Improvements to convertible aircraft with tilting rotors

Details Improvements to convertible aircraft with tilting rotors Improvements to convertible aircraft with tilting rotors

B - Operations, Transporting

64

C

B64C 29/00 (2006.01) B64C 9/00 (2006.01) B64C 13/16 (2006.01) B64C 13/50 (2006.01) B64C 27/28 (2006.01)

Patent

CA 2382879

The invention concerns a convertible aircraft (1) with tilting rotors (9), flying in aeroplane mode as well as in helicopter mode, with high fixed wings (5), raised with respect to the fuselage (2) and in positive dihedral supporting the engine cars (6) whereof at least the front part (8) tilts with the rotors (9). Each wing (5) is extended substantially along its wing span, outside the engine car (6), by an external wing system portion (13), whereof at least one part pivots about a transverse hinge line and forms a control and/or adjustable control surface, whereof the pivoting movements are controlled by at least one monitored actuator. The invention is useful for self-adaptive active anti-vibration control on convertible aircraft capable of landing in aeroplane mode, and increased roll control.

L'aéronef convertible (1) à rotors basculants (9), évoluant en mode avion comme en mode hélicoptère, a des ailes fixes (5), hautes, surélevées par rapport au fuselage (2) et en dièdre positif qui supportent des nacelles motrices (6) dont au moins la partie avant (8) bascule avec les rotors (9). Chaque aile (5) est prolongée sensiblement selon son envergure, à l'extérieur de la nacelle (6), par une portion externe de voilure (13), dont au moins une partie pivote autour d'un axe d'articulation transversal et constitue une surface de commande et/ou de contrôle orientable, dont les pivotements sont commandés par au moins un actionneur piloté. Application au contrôle anti- vibratoire actif, auto-adaptatif sur des aéronefs convertibles pouvant atterrir en configuration avion, et accroissement au contrôle en roulis.

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