HYBRID AIRCRAFT
2 Assignments
0 Petitions
Accused Products
Abstract
The invention relates to a hybrid aircraft (F). According to the invention, a suitable position for mounting an energy generation unit (14) in the aircraft is identified, said energy generation unit comprising an internal combustion engine (34) and an electric generator (30) that is coupled thereto via a shaft. Independently of the position of the energy generation unit (14), a position is also identified for a thrust generation unit (12) comprising an electric motor (24) and a propeller (20) that is coupled thereto via a shaft (22). When the aircraft (F) is built, the thrust generation unit (12) and the energy generation unit (14) are disposed in the positions identified therefor. The generator (30) is then coupled to the electric motor (24) via an electric transmission device (16).
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Citations
18 Claims
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1-10. -10. (canceled)
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11. A motor-driven, fixed-wing aircraft, comprising:
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a thrust creation unit including an electric motor, a propeller, and a shaft to couple the propeller to the electric motor; an energy generation unit spaced from the thrust creation unit by a distance of at least 0.5 m and including an internal combustion engine having a maximum possible power output which is less than the thrust power needed during a take-off of the aircraft, an electric generator, and a shaft to couple the electric generator to the internal combustion engine, said shaft of the energy generation unit being rotatable about an axis of rotation and extending transversely to a specified flight direction of the aircraft, said internal combustion engine being defined by a consumption-optimized operation which lies at a power output of the internal combustion engine in a range of 100% to 130% of a specified cruising power of the aircraft, wherein the aircraft is designed to assist the energy generation unit during takeoff of the aircraft so as to provide thrust needed during takeoff; an electric transmission device configured to transmit electric energy from the energy generation unit to the thrust creation unit; at least one energy supply device configured to supply the thrust creation device with additional electric energy and including a battery or a fuel cell; and a sound conducting device configured to emit sound created by the energy generation unit upwards away from the aircraft and including a channel for directing the sound upwards. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18)
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Specification