The invention discloses a method and modified aerodynamic apparatuses: fluid pushers-off and fluid motion-sensors, making enable efficient implementation and use of a controllable enhanced jet-effect, either the waving jet-effect, the Coanda jet-effect, the lift-effect, the effect of thrust, the Venturi effect, and/or the de Laval jet-effect, all are controllable using the Peltier effect and/or the Seebeck effect. The modified aerodynamic apparatuses are geometrically shaped and supplied with built-in thermoelectric devices, wherein the presence of the thermoelectric devices provides for new functional properties of the modified aerodynamic apparatuses. The method solves the problem of effective control of the operation of modified aerodynamic apparatuses such as airfoil wings of a flying vehicle, convergent-divergent nozzles, loudspeakers, and detectors of acoustic waves, all of a highly-efficient functionality.

There is provided a flight vehicle including: a wing unit; a battery that is arranged in the wing unit; an air intake unit that is formed at a position corresponding to the battery on a front side of the wing unit; a heat sink unit that is arranged for the battery and cools the battery by air which flows in from the air intake unit and that includes a ventilation unit having a shape widening from the front side toward a rear side; and an exhaust unit that is formed at a position corresponding to the battery on the rear side of the wing unit and that exhausts air which flows out from the heat sink unit.

There is provided a flight vehicle including: a wing unit; a battery that is arranged in the wing unit; an air intake unit that is formed at a position corresponding to the battery on a front side of the wing unit; a heat sink unit that is arranged for the battery and cools the battery by air which flows in from the air intake unit and that includes a ventilation unit having a shape widening from the front side toward a rear side; and an exhaust unit that is formed at a position corresponding to the battery on the rear side of the wing unit and that exhausts air which flows out from the heat sink unit.

A drone control system in which a drone can move to a position where a purpose can be achieved and performs an action according to the purpose is provided. The drone control system 1 controls a drone 10 capable of performing a predetermined action on a predetermined object, and includes a state data acquiring module 201 that acquires state data indicating a state of the object, a purpose data acquiring module 202 that acquires purpose data which is a purpose of moving the drone, and a detecting module 203 that detects an action point, which is position information at which an action for the purpose is executed, based on the acquired state data and purpose data.

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.

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.

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.

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.

The invention discloses a method and modified aerodynamic apparatuses: fluid pushers-off and fluid motion-sensors, making enable efficient implementation and use of a controllable enhanced jet-effect, either the waving jet-effect, the Coanda jet-effect, the lift-effect, the effect of thrust, the Venturi effect, and/or the de Laval jet-effect, all are controllable using the Peltier effect and/or the Seebeck effect. The modified aerodynamic apparatuses are geometrically shaped and supplied with built-in thermoelectric devices, wherein the presence of the thermoelectric devices provides for new functional properties of the modified aerodynamic apparatuses. The method solves the problem of effective control of the operation of modified aerodynamic apparatuses such as airfoil wings of a flying vehicle, convergent-divergent nozzles, loudspeakers, and detectors of acoustic waves, all of a highly-efficient functionality.

There is provided a flight vehicle including: a wing unit; a battery that is arranged in the wing unit; an air intake unit that is formed at a position corresponding to the battery on a front side of the wing unit; a heat sink unit that is arranged for the battery and cools the battery by air which flows in from the air intake unit and that includes a ventilation unit having a shape widening from the front side toward a rear side; and an exhaust unit that is formed at a position corresponding to the battery on the rear side of the wing unit and that exhausts air which flows out from the heat sink unit.