Actuating apparatus for a flap system having an upper surface blowing powered lift system
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-009/02
B64C-009/16
출원번호
US-0000118
(1979-01-02)
발명자
/ 주소
Rudolph Peter K. C. (13683 18th Ave. SW. Seattle WA 98166)
인용정보
피인용 횟수 :
40인용 특허 :
2
초록▼
A trailing edge flap moveable from a stowed position behind a wing to a downwardly and rearwardly extending position to deflect jet exhaust from an upper surface blowing jet engine downwardly and rearwardly to augment lift. The actuating mechanism rotates the flap about a variable radius which maint
A trailing edge flap moveable from a stowed position behind a wing to a downwardly and rearwardly extending position to deflect jet exhaust from an upper surface blowing jet engine downwardly and rearwardly to augment lift. The actuating mechanism rotates the flap about a variable radius which maintains the upper surface of the flap in contact with and generally in tangential alignment with the trailing edge of the upper surface of the wing. This mechanism comprises forward and rear radius links pivotally mounted at their lower ends to a stationary mounting arm, and extending upwardly and divergently therefrom to attach to the flap. In two embodiments, the rear radius link has its pivot end mounted to a moveable member which in turn enables the flap to be rotated so that its forward end moves downwardly. Thus, in its fully deployed position, the flap can be rotated to form a slot between the aft end of the wing and the leading edge of the flap.
대표청구항▼
In an aircraft having: a. an airfoil having a leading edge, a substantially non-adjustable trailing edge, an airfoil chordwise axis, an airfoil upper aerodynamic surface and a rear cove portion with a rear cove edge at a trailing edge of said airfoil aerodynamic surface, b. a flap member having a fo
In an aircraft having: a. an airfoil having a leading edge, a substantially non-adjustable trailing edge, an airfoil chordwise axis, an airfoil upper aerodynamic surface and a rear cove portion with a rear cove edge at a trailing edge of said airfoil aerodynamic surface, b. a flap member having a forward end, a rear end, a flap chordwise axis, and a flap upper aerodynamic surface, said flap member moveable between a stowed position in the cove portion of the airfoil with the flap chordwise axis being in general alignment with the airfoil chordwise axis, and a fully deployed position where the flap member extends downwardly from the rear cove edge, c. said flap upper surface having a contact area adapted to remain adjacent said rear cove edge as the flap member is moved between its stowed and fully deployed positions, said contact area having a varying radius of curvature which increases rearwardly along said chordwise axis, and a contact location which is that portion of the contact area adjacent the rear cover edge at any flap position, an actuating apparatus adapted to be used in conjunction with an upper surface blown powered lift system for said aircraft to move said flap member between its stowed position and its fully deployed position to intermediate positions between the stowed and fully deployed positions, in a manner that as the flap member rotates rearwardly or forwardly the upper flap surface is maintained in substantially constant contact with and in general alignment with the trailing edge of the airfoil aerodynamic surface, said actuating means comprising: a. a mounting structure positoned below said flap member in its stowed position, b. a forward positioning link having a lower end pivotally connected to said mounting structure at a lower first forward location and an upper end pivotally connected to said flap member at an upper second forward location, c. a rear positioning link having a lower end pivotally connected to said mounting structure at a lower third rear location and an upper end pivotally connected to said flap member at an upper fourth rear location, d. said second and fourth location being spaced from each other by a first greater distance, and said first and third locations being spaced from each other by a second lesser distance, in a manner that with said flap member in its stowed position, said links extend upwardly from said mounting structure divergently from one another, e. said first, second, third and fourth locations being so positioned that with said flap member in its stowed positon, a first line drawn through said first and second locations and a second line drawn through said third and fourth locations meet at a center point which is an instantaneous center of rotation of said flap member, and said instantaneous center of rotation shifts during movement of said flap member between its stowed and deployed positions in a manner to compensate for variations in curvature of the flap surface contact area, so as to maintain the contact location of said contact area in a position adjacent said rear cove edge, f. the actuating apparatus being characterized in that the actuating apparatus itself provides main compensation for the curvature of the upper flap surface.
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이 특허에 인용된 특허 (2)
Whitener ; Philip Charles, Efficient trailing edge system for an aircraft wing.
Lacy, Douglas S.; Kordel, Jan A.; Dovey, John V.; Balzer, Michael A.; Sakurai, Seiya; Huynh, Neal V., Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods.
Lacy, Douglas S.; Kordel, Jan A.; Dovey, John V.; Balzer, Michael A.; Sakurai, Seiya; Huynh, Neal V., Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods.
Lacy, Douglas S.; Kordel, Jan A.; Dovey, John V.; Balzer, Michael A.; Sakurai, Seiya; Huynh, Neal V., Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods.
Lacy, Douglas S.; Beyer, Kevin W.; Brown, Stephen T.; Dees, Paul W.; Huynh, Neal V.; Kordel, Jan A.; Prow, Clayton A.; Sakurai, Seiya, Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods.
Good,Mark S.; Viigen,Paul M.; Gitnes,Seth E.; Thomas,Glynn Michael, Aircraft wing systems for providing differential motion to deployable lift devices.
Huynh, Neal V.; Bleeg, Robert J.; Pepper, Ralph Scott; Standley, John A.; Bocksch, Brian L., Systems and methods for controlling aircraft flaps and spoilers.
Huynh,Neal V.; Bleeg,Robert J.; Pepper,Ralph Scott; Standley,John A.; Bocksch,Brian L., Systems and methods for controlling aircraft flaps and spoilers.
Good, Mark S.; Vijgen, Paul M.; Gitnes, Seth E.; Thomas, Glynn Michael, Systems and methods for providing differential motion to wing high lift device.
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