Aircraft flap system with aileron functionality

Patent metadata

Field	Value
Publication number	US-2015191240-A1
Application number	US-201414285712-A
Country	US
Kind code	A1
Filing date	May 23, 2014
Priority date	May 28, 2013
Publication date	Jul 9, 2015
Grant date	—

Abstract

The present disclosure pertains to an actuation mechanism for a flap with aileron functionality, including a crank having a crank axle, a crank arm and a crank pivot; a displacement shaft articulated to the crank pivot at an actuating end portion; and a rotatable linear-motion bearing in which the displacement shaft is slidably supported, wherein the displacement shaft is fixedly connectable to a flap body of the aircraft flap at a flap end portion of the displacement shaft opposite to the actuating end portion, and wherein the linear-motion bearing is rotatably attachable at a pivot point to an aircraft wing comprising the aircraft flap, so that the displacement shaft is able to rotate around an axis running spanwise of the aircraft wing around the pivot point. The present disclosure further pertains to an aircraft flap with such an actuation mechanism and an aircraft having an aircraft flap.

First claim

What is claimed is:

1 . An actuation mechanism for an aircraft flap with aileron functionality, comprising:
a crank having a crank axle, a crank arm and a crank pivot; a displacement shaft articulated to the crank pivot at an actuating end portion; and a rotatable linear-motion bearing in which the displacement shaft is slidably supported, wherein the displacement shaft is fixedly connectable to a flap body of the aircraft flap at a flap end portion of the displacement shaft opposite to the actuating end portion, and wherein the linear-motion bearing is rotatably attachable at a pivot point to an aircraft wing comprising the aircraft flap, so that the displacement shaft is able to rotate around an axis running spanwise of the aircraft wing around the pivot point.

2 . The actuation mechanism according to claim 1 , wherein the linear-motion bearing is a spherical plain bearing or a spherical rolling element bearing.

3 . The actuation mechanism according to claim 1 , wherein the crank is actuated by a linear actuator, in particular a hydraulic actuator, a pneumatic actuator, a rack and pinion drive actuator, a spindle actuator or a chain drive actuator.

4 . The actuation mechanism according to claim 1 , wherein the crank is actuated by a rotary actuator, in particular a hydraulic rotary actuator, a pneumatic rotary actuator or a mechanical rotary actuator.

5 . An aircraft flap with aileron functionality, comprising:
a flap body; and an actuation mechanism according to claim 1 , wherein the displacement shaft is fixedly connected to a flap body of the aircraft flap at the flap end portion of the displacement shaft.

6 . The aircraft flap according to claim 5 , further comprising:
a rotary vane fixedly attached to the linear-motion bearing, wherein the outer surface of the rotary vane proximate to the flap body has a contour substantially conforming to the contour of the flap body.

7 . The aircraft flap according to claim 6 , wherein the rotary vane comprises an outer surface distal to the flap body which has a contour substantially conforming to the contour of the aircraft wing.

8 . The aircraft flap according to claim 6 further comprising:
a hinged aerofoil edge portion hingably attachable to a downside surface of the aircraft wing.

9 . The aircraft flap according to claim 8 , wherein the hinged aerofoil edge portion is connected to the outer surface of the rotary vane proximate to the flap body by a linear slide bearing.

10 . The aircraft flap according to claim 5 , wherein the crank arm in actuatable in such a way, that the displacement shaft is pivotable around the pivot point of the linear-motion bearing within a range between a maximum negative pivot angle and a maximum positive pivot angle with respect to a neutral position of the displacement shaft.

11 . The aircraft flap according to claim 10 , wherein the neutral position of the displacement shaft corresponds to a cruise flight position of the aircraft flap.

12 . The aircraft flap according to claim 10 , wherein the maximum negative pivot angle corresponds to a maximum banking control position of the aircraft flap, and wherein the maximum positive pivot angle corresponds to a maximum lift assistance position of the aircraft flap.

13 . An aircraft, comprising:
at least one aircraft wing; and at least one aircraft flap with aileron functionality according to claim 5 , the flap being arranged at a trailing edge of the aircraft wing.

14 . The aircraft according to claim 13 , wherein the pivot point of the linear-motion bearing is located within the outer profile of the aircraft wing.

15 . The aircraft according to claim 13 , wherein the aircraft comprises a plurality of aircraft flaps with aileron functionality, all of which are used both as landing flaps and as ailerons.

Assignees

• Airbus Operations Gmbh

Inventors

• Burchard Alexander

Classifications

• B64C9/18 Primary

  by single flaps · CPC title

• Y10T74/18216

  Crank, lever, and slide · CPC title

• B64C9/16

  at the rear of the wing · CPC title

• B64C9/04

  with compound dependent movements · CPC title

• B64C2009/005

  Ailerons · CPC title