A UAV-carried surveillance and remote sensing platform is launched from a high altitude and flies over a target area, collecting remote sensing imagery before returning to earth. The UAV may be towed to a desired altitude by a powered aircraft or a balloon and then launched for cruising over a target area while capturing data. Instead of being piloted remotely, the UAV employs an autonomous flight control system.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

An aerial craft and sealed force vectoring flight system is disclosed. The aerial craft includes a main body hull, lift jets, a generator, an electrical re-introduction circuit, a hydraulic pump, air flow compressors, an RPM sensor, a max speed limiter hydraulic draft by-pass valve, and a battery. The electrical re-introduction circuit throttles the generator into high-velocity rotation and yields excess electrical current to then be applied to the lift jets. The hydraulic pump pulls pressurized hydraulic fluid across a preceding hydraulic drive impellor such that the pressurized hydraulic fluid returns to confinement under pneumatic pressure faster than a discharge of hydraulic fluid. The air flow compressors generate electricity that is re-introduced into the lift electric motors. The RPM sensor and max speed limiter hydraulic draft by-pass valve speed regulate the generator. The battery initially powers the generator.

An aerial craft and sealed force vectoring flight system is disclosed. The aerial craft includes a main body hull, lift jets, a generator, an electrical re-introduction circuit, a hydraulic pump, air flow compressors, an RPM sensor, a max speed limiter hydraulic draft by-pass valve, and a battery. The electrical re-introduction circuit throttles the generator into high-velocity rotation and yields excess electrical current to then be applied to the lift jets. The hydraulic pump pulls pressurized hydraulic fluid across a preceding hydraulic drive impellor such that the pressurized hydraulic fluid returns to confinement under pneumatic pressure faster than a discharge of hydraulic fluid. The air flow compressors generate electricity that is re-introduced into the lift electric motors. The RPM sensor and max speed limiter hydraulic draft by-pass valve speed regulate the generator. The battery initially powers the generator.

An aircraft that enables an efficient and safe transition from hovering to level-flight. The aircraft according to the present invention includes a lift generating part, a thrust generating part capable of flying and hovering, a connecting part that displaceably connects the lift generating part and the thrust generating part so that the lift generating part can maintain a positive angle of attack with respect to the flying direction at least at the time of ascending. The lift generating part is a wing part having a main surface, and at least at the time of hovering, a propulsion direction by the thrust generating part is along a direction obliquely intersecting the vertical direction. At least at the time of hovering, the propulsion direction and the main surface form an obtuse angle. At least at the time of hovering, the propulsion direction is along the vertical direction.

A rotary aircraft includes a cylindrical enclosure configured to form an open housing with a top opening and a bottom opening; a hover disc disposed within the open housing of the cylindrical enclosure and configured to direct airflow entering through the top opening, the hover disc forming a center opening; and a fan extending through the center opening of the hover disc and configured to direct airflow through the hover disc.

An aerial vehicle includes a fuselage, a wing, and a wing shift device. The wing shift device is configured to be coupled to the fuselage. The wing shift device comprises a plurality of apertures for coupling the wing to the aerial vehicle. The plurality of apertures are configured to permit the wing to be shifted in a forward or aft direction along the fuselage based on a center of gravity of the aerial vehicle.

An ejector system for propelling a vehicle. The system includes a diffusing structure and a duct coupled to the diffusing structure. The duct includes a wall having openings formed therethrough and configured to introduce to the diffusing structure a primary fluid produced by the vehicle. An airfoil is positioned within the flow of the primary fluid through the openings to the diffusing structure.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

An aircraft including: a pair of wings rotatably coupled to opposing lateral sides of the fuselage and being rotatable relative to each other; a pair of servo motors, each connected to a corresponding wing and configured to rotate the corresponding wing in two rotational directions; a pair of thrust motors, each of which mounted on a corresponding wing; and a flight controller connected to the servo motors and to the thrust motors, and configured to control each servo motor and each thrust motor, such that the aircraft can be selectively operated in a cruising mode, such that the pair of wings are in a non-permanent-rotation-state about a yawing axis which extends at least substantially through the center of gravity, and a monocopter mode, in which the pair of thrust motors provide thrust in opposite directions so that the pair of wings are in a permanent-rotation-state about the yawing axis.