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.
Gas propulsion thrust device
2024-02-22
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
Engineering Index Backfile | 1959
|Thrust group for a propulsion device and associated propulsion device
European Patent Office | 2024
|NTRS | 1991
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