Title:
【発明の名称】ダクト付きカウンタ回転同軸ロータを有する無人飛行体の空力的補助構造体
Document Type and Number:
Japanese Patent JPH08509930
Kind Code:
A
Abstract:
An unmanned aerial vehicle (UAV) having a toroidal fuselage and a rotor assembly including counter-rotating rotors coaxially mounted with respect to the toroidal fuselage incorporates ancillary aerodynamic structures aerodynamically configured and mounted in combination with the toroidal fuselage to provide a nose-down pitching moment to counteract the nose-up pitching moment generated by airflow over the toroidal fuselage during forward translational flight of the UAV. The ancillary aerodynamic structures have a cambered airfoil profile to provide high lifting forces. The ancillary aerodynamic structures may have centers of lift located significantly aft of the quarter-chord line of the airfoil, and are symmetrically mounted in combination with the lateral sides of the toroidal fuselage so that the centers of lift are located aftwardly of the fuselage axis of the toroidal fuselage in forward translational flight modes such that the ancillary aerodynamic structures generate a nose-down pitching moment to counteract the nose-up pitching moment due to airflow over the toroidal fuselage in forward translational flight. In a first embodiment, the ancillary aerodynamic structures are fixedly mounted in combination with the toroidal fuselage at a predetermined angle of incidence. In a second embodiment, the ancillary aerodynamic structures are rotatably mounted in combination with the toroidal fuselage to provide variable incidence ancillary aerodynamic structures for the UAV.
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Inventors:
Fleming, Robert Jay., Junior
Rosen, Kennis M.
Sea High, Thomas W.
Rosen, Kennis M.
Sea High, Thomas W.
Application Number:
JP52548494A
Publication Date:
October 22, 1996
Filing Date:
April 29, 1994
Export Citation:
Assignee:
United Technologies Corporation
International Classes:
B64C27/20; B64C27/26; B64C39/02; (IPC1-7): B64C27/26; B64C27/20; B64C39/02
Attorney, Agent or Firm:
Fujiya Shiga (1 person outside)