Aeronautics and astronautics – Aircraft – heavier-than-air – Airplane and fluid sustained
Reexamination Certificate
1999-12-30
2001-07-03
Barefoot, Galen L. (Department: 3644)
Aeronautics and astronautics
Aircraft, heavier-than-air
Airplane and fluid sustained
C244S012400, C244S02300R, C244S056000
Reexamination Certificate
active
06254032
ABSTRACT:
CROSS REFERENCE TO RELATED APPLICATIONS
This application claims the priority of Swiss patent application 1959/99, filed Oct. 26, 1999, the disclosure of which is incorporated herein by reference in its entirety.
BACKGROUND OF THE INVENTION
The invention relates to an aircraft and a method for its operation, in particular an aircraft with electrically driven motors.
Modern aircraft must combine a high level of safety with economic efficiency. Hence, compromises have been made.
BRIEF SUMMARY OF THE INVENTION
Therefore, it is a general object of the invention to provide an aircraft and a method for operating an aircraft that are characterized by a high level of safety and economic efficiency.
Now, in order to implement these and still further objects of the invention, which will become more readily apparent as the description proceeds, the aircraft is manifested by the features that it comprises at least one generator for generating electrical power, at least one engine for driving said generator, and electrically driven drive units for generating lift and forward thrust.
In a further aspect of the invention, a method is provided for operating an aircraft, said aircraft comprising a fuselage, at least one generator of generating electrical energy, at least one engine for driving said generator, and electrically driven, pivotal drive units for generating lift and forward thrust, wherein each drive unit has a thrust axis, said method comprising the steps of adjusting said thrust axes of said drive units downwards for generating a lift for hover flight and adjusting said thrust axes of said drive units horizontally for generating a forward thrust for cruise flight, wherein in said cruise flight a lift is generated by an aerodynamic profile of said aircraft.
According to the invention, the power for the drives is generated by a combustion engine driving an electric generator. The power from the generator is used by the electrically operated drive units for generating lift and forward thrust of the aircraft. This combines the good ratio between weight and energy storage of a combustion engine with the reliability and fast response of electric motors. Since the engine drives a generator only, its operating parameters are exposed to lesser variations than those of conventional aircraft engines, which reduces the risk of defects and increases efficiency.
Some or preferably all of the drive units can be pivoted individually, such that their thrust can be adjusted according to demand. Since they use electric motors and no combustion engines, their reliable operation is not impaired by the pivotal movements. Preferably, the drive units can be pivoted from a vertical position up to a horizontal position. In the vertical position, they generate a lift that carries the aircraft in hover flight. In the horizontal position, they generate a forward thrust for a cruise flight of the aircraft.
The drive units are preferably designed to be ducted fans comprising at least one fan or impeller arranged in a tube-like hosing. Such ducted fans reach very high flow velocities and generate a low amount of noise.
By arranging the drive units on a circle, a configuration that is especially stable and easy to control is provided. Preferably, the aircraft comprises a central cabin and a circular wing arranged around the cabin. The drive units are arranged between the cabin and the circular wing. A design of high symmetry is preferred, where a gap for receiving the drive units is provided between the central cabin and the circular wing, because such an aircraft can be assembled from few, simple units.
In their horizontal position, the thrust axes of the drive units should be arranged above the central plane of the circular wing, such that the airflow on its surface is increased and lift is improved.
Preferably, at least five drive units are used, because when using only four drive units, the loss of only one of them leads to a configuration that is impossible to control in most situations.
The aircraft can be operated in hover flight and cruise flight. In hover flight, the drive units are pivoted downwards to generate a lift for keeping the craft in the air. In cruise flight, the drive units are pivoted backwards to generate a forwards thrust, wherein the lift is dynamically generated by the profile of the fuselage.
The attitude of the aircraft, i.e. its pitch, roll and yaw can be controlled by pivoting the drive units and adjusting their thrust.
REFERENCES:
patent: 2876965 (1959-03-01), Streib
patent: 3082977 (1963-03-01), Arlin
patent: 3284027 (1966-11-01), Mesniere
patent: 3335977 (1967-08-01), Meditz
patent: 3410507 (1968-11-01), Moller
patent: 3614030 (1971-10-01), Moller
patent: 3640489 (1972-02-01), Jaeger
patent: 3985320 (1976-10-01), Brady
patent: 4554989 (1985-11-01), Gruich et al.
patent: 4605185 (1986-08-01), Reyes
patent: 4613097 (1986-09-01), Jordan
patent: 4799629 (1989-01-01), Mori
patent: 5242132 (1993-09-01), Wukowitz
patent: 5383627 (1995-01-01), Bundo
patent: 5419514 (1995-05-01), Ducan
patent: 5895011 (1999-04-01), Gubin
patent: 3829329A1 (1989-03-01), None
patent: 1550060 (1968-11-01), None
Barefoot Galen L.
Cooper & Dunham LLP
Dowden Donald S.
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