An aircraft airfoil or wing or fuselage MODULE is fitted with a gas turbine engine driving a fan or propeller, in combination with a gaseous pressure accumulator, wherein said fan or propeller and said gaseous pressure accumulator both provide thrust, said fan thrust being provided from a rear of the MODULE via a drop-down thrust vectoring panel and said gaseous pressure accumulator thrust being provided from a fore of said MODULE, wherein the gaseous pressure accumulator is supplied with exhaust from said gas turbine engine and said exhaust is delivered downwardly at a variable angle, and said thrust vectoring panel is a panel with multiple minor panels which vector fan thrust at more than one angle. The gas turbine engine exhaust is delivered forwardly of said fan or propeller exhaust.

Systems and methods to reduce aerodynamic drag and/or affect flight characteristics of an aerial vehicle may include adjustable fairings associated with one or more components of the aerial vehicle. The adjustable fairings may be coupled to and at least partially surround a motor, propulsion mechanism, motor arm, strut, or other component of an aerial vehicle. In addition, the adjustable fairings may be passively movable between two or more positions responsive to airflow around the fairings, and/or the adjustable fairings may be actively moved between two more positions to affect flight characteristics. Further, the adjustable fairings may include actuatable elements to alter a portion of an outer surface of the fairings to thereby affect flight characteristics. In this manner, adjustable fairings associated with various components of an aerial vehicle may reduce aerodynamic drag and/or may improve control and safety of an aerial vehicle.

The present invention includes pilotable capsules, detachable from an aircraft and aircrafts including such capsules. According to some embodiments, there may be provided one or more capsules capable of flight and designed to detachably connect to an aircraft. According to some embodiments, detachable capsules may be designed to carry cargo and/or passengers. According to some embodiments, detachable capsules may, after detachment, be piloted by pilots or by automated systems (unmanned) or a combination of the two.

A vertical-takeoff aircraft with a wing. A first drive unit and a second drive unit are swivellably mounted on the wing. The first drive unit and the second drive unit are arranged on the wing at a distance from a wing-end of the wing. A first distance between the first drive unit and a longitudinal axis of the aircraft is approximately equal to a second distance between the second drive unit and the longitudinal axis of the aircraft. The first drive unit and the second drive unit are swivellable into a horizontal flying position and a vertical flying position. In the horizontal flying position the first drive unit is arranged above a wing surface and the second drive unit below the wing surface on the wing. In the vertical flying position the first drive unit and the second drive unit are arranged in an approximately horizontal plane. The first drive unit and the second drive unit each have a swivel arm, wherein the swivel arms are swivellably mounted on the wing.

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.

This aircraft is a Vertical Take Off and Landing Fighter type. The primary power source will be a low bypass jet turbine/engine. The auxiliary power source will be provided by axial flux electric motors. These motors will be housed in a moveable section, the EVTOL apparatus, that houses multiple turbines. These moveable sections will be attached to sides of the fuselage, extending into the dual wing. These moveable sections will move to a vertical position during take-off and landing; and be in a horizontal position during normal flight. These moveable sections will have an intake area aft, and vectoring thrust at the rear. This aircraft is a hybrid utilizing a gas jet turbine and electrical axial flux motors. The EVTOL apparatus is a compact self-contained unit capable of generating thrust through a turbine driven by Axial Flux electric motors.

An aircraft is provided that is convertible in flight between a rotary wing configuration and a fixed wing configuration. In its fixed wing configuration the aircraft resembles a Blended Wing Body (BWB) having a swept wing angle . Conversions from the fixed wing configuration to the rotary wing configuration, and vice versa, are accomplished by flipping an outboard portion of one wing through 180 to reorient the leading edge of the outboard portion by an angle of 2 to establish a reverse sweep. In its rotary configuration, the entire aircraft is rotated.

An electric aircraft is capable of vertically taking off and landing. The aircraft includes a fuselage, front and rear power units, power pods, main wings, ailerons, front landing gears, a tail wing and a rear landing gear. The power units include first and second electric duct groups. The first electric duct group includes two electric duct fans symmetrically and connected to two sides of a front portion of the fuselage respectively. The second electric duct group includes two electric duct fans symmetrically provided at two sides of a rear portion of the fuselage respectively. The power pods are configured to connect the fuselage to the first electric duct group. The two main wings are symmetrically and foldably connected to two sides of the fuselage respectively. The two ailerons are symmetrically connected to front ends of the two main wings respectively.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one tail conduit is fluidly coupled to the generator. First and second fore ejectors are 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 includes a closed wing having a leading edge and a trailing edge. The leading and trailing edges of the closed wing define an interior region. The at least one propulsion device is at least partially disposed within the interior region.

[Object] To detect airspeed and an airflow direction with respect to an airframe of a motorized aircraft with high accuracy without increasing the cost and weight and rapidly control attitudes of an electric propulsion system and the airframe in accordance with fluctuations of the airspeed and airflow direction. [Solving Means] An electric propulsion system control device includes: a first airspeed measurement unit that is mounted on an airframe of an aircraft and includes a first propulsion system parameter detector that detects a propulsion system parameter, the propulsion system parameter being a parameter of an electric propulsion system, the electric propulsion system being driven by an electric motor and rotating about a rotation axis as a center, and a first airspeed calculator that calculates first airspeed on a basis of the propulsion system parameter, the first airspeed being airspeed with respect to a first direction that is a direction of the rotation axis; a second airspeed measurement unit that is mounted on the airframe and measures second airspeed, the second airspeed being airspeed with respect to a second direction different from the first direction; and an airflow calculator that calculates airspeed and airflow direction with respect to the airframe on a basis of the first direction and the first airspeed and the second direction and the second airspeed.