An adjustable tension kite holding and release apparatus, which has an apparatus head, and an apparatus body having an adjustable thumbscrew coupled to the apparatus body, and first and second ring grippers having first and second bumps providing a ring gripping mechanism at a distal end of the apparatus body. The ring gripping mechanism holding a releasable ring, running a fishing line through the releasable ring, tightening the adjustable thumbscrew such that the ring gripping mechanism applies tension to the releasable ring, and increasing or decreasing the tension based on an estimated force desired to release the releasable ring.

An aircraft can include a first wing and a second wing. The first wing can extend laterally from an aircraft body to a first tip, and the second wing can extend laterally from the aircraft body to a second tip. The aircraft can include a first end effector and a second end effector, each including a fore winglet and an aft winglet. The fore and aft winglets of the first end effector can be pivotably connected to the first tip. The fore and aft winglets of the second end effector can be pivotably connected to the second tip. The fore and aft winglets of the first and second end effectors can be independently operable. The first and second end effectors can be independently operable. A processor can be operatively connected to control movement of the fore and aft winglets of the first and second end effectors.

An aircraft can include a first wing and a second wing. The first wing can extend laterally from an aircraft body to a first tip, and the second wing can extend laterally from the aircraft body to a second tip. The aircraft can include a first end effector and a second end effector, each including a fore winglet and an aft winglet. The fore and aft winglets of the first end effector can be pivotably connected to the first tip. The fore and aft winglets of the second end effector can be pivotably connected to the second tip. The fore and aft winglets of the first and second end effectors can be independently operable. The first and second end effectors can be independently operable. A processor can be operatively connected to control movement of the fore and aft winglets of the first and second end effectors.

An aircraft can include a first wing and a second wing. The first wing can extend laterally from an aircraft body to a first tip, and the second wing can extend laterally from the aircraft body to a second tip. The aircraft can include a first end effector and a second end effector, each including a fore winglet and an aft winglet. The fore and aft winglets of the first end effector can be pivotably connected to the first tip. The fore and aft winglets of the second end effector can be pivotably connected to the second tip. The fore and aft winglets of the first and second end effectors can be independently operable. The first and second end effectors can be independently operable. A processor can be operatively connected to control movement of the fore and aft winglets of the first and second end effectors.

An aircraft can include a first wing and a second wing. The first wing can extend laterally from an aircraft body to a first tip, and the second wing can extend laterally from the aircraft body to a second tip. The aircraft can include a first end effector and a second end effector, each including a fore winglet and an aft winglet. The fore and aft winglets of the first end effector can be pivotably connected to the first tip. The fore and aft winglets of the second end effector can be pivotably connected to the second tip. The fore and aft winglets of the first and second end effectors can be independently operable. The first and second end effectors can be independently operable. A processor can be operatively connected to control movement of the fore and aft winglets of the first and second end effectors.

A propulsion system for providing propulsion of an aircraft includes a plurality of electric motors coupled with a rotor of the aircraft to drive the rotor and a propulsion motor control. The propulsion motor control includes at least one processor electrically connected with at least one electric motor to actuate the at least one electric motor and at least one battery electrically connected with the at least one processor and at least one electric motor to provide power to the at least one processor and the at least one electric motor. The propulsion motor control actuates the plurality of electric motors based on a desired torque level to drive the rotor to provide propulsion of the aircraft.

The present invention refers to an airborne system (100′) and in particular to an airborne power generation system (100). The airborne power generation system (100) comprises an airborne unit (10) configured (i) as an aerial vehicle (10′), in particular as a kite or a multicopter, and (ii) to harvest and convert wind power into electrical power, a ground unit (50) configured to send and/or receive electrical power to and from the airborne unit (10), respectively, and a coupling and tether unit (30) for mechanically and electrically coupling the airborne unit (10) to the ground unit (50) and configured to transmit electrical power between the airborne unit (10) and the ground unit (50). The airborne unit (10) comprises a plurality of motor/generator units (12) each of which having a wind harvesting/propelling rotor (14) mechanically coupled thereto and groups (16) of motor/generator units (12) and their assigned electrical transmission paths are electrically and/or galvanically uncoupled, insulated, isolated and/or separated with respect to each other at least in the airborne unit (10) and the coupling and tether unit (30).

The present invention refers to an airborne system (100′) and in particular to an airborne power generation system (100). The airborne power generation system (100) comprises an airborne unit (10) configured (i) as an aerial vehicle (10′), in particular as a kite or a multicopter, and (ii) to harvest and convert wind power into electrical power, a ground unit (50) configured to send and/or receive electrical power to and from the airborne unit (10), respectively, and a coupling and tether unit (30) for mechanically and electrically coupling the airborne unit (10) to the ground unit (50) and configured to transmit electrical power between the airborne unit (10) and the ground unit (50). The airborne unit (10) comprises a plurality of motor/generator units (12) each of which having a wind harvesting/propelling rotor (14) mechanically coupled thereto and groups (16) of motor/generator units (12) and their assigned electrical transmission paths are electrically and/or galvanically uncoupled, insulated, isolated and/or separated with respect to each other at least in the airborne unit (10) and the coupling and tether unit (30).

An aerial vehicle (10) has an aerial platform (12) that supports lift elements (11), an engine (14) and a fuel supply (15) and that has a coupling mechanism (16) adapted for coupling to a removable load (17). The lift elements include a soft or flexible wing (11) flexibly coupled to the aerial platform at points of suspension on opposite sides of the aerial platform whose location (A, B) relative to a longitudinal axis of the platform is such that the aerial platform and the attached load has a center of gravity (C.G.) which maintains balance of the aerial platform. An adjustment system (18) is coupled to the points of suspension and is operative for moving the points of suspension relative to the longitudinal axis of the platform when cargo is unloaded from the flying platform to preserve balance.

Disclosed is a collapsible kite frame that permits at kite to be fit into an economical shipping box, thereby significantly decreasing the costs associated with shipping. The kite frame utilizes a double revolute joint to connect the support members of a kite frame. A support sheath locks the joint and support members in a straight alignment, but, when removed, the support members are free to rotate and move inward, towards each other, thereby shortening the combined length span of the support members when in a straight alignment.