Record Details

Variable Camber Continuous Aerodynamic Control Surfaces and Methods for Active Wing Shaping Control
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Author and Affiliation: Nguyen, Nhan T. [Inventor]
Abstract: An aerodynamic control apparatus for an air vehicle improves various aerodynamic performance metrics by employing multiple spanwise flap segments that jointly form a continuous or a piecewise continuous trailing edge to minimize drag induced by lift or vortices. At least one of the multiple spanwise flap segments includes a variable camber flap subsystem having multiple chordwise flap segments that may be independently actuated. Some embodiments also employ a continuous leading edge slat system that includes multiple spanwise slat segments, each of which has one or more chordwise slat segment. A method and an apparatus for implementing active control of a wing shape are also described and include the determination of desired lift distribution to determine the improved aerodynamic deflection of the wings. Flap deflections are determined and control signals are generated to actively control the wing shape to approximate the desired deflection.
Publication Date: Jan 05, 2016
Document ID:
20160001290
(Acquired Feb 01, 2016)
Subject Category: AIRCRAFT DESIGN, TESTING AND PERFORMANCE; AERODYNAMICS
Report/Patent Number: US-Patent-9,227,721, US-Patent-Appl-SN-13/648,197
Document Type: Patent
Financial Sponsor: NASA; Washington, DC United States
Organization Source: NASA; Washington, DC United States
Description: 61p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: CAMBER; DEFLECTION; FLAPPING; AEROELASTIC RESEARCH WINGS; ACTIVE CONTROL; AERODYNAMICS; SHAPES; LIFT; TRAILING EDGES; DRAG; LEADING EDGES; ANGLE OF ATTACK; VORTICES; CONTROL SURFACES; PATENTS
Miscellaneous Notes: This patent application claims the benefit of U.S. provisional patent application 61/628,299, filed Oct. 7, 2011 and entitled "Elastically Shaped Future Air Vehicle Concept," which is incorporated by reference along with all other references cited in this application.
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