HYBRID AIRCRAFT
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 ).
1 .- 10 . (canceled)
11 . A motor-driven, fixed-wing aircraft, comprising:
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.
12 . The aircraft of claim 11 , constructed to define an overall center of gravity arranged between a center of gravity of the energy generation unit and a center of gravity of the thrust creation unit.
13 . The aircraft of claim 11 , wherein the electric transmission device includes a DC link circuit, said energy generation unit including a rectifier configured to couple the DC link circuit to the electric generator of the energy generation unit.
14 . The aircraft of claim 11 , further comprising an aircraft fuselage, and a converter arranged in the aircraft fuselage and configured to operate the electric motor of the thrust creation unit.
15 . The aircraft of claim 11 , further comprising wings and a tailplane assembly, said thrust creation unit being arranged between the wings and the tailplane assembly.
16 . The aircraft of claim 11 , further comprising a further thrust creation unit coupled electrically via the transmission device to the energy generation unit.
17 . The aircraft of claim 11 , wherein the propeller is a free-running propeller or a ducted propeller.
18 . The aircraft of claim 11 , wherein the electric motor of the thrust creation unit is coupled via a gearing to the propeller and/or the internal combustion engine of the energy generation unit is coupled via a gearing to the electric generator.