A tri-wing aircraft includes a fuselage having a longitudinally extending fuselage axis. Three wings extend generally radially outwardly from the fuselage axis and are circumferentially distributed generally uniformly about the fuselage at approximately 120-degree intervals. The wings have airfoil cross-sections including first and second surfaces having chordwise channels therebetween. A distributed propulsion system includes a plurality of propulsion assemblies. Each propulsion assembly includes a variable thrust cross-flow fan disposed within one of the chordwise channels of one of the wings. At least two variable thrust cross-flow fans are disposed within the chordwise channels of each of the wings. A flight control system is operably associated with the distributed propulsion system such that the flight control system and the distributed propulsion system are operable to generate a triaxial dynamic thrust matrix.

A method for controlling a thrust vectored aircraft includes mapping aircraft control commands with a flight controller through a number of transformations including: transforming, with the flight controller, a command space into an inner-mixing space, which comprises of at least a pair of two orthogonal force components located at each thrusting motor; transforming, with the flight controller, the inner-mixing space into an outer-mixing space, which comprises a thrust angle and thrust magnitude pair located at each thrusting motor; and generating output commands with the flight controller.

A method for controlling a thrust vectored aircraft includes mapping aircraft control commands with a flight controller through a number of transformations including: transforming, with the flight controller, a command space into an inner-mixing space, which comprises of at least a pair of two orthogonal force components located at each thrusting motor; transforming, with the flight controller, the inner-mixing space into an outer-mixing space, which comprises a thrust angle and thrust magnitude pair located at each thrusting motor; and generating output commands with the flight controller.

Aspects described herein may relate to aerial structures such as aircraft. An aerial structure may include a fuselage, a wing attached to the fuselage, and a plurality of propulsion systems configured to generate thrust. A propulsion system may include a plurality of propulsors, such as propulsor fans. A propulsor fan may be configured to be actuated between a conventional take-off and landing (CTOL) flight mode, a short take-off and landing (STOL) flight mode, and a vertical take-off and landing (VTOL) flight mode.

A differential thrust vectoring system includes a first thruster, a second thruster, a main actuator, and a trim actuator. The system is configured such that actuation of the main actuator causes rotation of the thrusters together about an axis, whereas actuation of the trim actuator causes relative rotation of the first and second thrusters about the axis.

A differential thrust vectoring system includes a first thruster, a second thruster, a main actuator, and a trim actuator. The system is configured such that actuation of the main actuator causes rotation of the thrusters together about an axis, whereas actuation of the trim actuator causes relative rotation of the first and second thrusters about the axis.

An amphibious vertical takeoff and landing (VTOL) unmanned device is provided. The amphibious VTOL unmanned device includes a modular and expandable waterproof body, an outer body shell, a gimbaled swivel propulsion system comprising a plurality of VTOL jet engines and VTOL ducted fans, a processor, electronic speed controllers, a two-way telemetry device, a video transmitter, a radio control receiver, a power distribution board, an electrical machine, an onboard electricity generator comprising a plurality of solar cells, a light detection and ranging device, an ultrasonic radar sensor, a plurality of sensors, a tail configured to stabilize the amphibious VTOL unmanned device, a head VTOL ducted fan adapted for VTOL, a plurality of wheels, a plurality of foldable wings configured to create a pressure difference and creating a lift, a plurality of parachutes configured to safely land the amphibious VTOL unmanned device in an emergency.

The invention pertains to an automobile and more particularly, to a flying car. A flying car, comprises a body, adapted for carrying the payload from once place to another, a tail attached to body at rear end adapted for stabilizing the vehicle, plurality of wheels at the bottom of car connected to a power transmission system, plurality of foldable wings on the sides of body, adapted for creating the pressure difference and creating lift to the vehicle. Further, plurality of jet engines adapted for driving the jet flying car on surface as well as on air. A gimbaled swivel propulsion (GSP) thrust vector control, to controls the direction of the thrust generated by the engines. And plurality of parachutes attached to the flying jet car to safe land the flying jet car under emergency.

The aircraft thrust control system comprises a central power unit and peripheral power units. The central power unit comprises upper and lower propellers arranged one above the other and adapted to rotate in opposite directions, while propellers of the peripheral power units are located outside the aerodynamic operating range of the central power unit propellers.

The aircraft thrust control system comprises a central power unit and peripheral power units. The central power unit comprises upper and lower propellers arranged one above the other and adapted to rotate in opposite directions, while propellers of the peripheral power units are located outside the aerodynamic operating range of the central power unit propellers.