# US 2014/0151510 A1 · Formvariable Aerodynamic Fairing Body For A Flap Actuator Mechanism Of An Aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0151510 A1 - Document ID: US20140151510A1 - Status: Published application - Kind: A1 - Application number: 14/089,793 - Filed: 2013-11-26 - Published: 2014-06-05 - Earliest claimed: 2012-11-30 - Assignees: Airbus Operations GmbH - Applicants: Airbus Operations GmbH - Inventors: Karsten Schroeder; Hendrik Friedel - Web page: https://patentgrep.com/patent/US20140151510A1 ## CPC - B64C 9/38: Jet flaps - B64C 7/00: Structures or fairings not otherwise provided for - B64C 9/16: at the rear of the wing - Y10T 29/49826: Assembling or joining - B64C: AEROPLANES; HELICOPTERS - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## 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. ## Claims ### Claim 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, which engine produces a blast which varies depending on the flight phase; wherein 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 in every flight phase of the aircraft. ### Claim 2 (depends on 1) The aerodynamic fairing body according to claim 1, wherein the variation in the shape of the fairing body is inversely mechanically coupled to at least one of retraction and extension of flaps of the aircraft. ### Claim 3 (depends on 1) The aerodynamic fairing body according to claim 1, wherein the variation in shape of the fairing body corresponds to a variation in length of the fairing body in a direction of flight of the aircraft. ### Claim 4 (depends on 1) The aerodynamic fairing body according to claim 1, wherein the fairing body comprises a front module and a rear module; and wherein the variation in the shape of the fairing body is brought about by adjusting the rear module with respect to the front module. ### Claim 5 (depends on 4) The aerodynamic fairing body according to claim 4, wherein the front module is configured so as to receive the rear module. ### Claim 6 (depends on 4) 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. ### Claim 7 (depends on 1) The aerodynamic fairing body according to claim 1, wherein the fairing body is configured so as to take on a 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 an extended state during a cruising phase 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. ### Claim 8 (depends on 7) The aerodynamic fairing body according to claim 7, 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. ### Claim 9 (depends on 1) The aerodynamic fairing body according to claim 1, wherein the variation in the shape of the fairing body is brought about by the flap adjustment mechanism. ### Claim 10 An aeroplane, the aeroplane comprising an aerofoil; an engine, which produces a blast which varies depending on the flight phase; and an aerodynamic fairing body, 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, which engine produces a blast which varies depending on the flight phase; wherein 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 in every flight phase of the aircraft; and wherein the engine and the fairing body are arranged on the aerofoil of the aeroplane. ### Claim 11 (depends on 10) The aeroplane according to claim 10, 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 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 body is converted into an extended state when the flap is retracted. ### Claim 12 (depends on 1) A method for manufacturing an aerodynamic fairing body according to claim 1, the method comprising the following steps: arranging a fairing body on a flap adjustment mechanism of an aircraft at a predetermined distance from an engine which produces a blast which varies depending on the flight phase; and configuring the fairing body in such a way that it can be varied in shape in such a way that the fairing body is located outside the blast of the engine permanently.