Gas propulsion thrust device
OwnerIgor Morozovinventor
Life of this patent
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Abstract
A novel gas propulsion device comprises one or more high-frequency linear actuators (such as a voice coil linear actuator or a piezoelectric linear actuator) attached to one or more gas propulsion elements having a concave internal surface facing a first side thereof. Linear actuators operate to cause reciprocal movements of each gas propulsion element at a sufficient speed, such as a subsonic or supersonic speed, and suitable amplitude to form a high gas pressure zone on the first side of the gas propulsion element and a low gas pressure zone on the second side thereof. The gas pressure differential in turn causes propulsion of gas away from the device along the longitudinal axis or to the side of it if the gas propulsion element is tilted. The invention may be used as a main or secondary thrust engine for an aircraft.
Claims20
A gas propulsion thrust device comprising:
- a first high-frequency linear actuator aligned along a direction of propulsion thrust, and
- a first gas propulsion element having a rigid concave internal surface facing a first side thereof, the concave internal surface is axisymmetric about a longitudinal axis aligned along the direction of propulsion thrust, the first gas propulsion element having a second convex external surface adjacent the concave internal surface and facing the second side, opposite the first side thereof, the first gas propulsion element is submerged in and surrounded by said gas,
- wherein the first high-frequency linear actuator is operatively attached to the first gas propulsion element and configured to cause reciprocal movements thereof along the direction of propulsion thrust with a speed at or exceeding a predetermined transonic speed threshold and an amplitude at or exceeding a predetermined amplitude threshold being sufficient to cause a formation of a high gas pressure zone on the first side thereof and a low gas pressure zone on the second side thereof as a result of reciprocal movement thereof, wherein the speed of movement is the same in both directions of the reciprocal movements, thereby generating a gas pressure differential across the gas propulsion element and along the direction of propulsion thrust causing propulsion of gas away from the first gas propulsion element and in a direction opposite the direction of propulsion thrust.
Dependencies are inferred from the claim text.