Aircraft flap or slat drive system with redundant drives and shaft drive lines

• US 20050029407A1
• Filed: 06/14/2004
• Published: 02/10/2005
• Est. Priority Date: 06/13/2003
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Deutschland GmbH (Airbus SE)
• Inventors: Pohl, Ulrich, Thomas, Carsten
• Granted Patent: US 7,051,975 B2
• Time in Patent Office: Days
• US Class Current: 244/221
• CPC Class Codes: B64C 13/24 Transmitting means
• CPC Class Codes: B64C 9/16 at the rear of the wing
• CPC Class Codes: B64D 2045/001 for indicating symmetry of flaps deflection
• CPC Class Codes: B64D 45/0005 Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

An aircraft flap (or slat) drive apparatus includes first and second centralized drive units that respectively rotationally drive first and second drive lines in both wings. The first drive line includes shaft segments connected end-to-end by selectively engageable separating devices. The outboard ends of the first and second drive lines are coupled through one of the separating devices, in each wing. At least one actuator mechanism connects each flap to a respective shaft segment of the first drive line, and converts the drive line rotational motion to a flap translational motion. If a component breaks, jams, or otherwise fails, it is isolated by disengaging the two adjacent separating devices with the faulty component therebetween, so that the rest of the apparatus remains functional. Each one or both of the drive units can drive one or more or all of the flaps through the interconnected first and second drive lines.

Claims

1. An apparatus for actuating lift enhancing elements selected from trailing edge flaps and leading edge slats on left and right lifting wings of an aircraft, comprising:

a first centralized drive unit;

a left first rotational shaft drive line that is mechanically connected to and rotationally drivable by and extends leftwardly from said first centralized drive unit along said left lifting wing;

a right first rotational shaft drive line that is mechanically connected to and rotationally drivable by and extends rightwardly from said first centralized drive unit along said right lifting wing;

plural actuator mechanisms that are mechanically interconnected between said first rotational shaft drive lines and said lift enhancing elements on said wings, and that are adapted to convert a rotational motion of said drive lines to a translational motion that is applied by said actuator mechanisms to said lift enhancing elements;

plural drive line separating devices that are interposed in said first rotational shaft drive lines respectively at locations between respective ones of said actuator mechanisms connected to adjacent ones of said lift enhancing elements on each of said wings, and that are each adapted to selectively couple and separate respective portions of said first rotational shaft drive line on opposite sides thereof, wherein said drive line separating devices couple said respective portions of said first rotational shaft drive lines in a normal operating condition;

a second centralized drive unit;

a left second rotational shaft drive line that is mechanically connected to and rotationally drivable by and extends leftwardly from said second centralized drive unit along said left lifting wing;

a right second rotational shaft drive line that is mechanically connected to and rotationally drivable by and extends rightwardly from said second centralized drive unit along said right lifting wing;

wherein said first and second centralized drive units are coupled with one another via said first and second rotational shaft drive lines in such a manner so that said lift enhancing elements are respectively driven by a respective one of said drive lines and each one of said drive lines is connected at a respective end thereof with said centralized drive units.

2. The apparatus according to claim 1, further comprising a controller that comprises a regulation algorithm, and that is connected to said centralized drive units and adapted to control said centralized drive units according to said regulation algorithm so as to distribute a total drive load between said centralized drive units.

3. The apparatus according to claim 1, wherein in a fault operating condition in which a faulty component of said apparatus suffers a local mechanical fault, said drive line separating devices located adjacent to and on opposite sides of said faulty component are adapted to separate said portion of said drive line therebetween from remaining portions of said drive line so as to isolate said faulty component.

4. The apparatus according to claim 3, further comprising a brake arrangement connected to and adapted to selectively arrest at least one of said portion of said drive line and said faulty component that has been isolated.

5. The apparatus according to claim 1, wherein said two adjacent ones of said drive line separating devices are located with at least two of said lift enhancing elements and associated ones of said actuator mechanisms arranged therebetween.

6. In an aircraft including a fuselage, left and right lifting wings extending from said fuselage, lift enhancing elements selected from flaps movably arranged on trailing edges of said wings and slats movably arranged on leading edges of said wings, and a drive system connected to and adapted to selectively actuate said lift enhancing elements,

an improvement in said drive system comprising:

a first centralized drive unit;

a left first drive line that is mechanically connected to and rotationally drivable by and extends leftwardly from said first centralized drive unit along said left wing, and that includes plural left drive shaft segments arranged successively end-to-end;

a right first drive line that is mechanically connected to and rotationally drivable by and extends rightwardly from said first centralized drive unit along said right wing, and that includes plural right drive shaft segments arranged successively end-to-end;

plural actuator mechanisms, wherein at least a respective one of said actuator mechanisms is mechanically interconnected between each one of said lift enhancing elements and a respective one of said drive shaft segments, and wherein said actuator mechanisms are adapted to convert and transmit a rotational motion of said drive shaft segments to an actuating motion of said lift enhancing elements;

plural drive line separating devices that are respectively interposed between and selectively connect and disconnect respective adjacent ends of said drive shaft segments;

a second centralized drive unit;

a left second drive line that is mechanically connected to and rotationally drivable by and extends leftwardly from said second centralized drive unit along said left wing;

a right second drive line that is mechanically connected to and rotationally drivable by and extends rightwardly from said second centralized drive unit along said right wing; and

additional drive line separating devices that are respectively interposed between and selectively connect and disconnect respective outboard ends of said first and second drive lines.

7. The improvement in the drive system in the aircraft according to claim 6, wherein each one of said lift enhancing elements is respectively connected by at least one of said actuator mechanisms to a respective one of said drive shaft segments between two successive ones of said drive line separating devices.

8. The improvement in the drive system in the aircraft according to claim 6, wherein at least two of said lift enhancing elements are connected by at least two of said actuator mechanisms to a respective one of said drive shaft segments between two successive ones of said drive line separating devices.

9. The improvement in the drive system in the aircraft according to claim 6, wherein said first and second drive lines are connected with one another only at said outboard ends thereof and only via said additional drive line separating devices.

10. The improvement in the drive system in the aircraft according to claim 6, wherein said first and second centralized drive units are arranged in said fuselage, inboard ends of said first drive lines are mechanically connected to said first centralized drive unit, and inboard ends of said second drive lines are mechanically connected to said second centralized drive unit.