B - Operations – Transporting – 64 – D
Patent
B - Operations, Transporting
64
D
B64D 27/02 (2006.01) B64C 29/00 (2006.01)
Patent
CA 2311938
The present invention relates to a system for the transformation of a traditional self-sustained horizontal take-off and landing aircraft into hybrid, integrated, self-sustained vertical take-off and landing and horizontal flight comprising, besides the propulsion system already provided in the aircraft, a hydraulic propulsion system, activating at least a blade rotor (1), to be used during the vertical takeoff and landing and transition phases, said hydraulic system being powered by the engines of the aircraft, and at least an auxiliary engine (2), provided in a rear position and/or under the aircraft, said at least an auxiliary engine being progressively tiltable and swingable between two limit positions, respectively vertical position and horizontal position, said standard propulsion means of the aircraft being deactivated during the vertical take-off and landing and the transition and activated during the self-sustained horizontal flight, and said at least an auxiliary engine and said at least one auxiliary engine being operating during the vertical take-off and landing and the transition and deactivated during the self-sustained horizontal flight.
La présente invention concerne un système permettant de transformer un avion à classique à décollage et atterrissage horizontaux et à autosustentation, en un avion intégré, hybride, à décollage et atterrissage verticaux, à vol horizontal et à autosustentation. Ce dernier comporte, outre le système de propulsion déjà prévu dans l'avion, un système à propulsion hydraulique, actionnant au moins un rotor à pales (1), servant lors des décollage et atterrissage verticaux, et des phases de transition. Ce système hydraulique est animé par les moteurs de l'avion, et au moins un moteur auxiliaire (2) placé dans une partie arrière et/ou inférieure de l'avion. Ledit moteur auxiliaire est progressivement basculable et pivotable entre deux positions limites, respectivement une position verticale et une position horizontale. Ledit dispositif de propulsion standard de l'avion est désactivé pendant les décollage et atterrissage verticaux, et pendant les phases de transition, et activé lors du vol horizontal à autosustentation. Ledit moteur auxiliaire fonctionne pendant les décollage et atterrissage verticaux, et pendant les phases de transition, et est désactivé lors du vol horizontal à autosustentation.
Capanna Franco
Dennison Associates
LandOfFree
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