The mechanism for cambering the wing leading edge provides an infinitely variable camber to the wing zero camber is provided for high speed flight, a slight camber for subsonic cruise, and very high cambers for landing and take-off flight modes.Ĭonventional high lift devices such as leading edge flaps and slats have been successfully employed on subsonic wings to improve their lift characteristics at low speeds such as during landing and take-off. The truss members are actuated by a screwdrive system to rotate about canted hinges for producing an airfoil camber deflection toward the wing leading edge and also the truss mechanism provides structural rigidity to the deflected surface as long as it is held immobile by the screw-drive system. The upper surface of the wing is a continuous structural skin which carries the variable camber mechanism and the lower surface of the wing is substantially a nonstructural skin and is provided with slip joints to permit shortening of the lower surface relative to the upper surface. The leading edge mechanism of the present invention is generally positioned forward of the front spar and comprises a series of trusswork members connected by canted hinges in a chordwise alignment or more specifically, normal to the wing leading edge. B64C3/48- Varying camber by relatively-movable parts of wing structures.B64C3/38- Adjustment of complete wings or parts thereof.238000000926 separation method Methods 0.000 description 2. ![]() ![]() 238000006011 modification reaction Methods 0.000 description 2.238000004904 shortening Methods 0.000 abstract description 6.Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.) Filing date Publication date Priority claimed from US13245271A external-priority Application filed by Boeing Co filed Critical Boeing Co Application granted granted Critical Publication of US3698668A publication Critical patent/US3698668A/en Anticipated expiration legal-status Critical Status Expired - Lifetime legal-status Critical Current Links Original Assignee Boeing Co Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.) Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.) Expired - Lifetime Application number US132452A Inventor James B Cole Current Assignee (The listed assignees may be inaccurate. Google Patents US3698668A - Variable camber airfoilÄownload PDF Info Publication number US3698668A US3698668A US132452A US3698668DA US3698668A US 3698668 A US3698668 A US 3698668A US 132452 A US132452 A US 132452A US 3698668D A US3698668D A US 3698668DA US 3698668 A US3698668 A US 3698668A Authority US United States Prior art keywords airfoil hinges canted pair camber Prior art date Legal status (The legal status is an assumption and is not a legal conclusion.
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