An aircraft includes a body defining an interior compartment configured to hold at least one of a passenger and a payload, a battery system, a plurality of arms coupled to and extending from the body, and a plurality of propulsion devices configured to provide thrust to fly the aircraft. Each of the plurality of propulsion devices is coupled to a respective one of the plurality of arms. The plurality of propulsion devices are powered by the battery system. Each of the plurality of propulsion devices is selectively pivotable about at least one axis. The plurality of propulsion devices include at least one of (i) counter rotating ducted fans and (ii) ionizing electrode engines.

Systems for transmitting power to and from flight vehicles, and associated devices and methods are described herein. A representative flight power-transmission system includes a surface-based transmitter on or adjacent to the surface of the Earth, a flight platform remote from the surface-based transmitter, and a free electron laser (FEL) carried by the flight platform. The transmitter is configured to transmit electromagnetic radiation to the FEL, and the FEL is configured to receive at least a portion of the electromagnetic radiation from the FEL and generate a laser beam based at least in part on the received electromagnetic radiation. The flight platform can be an aerostat positioned at high altitude within the stratosphere. The FEL can direct the laser beam for one or more end uses, such as (i) supplying power to a downrange electric aircraft, (ii) supplying power to a surface-based receiver, (iii) providing directed-energy for destroying or disabling a target, and/or (iv) providing directed-energy for clearing orbital debris.

An air duct system for an aircraft provides passengers with light, data, electrical power, and sanitized air. The air duct system includes an air duct having a main body and a visible light source configured to generate visible light, where the visible light is modulated by one or more controllers based on a visible light communication protocol. The air duct system simultaneously achieves four functions for improving passengers' flying experience. First, a portion of the visible light transmitted by the air duct illuminates the interior cabin of the aircraft. Second, by modulating the visible light, the air duct system transmits and distributes data that is received by the passengers' electronic devices. Third, a portion of the visible light is converted into electrical power at each passenger seat to power passengers' electronic devices. Fourth, in embodiments, the visible light is emitted at a germicidal wavelength spectrum to create sanitized air.

Systems, methods, and devices are provided herein for improving the power performance of vehicle. A hybrid power system may comprise a power controller adapted to be in communication with a first power source, a second power source, and a load. The power controller may be configured to detect whether a current drawn by the load exceeds a predetermined threshold, control discharging of the first power source without permitting discharging of the second power source to power the load when the current drawn by the load is less than the predetermined threshold current, and control discharging of the first power source and the second power source to power the load when the current drawn by the load is greater than the predetermined threshold current.

Various embodiments of a solar wing are disclosed. A solar wing sail generates power from a series of parallel, spaced-apart solar rib assemblies, each assembly having a solar array mounted on top. A sail is formed of transparent material that surrounds the solar rib assemblies, forming an airfoil. The power generated by the solar wing sail can be used to charge batteries and operate onboard electronics.

A system for redirecting sunlight to a mobile platform includes a satellite and a mobile platform including a first RF antenna that transmits a message including a position and velocity of the mobile platform on the path, along with a time of transmission, and a photovoltaic cell that receives and converts light into electrical energy. The satellite includes a second RF antenna that receives the message, an optical channel, a collector system coupled to the optical channel and that gathers sunlight into the optical channel, a diffuser system coupled to the optical channel and that diffuses light therefrom to generate a beam of light, and a processor coupled to the second RF antenna. The processor computes a target position of the mobile platform based on the position, the velocity, and the time of transmission, and instructs the diffuser system to direct the beam to the target position.

A secondary UAV flies over the solar-powered UAV at night and illuminates the solar-powered UAV's solar panels to help supplement the solar-powered UAV's battery charge mid-flight. The secondary UAV could be equipped with a directional light source for providing light of a color and intensity selected for optimal absorption by the solar cells of the solar-powered UAV. As the secondary UAV flies over the solar-powered UAV, the secondary UAV could thus direct its light source at the solar-powered UAV for absorption by the solar cells, to help supplement the solar-powered UAV's battery charge. Further, the secondary UAV could potentially recharge multiple solar-powered UAVs during a single nighttime mission.

An airfoil body for an aircraft extending from an inner end to an outer end, between a leading edge and a trailing edge and having a pressure surface and a suction surface, the airfoil body having an outer surface and an inner support structure, the outer surface including a fixed skin section and a movable skin section, wherein the movable skin section comprises a first portion including an array of transducer elements, and the airfoil body including an actuator for moving the movable skin section to selectively position the transducer elements on the outer surface.

A lighter than air airship (1) comprising a gas-filled flexible hull (2) which is elongate with a longitudinal axis (1) and with a front end (4) and a rear end (5), wherein a harness-structure (3) is abutting an outer side of the hull (2) and not perturbing the hull and not extending through the hull, the harness-structure (3) is made of a bendable material and carries a propeller engine (10) for forward thrust of the airship (1), rechargeable batteries (11) for providing electrical power to the propeller engine (10), and a solar panel for providing electrical power to recharge the batteries (11).

The disclosure relates to an airfoil body for an aircraft extending from an inner end to an outer end, and between a leading edge and a trailing edge. The airfoil body comprises an internal structure and a skin covering the internal structure. The skin has a pressure side and a suction side, and the suction side includes a light transmitting portion. The internal structure includes an array of solar cells configured to receive solar light through the light transmitting portion. The present disclosure further relates to wings and aerial vehicles.