A multi-boom aircraft with an adjustable wing geometric twist includes at least one wing, and at least three booms arranged transversely to at least one of the wings. Each of the booms includes at least one actuator, and the at least one wing is mounted on the booms so as at least a portion of the corresponding wing can be pivoted by means of the actuators about an axis extending substantially along the corresponding wing.

Provided is a disc-shaped aircraft including a rotatable disc-shaped wing inclined downward from a center to an edge of the wing and including a through hole vertically penetrating through a center of the wing, a body provided in a space under the wing, a driving mechanism for providing rotary power to the wing, a connector including an end connected to a side of the wing forming the through hole, and another end connected to the driving mechanism to transmit rotary power to the wing, a main channel provided between the wing and the body to serve as a passage for a gas sucked into the through hole, an ejection hole provided between a lower end of the wing and the body to eject the gas flowing along the main channel, downward, and a flight controller for adjusting an ejection amount of the gas ejected from the ejection hole, by changing a shape of the main channel by adjusting a height of the wing.

Provided is a disc-shaped aircraft including a rotatable disc-shaped wing inclined downward from a center to an edge of the wing and including a through hole vertically penetrating through a center of the wing, a body provided in a space under the wing, a driving mechanism for providing rotary power to the wing, a connector including an end connected to a side of the wing forming the through hole, and another end connected to the driving mechanism to transmit rotary power to the wing, a main channel provided between the wing and the body to serve as a passage for a gas sucked into the through hole, an ejection hole provided between a lower end of the wing and the body to eject the gas flowing along the main channel, downward, and a flight controller for adjusting an ejection amount of the gas ejected from the ejection hole, by changing a shape of the main channel by adjusting a height of the wing.

A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume having a first average velocity from an engine, and expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave.

A method of supersonic thrust generation includes generating a thrust supersonic exhaust plume having a first average velocity from an engine, and expelling a bypass exhaust plume having a second average velocity from the engine, the first average velocity greater than the second average velocity, so that the bypass exhaust plume inhibits coalescence of an engine exhaust plume compression shockwave.

A locking pin associated with one of a fixed wing and a wing tip device, and a bush associated with the other of the fixed wing and wing tip device, the bush configured to receive the locking pin. The bush is located within a bush housing arranged to allow relative movement of the bush in the direction of a longitudinal axis of the locking pin when the locking pin is received within the bush.

A multirotor aircraft that includes a chassis, three or more vertical rotors, one or more free wings and on ore more fixed horizontal rotor. The free wing is attached to the chassis by an axial connection so that the angle of the free wing is changed relative to the chassis according the flow of air over the free wing. The fixed horizontal rotor enables the multirotor aircraft to lower and climb while flying forward at a stable horizontal pitch of the chassis.

A system includes a plurality of sensors along a surface of an airfoil operable to measure a first set of ice thickness values at a first time and a second set of ice thickness values at a second time. The system further includes a processor configured to determine a first plurality of lift calculation variables and a second plurality of lift calculation variables. The processor also generates a threshold angle of attack value and updates the threshold angle of attack value at the second time, based on one or more differences between the first and second sets of ice thickness values and the first and second plurality of lift calculation variables. The processor is further configured to send, to a display, based on the updated threshold angle of attack, one or more changes to flight data to adjust the actual angle of attack of the airfoil.

A system includes a plurality of sensors along a surface of an airfoil operable to measure a first set of ice thickness values at a first time and a second set of ice thickness values at a second time. The system further includes a processor configured to determine a first plurality of lift calculation variables and a second plurality of lift calculation variables. The processor also generates a threshold angle of attack value and updates the threshold angle of attack value at the second time, based on one or more differences between the first and second sets of ice thickness values and the first and second plurality of lift calculation variables. The processor is further configured to send, to a display, based on the updated threshold angle of attack, one or more changes to flight data to adjust the actual angle of attack of the airfoil.

An unmanned vehicle including a vehicle body, a propulsion system, a maneuvering system, a vehicle control system, a buoyancy control system, a sensor system, and at least one power supply is disclosed. The propulsion system, maneuvering system, vehicle control system, buoyancy control system, sensor system, and power supply are carried by the vehicle body. The sensor system includes a sensor adapted to detect an item of interest and provide an item of interest signal to the vehicle control system. The vehicle control system is adapted to receive the item of interest signal, identify an item of interest classification and provide a classification signal. The classification signal is determined by the item of interest classification and is utilized by the propulsion system, maneuvering system, vehicle control system, or buoyancy control system to avoid physical, electrical, acoustic, or thermal detection of the unmanned vehicle by the item of interest.