Controlled transitory or sustained gliding flight with dihedral angle and trailing flaps
- Creators
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Paranjape, Aditya A.
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Chung, Soon-Jo
Abstract
A micro aerial vehicle capable of controlled transitory or sustained gliding flight. The vehicle includes a fuselage. A pair of articulated wings are forward of a center of gravity of the vehicle, the wings being articulated and having trailing edge flaps, and having actuators for controlling the dihedral angles of the wings and the flaps for effective yaw control across the flight envelope. The dihedral angles can be varied symmetrically on both wings to control the aircraft speed independently of the angle of attack and flight-path angle, while an asymmetric dihedral setting can be used to control yaw and the actuators control the dihedral settings of each wing independently. The aircraft lacks a vertical tail or other vertical stabilizer.
Additional Information
Publication number US9394050B2. Publication type Grant. Publication date July 19, 2016. Application number US14068235. Filing date October 31, 2013. Priority date November 15, 2012. Government Interests: STATEMENT OF GOVERNMENT INTEREST. This invention was made with government support under contract number FA95500910089 awarded by the Air Force Office of Scientific Research. The government has certain rights in the invention. Parent Case Text: PRIORITY CLAIM AND REFERENCE TO RELATED APPLICATION. The application claims priority under 35 U.S.C. .sctn.119 from prior provisional application Ser. No. 61/726,663, which was filed Nov. 15, 2012, and which is incorporated by reference herein.Attached Files
Published - US20140319267.pdf
Published - US9394050.pdf
Published - US9394050B2-uspto.pdf
Files
Additional details
- Eprint ID
- 73606
- Resolver ID
- CaltechAUTHORS:20170123-074947443
- Air Force Office of Scientific Research (AFOSR)
- FA95500910089
- Created
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2017-02-03Created from EPrint's datestamp field
- Updated
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2020-03-09Created from EPrint's last_modified field