Crocodile-type flight control surface for aircraft with locking mechanism for additional stiffness

Patent metadata

Field	Value
Publication number	US-10518871-B2
Application number	US-201715651769-A
Country	US
Kind code	B2
Filing date	Jul 17, 2017
Priority date	Jul 18, 2016
Publication date	Dec 31, 2019
Grant date	Dec 31, 2019

Abstract

A crocodile-type flight control surface comprising an upper foil flap, a lower foil flap, an actuating mechanism which guarantees the rotational displacement of each foil flap about a joint axis, either in the same direction or in different directions, and a locking mechanism alternatively adopting a locking position in which the upper foil flap and the lower foil flap are fixed with respect to each other and an unlocking position in which the upper foil flap and the lower foil flap are free with respect to the other. A crocodile-type flight control surface of this kind is therefore stiffened by the locking mechanism that joins the two foil flaps.

First claim

The invention claimed is:

1. A crocodile-type flight control surface comprising:
an upper foil flap,
a lower foil flap,
an actuating mechanism configured to guarantee the rotational displacement of each foil flap about a joint axis, either in the same direction or in different directions, wherein the actuating mechanism comprises:
a first actuator,
a second actuator,
an upper connecting rod fixed at one end to the upper foil flap and at another end to the first actuator and
a lower connecting rod fixed at one end to the lower foil flap and at another end to the second actuator,
the upper connecting rod and the lower connecting rod being mounted in a rotationally movable manner about the shared axis, wherein one of the connecting rods comprises a first shaft, whereas the other connecting rod comprises a second shaft which is hollow and in which is housed said first shaft, and

a locking mechanism alternatively adopting a locking position in which the upper foil flap and the lower foil flap are fixed, with respect to each other, and an unlocking position in which the upper foil flap and the lower foil flap are free, with respect to each other, wherein the locking mechanism comprises:
a plunger cylinder, the cylinder extending the second shaft and a piston extending the first shaft, defining a chamber between the bottom of the cylinder and the piston,
an energy source connected to the chamber and adapted to adopt, alternatively, a pressurized position in which the energy source puts the chamber under pressure and tends to push back the piston from the bottom of the chamber and an unpressurized position in which the energy source does not place the chamber under pressure,
a return travel means which prevents the piston from moving towards the bottom of the chamber, and,
wherein that part of the inner surface of the cylinder takes the shape of a first frustum and part of the outer surface of the piston takes the shape of a second frustum, the two frustums being arranged such that in an unpressurized position corresponding to the locking position, their lateral surfaces are in contact, preventing any movement with respect to the other, and such that in a pressurized position corresponding to the unlocking position, their lateral surfaces are not in contact, allowing movements of one with respect to the other.

2. An aircraft comprising:
a structure; and
at least one crocodile-type flight control surface according to claim 1 fixed to said structure.

3. A control method of a crocodile-type flight control surface according to claim 1 , said control method comprising:
displacing the two foil flaps in the same direction by the actuating mechanism into an angular position during a displacement stage,
applying a force in an overload stage to each foil flap when the foil flaps have reached said angular position, corresponding to an angular deviation tending to bring the foil flaps closer and determined during a fine-tuning stage.

4. A control method of a crocodile-type flight control surface according to claim 1 , said control method comprising:
a fine-tuning stage comprising:
clamping the upper foil flap in an angular reference position during a clamping sub-stage,
applying a force to the lower foil flap during an application sub-stage, said forcing tending to press the lower foil flap against the upper foil flap,
evaluating an angular deviation of the lower foil flap corresponding to the force thereby applied during an evaluation sub-stage,
clamping the lower foil flap in the reference angular position during a clamping sub-stage,
applying a force to the upper foil flap during an application sub-stage, said force tending to press the upper foil flap against the lower foil flap,
evaluating the angular deviation of the first-upper foil flap corresponding to the force thereby applied during an evaluation sub-stage.

Assignees

• Airbus Operations Sas

Inventors

• Robillard Jerome
• Dourel Pierre

Classifications

• B64C13/28 Primary

  mechanical · CPC title

• B64C9/00

  Adjustable control surfaces or members, e.g. rudders (trimming stabilising surfaces B64C5/10) · CPC title

• B64C13/50

  using electrical energy · CPC title

• B64C9/06

  with two or more independent movements · CPC title

• B64C13/40

  using fluid pressure · CPC title