---|---|
| BE (1) | BE1024276B1 (en) |
| CA (1) | CA3042316A1 (en) |
| WO (1) | WO2018083145A1 (en) |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4542869A (en) * | 1983-06-23 | 1985-09-24 | Mcdonnell Douglas Corporation | Flap mechanism |
| US5686907A (en) | 1995-05-15 | 1997-11-11 | The Boeing Company | Skew and loss detection system for individual high lift devices |
| DE102004006940B4 (en) * | 2004-02-12 | 2009-02-26 | Airbus Deutschland Gmbh | Landing flap guide for aircraft |
| DE102006036464B4 (en) * | 2006-08-04 | 2009-08-20 | Airbus Deutschland Gmbh | High-lift system for an aircraft |
| US9281735B2 (en) * | 2012-01-05 | 2016-03-08 | Rensselaer Polytechnic Institute | Flux-switching linear permanent magnet machine with yokeless translator |
| JP2016078584A (en) * | 2014-10-15 | 2016-05-16 | 三菱航空機株式会社 | aircraft |
| CN205610454U (en) * | 2016-04-28 | 2016-09-28 | 深圳线马科技有限公司 | Synchronous linear electric motor of cored permanent magnetism |
-
2016
- 2016-11-04 BE BE2016/5823A patent/BE1024276B1/en active IP Right Grant
-
2017
- 2017-11-02 CA CA3042316A patent/CA3042316A1/en active Pending
- 2017-11-02 WO PCT/EP2017/078003 patent/WO2018083145A1/en active Application Filing
Also Published As
| Publication number | Publication date |
|---|---|
| WO2018083145A1 (en) | 2018-05-11 |
| BE1024276B1 (en) | 2018-01-11 |
| BR112019008662A2 (en) | 2019-07-09 |
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