A vehicle-based airborne wind turbine system having an aerial wing, a plurality of rotors each having a plurality of rotatable blades positioned on the aerial wing, an electrically conductive tether secured to the aerial wing and secured to a ground station positioned on a vehicle, wherein the aerial wing is adapted to receive electrical power from the vehicle that is delivered to the aerial wing through the electrically conductive tether; wherein the aerial wing is adapted to operate in a flying mode to harness wind energy to provide a first pulling force through the tether to pull the vehicle; and wherein the aerial wing is also adapted to operate in a powered flying mode wherein the rotors may be powered so that the turbine blades serve as thrust-generating propellers to provide a second pulling force through the tether to pull the vehicle.

A flying apparatus is provided that comprises a airfoil (1) with a streamlined profile for generating an aerodynamic lift force vector (L) acting on the flying apparatus when being exposed to an apparent air flow. The flying apparatus also comprises at least three drive units (4, 42; 5, 51; 6, 61) being adapted to generate a resulting thrust force vector acting on the flying apparatus, the thrust force vector being alignable essentially in parallel with the aerodynamic lift force vector (L). For controlling the aerodynamic pitch of the flying apparatus, the flying apparatus comprises at least one control surface (31, 11). Furthermore, the flying apparatus has an aerodynamic neutral point (NP) that lies, along the longitudinal centre axis (10) and in the direction from the leading edge (17) to the trailing edge (18) of the airfoil (1), behind the centre of gravity (CG) of the flying apparatus.

A flying apparatus is provided that comprises a airfoil (1) with a streamlined profile for generating an aerodynamic lift force vector (L) acting on the flying apparatus when being exposed to an apparent air flow. The flying apparatus also comprises at least three drive units (4, 42; 5, 51; 6, 61) being adapted to generate a resulting thrust force vector acting on the flying apparatus, the thrust force vector being alignable essentially in parallel with the aerodynamic lift force vector (L). For controlling the aerodynamic pitch of the flying apparatus, the flying apparatus comprises at least one control surface (31, 11). Furthermore, the flying apparatus has an aerodynamic neutral point (NP) that lies, along the longitudinal centre axis (10) and in the direction from the leading edge (17) to the trailing edge (18) of the airfoil (1), behind the centre of gravity (CG) of the flying apparatus.

An airship dynamic adaptive harness is provided to stabilize airships and particularly a tethered aerostat in high winds and atmospheric changes. A novel adaptive device accommodates the supply of a lift gas and simultaneously controls opposing cables in a tethered harness with a cascade control system that provides an immediate and particularly the dynamic control of roll, yaw and particularly the pitch of the aerostat in response to real time environmental flight conditions and impart stability to the airship in high winds using a stability zone geometric suspension control system and enhance the duration of in flight missions. A lifting gas replenishment system and particularly a ground based lifting gas replenishment system adds long duration deployment to the dynamic adaptability to high wind conditions for long term deployment.

A tethered unmanned aerial system (UAS) is described, wherein the flight of one or more UASs may be used in connection with a water and light display.

A tethered unmanned aerial system (UAS) is described, wherein the flight of one or more UASs may be used in connection with a water and light display.

A flying machine includes: a flying machine body that includes a rotor blade; a protective member that forms a frame shape inside which the rotor blade is disposed, that is rotatably fixed to both end portions of the flying machine body, and that is pipe shaped; and a connecting wire that passes through an inner portion of the protective member to connect the flying machine body and an external device together.

Short takeoff and landing aircraft are disclosed. An example fixed wing aircraft includes a primary power source to provide power to a propulsion unit, a secondary power source to provide power to the propulsion unit, and a detachable power coupling to transfer power to the secondary power source from a source external to the fixed wing aircraft during takeoff.

Short takeoff and landing aircraft are disclosed. An example fixed wing aircraft includes a primary power source to provide power to a propulsion unit, a secondary power source to provide power to the propulsion unit, and a detachable power coupling to transfer power to the secondary power source from a source external to the fixed wing aircraft during takeoff.

A reactive tether spool comprises a drum, a signal cable, a drum actuator, a tension sensor, and a controller. The signal cable transports power and a control signal to a UAV. A controller receives a tension measurement from the tension sensor and controls the drum actuator to maintain a determined tension on the signal cable while performing at least one of the following: dispensing the signal cable; holding the signal cable steady; and collecting the signal cable.