A light helicopter with an empty mass of <1000kg, 2000kg maximum gross mass, a rotor assembly with a rotor hub 2500-3500mm from fuselage nose, an aerodynamic composite shell 1010, a landing gear arrangement, and a power plant with a primary fuel cell 3300 behind the passenger cabin having four-six forward-facing seats. The elongate fuselage 1000 tapers to a tail boom assembly 1200 and may be streamlined. A rotatable aerodynamic fairing 2202 may be mounted on the rotor hub, with a separate static pylon fairing 2204 fixed around the swashplate assembly. The landing gear may retract into the fuselage defining a track wider than the cabin width when deployed. Optionally, the primary fuel cell capacity is 500-700 litres. An optional secondary fuel cell 3400, or trimmer tank, in a nose cavity 1060 in front of seating positions 1110 is fluidly connected to the primary fuel cell and/or the engine 3100.
An improved rotorcraft
2024-08-14
Patent
Electronic Resource
English
Rotorcraft controls and rotorcraft including such rotorcraft controls
European Patent Office | 2018
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