Formvariable aerodynamic fairing body for a flap actuator mechanism of an aircraft

Patent metadata

Field	Value
Publication number	US-10035580-B2
Application number	US-201314089793-A
Country	US
Kind code	B2
Filing date	Nov 26, 2013
Priority date	Nov 30, 2012
Publication date	Jul 31, 2018
Grant date	Jul 31, 2018

Abstract

An aerodynamic fairing body for an aircraft, a corresponding aircraft and a corresponding method of manufacture for an aerodynamic fairing body are described. The fairing body is configured so as to accommodate a flap adjustment mechanism. Further, the fairing body is configured so as to be arranged at a predetermined distance from an engine of the aircraft, which produces a blast which varies depending on the flight phase. Furthermore, the fairing body is configured so as to be varied in shape in such a way that the fairing body is located outside the blast of the engine permanently. In other words, the fairing body can be varied in shape in such a way that it is located outside the engine blast in any flight phase of the aircraft.

First claim

The invention claimed is:

1. An aerodynamic fairing body for an aircraft,
the fairing body being configured so as to accommodate a flap adjustment mechanism;
the fairing body being configured so as to be arranged at a predetermined distance from an engine of the aircraft and near a blast produced by the engine,;
wherein the fairing body is configured to vary between at least one extended state and at least one retracted state;
wherein the fairing body is configured so as to take on the at least one retracted state during at least one of a take-off phase and a landing phase of the aircraft,
wherein the fairing body is configured so as to take on the at least one extended state during a cruising phase of the aircraft thereby reducing the flow resistance of the aircraft, and
wherein the total length of the fairing body in the direction of flight is smaller in the retracted state than in the extended state.

2. An aerodynamic fairing body for an aircraft,
the fairing body being configured so as to accommodate a flap adjustment mechanism;
the fairing body being configured so as to be arranged at a predetermined distance from an engine of the aircraft and near a blast produced by the engine,
wherein the fairing body is configured to vary between at least one extended state and at least one retracted state, and
wherein a variation in a shape of the fairing body from one of the at least one extended state and the at least one retracted state to the other of the at least one extended state and the at least one retracted state is associated with retraction and extension of flaps of the aircraft such that if the flaps are extended, the fairing body is retracted and if the flaps are retracted, the fairing body is extended.

3. The aerodynamic fairing body according to claim 1 , wherein a variation in a shape of the fairing body from one of the at least one extended state and the at least one retracted state to the other of the at least one extended state and the at least one retracted state corresponds to a variation in length of the fairing body in a direction of flight of the aircraft.

4. The aerodynamic fairing body according to claim 1 , wherein the fairing body comprises a front module and a rear module; and
wherein a variation in a shape of the fairing body is brought about by adjusting the rear module with respect to the front module.

5. The aerodynamic fairing body according to claim 4 , wherein the front module is configured so as to receive the rear module.

6. The aerodynamic fairing body according to claim 4 , further comprising:
a rail element;
wherein the front module is connected to the rear module by the rail element; and
wherein the rear module is configured so as to be moved into the front module in a linear movement along the rail element.

7. The aerodynamic fairing body according to claim 1 , wherein the fairing body is dimensioned in such a way that the width of the fairing body is 5% to 12% of the length of the fairing body in the extended state.

8. The aerodynamic fairing body according to claim 1 , wherein a variation in a shape of the fairing body is brought about by the flap adjustment mechanism.

9. An aircraft, the aircraft comprising:
an airfoil;
an engine producing a blast; and
an aerodynamic fairing body, the fairing body being configured so as to accommodate a flap adjustment mechanism;
the fairing body being configured to vary between at least one extended state and at least one retracted state;
wherein the engine and the fairing body are arranged on the airfoil of the aircraft;
the aircraft further comprising a flap configured so as to be retracted and extended;
wherein the fairing body is coupled to the flap in such a way that said fairing body is converted into a retracted state when the flap is extended; and
wherein the fairing body is coupled to the flap in such a way that said fairing body is converted into an extended state when the flap is retracted.

10. A method for manufacturing an aerodynamic fairing body according to claim 1 , the method comprising:
arranging a fairing body on a flap adjustment mechanism of an aircraft at a predetermined distance from an engine and near a blast produced by the engine, and
configuring the fairing body to vary between at least one extended state and at least one retracted state;
wherein the fairing body is configured so as to take on the at least one retracted state during at least one of a take-off phase and a landing phase of the aircraft,
wherein the fairing body is configured so as to take on the at least one extended state during a cruising phase of the aircraft thereby reducing the flow resistance of the aircraft; and
wherein the total length of the fairing body in the direction of flight is smaller in the retracted state than in the extended state.

Assignees

• Airbus Operations Gmbh

Inventors

• Schroeder Karsten
• Friedel Hendrik

Classifications

• Y10T29/49826

  Assembling or joining · CPC title

• B64C7/00 Primary

  Structures or fairings not otherwise provided for · CPC title

• B64C9/38 Primary

  Jet flaps · CPC title

• B64C9/16

  at the rear of the wing · CPC title