[특허]Airfoil flap assembly with split flap track fairing system

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Airfoil flap assembly with split flap track fairing system

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-007/00 B64C-009/18
출원번호	US-0718324 (2015-05-21)
등록번호	US-9567063 (2017-02-14)
발명자 / 주소	Colaciti, Alysson Kennerly Crenite Simões, Leandro Guilherme Ferreira, Alexandre Viana Valle do Carmo, Micael Gianini Triches, Jr., Mário Gouveia, Vinicius Losada
출원인 / 주소	EMBRAER S.A.
대리인 / 주소	Nixon & Vanderhye P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 14

초록
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Flap track fairing systems are split into a forward immovably fixed portion and an aft movable portion. The fixed forward portion is immovably attached to the main wing structure of an aircraft while the movable aft portion is attached either to the movable components of the flap deployment mechanism or to the lower surface of the flap. A separation line between the forward movable portion and the aft fixed portion is provided such that the movable portion does not interfere structurally with the flap fairing structure during a flap extension/retraction cycle. An airflow deflector is positioned near a forward separation edge of the aft fairing portion so as to be positioned within a gap defined between the forward edge of the aft fairing portion and a rearward edge of the forward fairing portion when the flap is in the deployed configuration thereof to thereby deflect airflow away from the interior space of the fairing.

대표
청구항
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1. A flap assembly for an airfoil comprising: a flap;a flap operating mechanism operably connected to the flap for moving the flap between a retracted configuration and a deployed configuration wherein the flap is positioned rearwardly and downwardly relative to the airfoil; anda flap track fairing having an interior cavity space for housing the flap operating mechanism, wherein the flap track fairing comprises,(i) a forward fairing portion having an aft separation edge and being immovably fixed to the airfoil;(ii) an aft fairing portion having a forward separation edge and being connected to the flap so as to be movable downwardly and laterally relative to the forward fairing portion in response to the flap being moved between the retracted and deployed configurations thereof; and(iii) a primary airflow deflector blade positioned along the forward separation edge of the aft fairing portion, wherein the primary airflow deflector blade includes: an outer fixed edge which is fixed to the forward separation edge of the aft fairing portion, andan inner free edge which is unconnected to the aft fairing portion, whereinthe primary airflow deflector blade is slanted inwardly towards the interior cavity space of the flap track fairing between the outer fixed edge and the inner free edge thereof, and whereinthe primary airflow deflector blade is housed within the interior cavity space of the flap track fairing when the flap is in the retracted configuration thereof and is positioned within a fairing gap defined between the forward and rearward separation edges of the aft and forward fairing portions, respectively, when the flap is in the deployed configuration thereof to thereby deflect airflow away from the interior cavity space of the fairing. 2. The flap assembly as in claim 1, further comprising at least one secondary airflow deflector blade, wherein the primary airflow deflector blade is positioned along an upper region of the forward separation edge, and the at least one secondary airflow deflector blade is positioned along a lower region of the forward separation edge. 3. The flap assembly as in claim 2, further comprising a plurality of the secondary airflow deflector blades positioned along the forward separation edge of the aft fairing portion. 4. The flap assembly as in claim 1, wherein the flap is a single slotted flap. 5. The flap assembly as in claim 1, wherein the flap is comprised of a single flap having an upper flap surface and a vane fixed to the single flap so as to be in operative association with the upper surface thereof. 6. An aircraft which comprises: a fuselage,a pair of wings extending from the fuselage, anda plurality of wing flaps operatively associated with each wing, whereineach wing flap comprises a flap assembly in accordance with claim 1. 7. The aircraft as in claim 6, further comprising at least one secondary airflow deflector blade, wherein the primary airflow deflector blade is positioned along an upper region of the forward separation edge, and the at least one secondary airflow deflector blade is positioned along a lower region of the forward separation edge. 8. The aircraft as in claim 7, further comprising a plurality of the secondary airflow deflector blades positioned along the forward separation edge. 9. The aircraft as in claim 6, wherein each wing flap is a single slotted flap. 10. The aircraft as in claim 6, wherein each wing flap is comprised of a single flap having an upper flap surface and a vane fixed to the single flap so as to be in operative association with the upper surface thereof. 11. The aircraft as in claim 6, wherein the wings are swept wings which are angled either rearwardly or forwardly relative to the aircraft fuselage. 12. A flap assembly for an airfoil comprising: a flap;a flap operating mechanism operably connected to the flap for moving the flap between a retracted configuration and a deployed configuration wherein the flap is positioned rearwardly and downwardly relative to the airfoil; anda flap track fairing having an interior cavity space for housing the flap operating mechanism, wherein the flap track fairing comprises:(i) a forward fairing portion having an aft separation edge and being immovably fixed to the airfoil;(ii) an aft fairing portion having a forward separation edge and being connected to the flap so as to be movable downwardly and laterally relative to the forward fairing portion in response to the flap being moved between the retracted and deployed configurations thereof; and(iii) a primary airflow deflector blade positioned along an upper region of the forward separation edge of the aft fairing portion, and(iv) a secondary airflow deflector blade positioned along a lower region of the forward separation edge of the aft fairing portion, the primary and secondary airflow deflector blades being housed within the interior space of the flap track fairing when the flap is in the retracted configuration thereof and are positioned within a fairing gap defined between the forward and rearward separation edges of the aft and forward fairing portions, respectively, when the flap is in the deployed configuration thereof to thereby deflect airflow away from the interior cavity space of the fairing. 13. The flap assembly as in claim 12, further comprising a plurality of the secondary airflow deflector blades positioned along the forward separation edge of the aft fairing portion. 14. The flap assembly as in claim 12, wherein the primary airflow deflector blade is slanted inwardly towards the interior space of the flap track fairing. 15. The flap assembly as in claim 12, wherein the flap is a single slotted flap. 16. The flap assembly as in claim 12, wherein the flap is comprised of a single flap having an upper flap surface and a vane fixed to the single flap so as to be in operative association with the upper surface thereof. 17. An aircraft which comprises: a fuselage;a pair of wings extending from the fuselage; anda plurality of wing flaps operatively associated with each wing;wherein each wing flap comprises a flap assembly in accordance with claim 12. 18. The aircraft as in claim 17, wherein the primary airflow deflector is slanted inwardly towards the interior space of the flap track fairing. 19. The aircraft as in claim 17, wherein each wing flap is a single slotted flap. 20. The aircraft as in claim 17, wherein each wing flap is comprised of a single flap having an upper flap surface and a vane fixed to the single flap so as to be in operative association with the upper surface thereof. 21. The aircraft as in claim 17, wherein the wings are swept wings which are angled either rearwardly or forwardly relative to the aircraft fuselage.

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Airfoil flap assembly with split flap track fairing system

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이 특허에 인용된 특허 (14)

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Airfoil flap assembly with split flap track fairing system

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이 특허에 인용된 특허 (14)

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