A flight vehicle of an embodiment includes a wing, double-side generation type solar cells, and a light reflecting part. The wing has an outer shell member. The outer shell member has transmittance. The wing is formed by an outer shell member in a hollow shape. The solar cells are disposed on the upper surface of the wing. The light reflecting part is provided on an inner surface of the outer shell member.

The present disclosure discloses an energy management system suitable for a solar-powered unmanned aerial vehicle and a control method thereof, which are used for an aerospace vehicle energy system. The system comprises a photovoltaic module, an MPPT controller, a first DC-DC circuit, a battery pack, a first anti-reverse circuit, a second DC-DC circuit, a second anti-reverse circuit, an ESC, a BLDC, an on-board controller, a communication link and a voltage stabilizing module. During cruising, the battery pack directly supplies power to the ESC through the first anti-reverse circuit; when high-power power output is needed, the battery pack supplies power to the ESC through the second DC-DC circuit and the second anti-reverse circuit in sequence, wherein the output voltage of the second DC-DC circuit and the accelerator signal input of the ESC are controlled by the on-board controller.

A flight controller of a flight vehicle includes an electric motor control unit for controlling each of a plurality of electric motors, and in a case where the plurality of electric motors are driven by electric power stored in a battery or in a case where the battery is charged with electric power generated by a generator, the electric motor control unit controls the plurality of electric motors in accordance with the state of the battery.

Drones with propulsions systems supported in a housing are provided where the orientation of the housing is independent from the orientation of the propulsion system. Drones are provided where a propulsion system is rotatable about a first axis and a second axis that is perpendicular to the first axis, permitting the propulsion system to assume substantially any position with a sphere. Drones are provided where a bladeless inner tube is rotatable about a first axis and a second axis that is perpendicular to the first axis, permitting the inner tube to assume substantially any position within a sphere. Drone systems are provided with connectable unit drones. An unmanned land vehicle is provided having a wheel assembly that is rotatable about a first axis and a second axis that is perpendicular to the first axis, permitting the wheel assembly to assume substantially any position with a sphere.

Systems, devices, and methods including: at least one unmanned aerial vehicle (UAV); at least one battery pack comprising at least one battery; and at least one motor of the at least one UAV, where the at least one battery is configured to transfer energy to the at least one motor; where power from the at least one motor is configured to ascend the at least one UAV to a second altitude when the at least one battery is at or near capacity, and where the second altitude is higher than the first altitude; and where power from the at least one motor is configured to descend the at least one UAV to the first altitude after the Sun has set to conserve energy stored in the at least one battery.

The present invention is a variable geometry aircraft that is capable of morphing its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The aircraft may include variable span, length, and camber. The variability of the structure and the flexible envelope allows the aircraft to adjust its aspect ratio along with the camber of the upper and/or lower surfaces to achieve varying shapes. This transformation changes both the lift and drag characteristics of the craft and may be accomplished while the craft is airborne.

An antenna system is configured for use in Low Earth Orbit (LEO) around Earth. The system has a plurality of antenna satellites coupled together to form a phased array. Each of the plurality of antenna satellites have an antenna body with an antenna and a solar cell. A processing device determines an orientation of the plurality of antenna satellites and position the phased array in the orientation based on an analysis of the solar cell of the antenna bodies facing the sun, the antenna of the antenna bodies facing the Earth, and maintaining a torque equilibrium of the phased array.

There is provided a flight vehicle including: a wing unit; a main body unit; a battery that is arranged in the wing unit; a payload that is arranged in the main body unit; a radiator; and a heat pipe that exchanges heat between the battery, the payload, and the radiator and that has a check valve which causes a hydraulic fluid to be circulated to transfer the heat of the battery to the payload and the radiator.

A solar panel includes a substrate. The substrate includes a front portion and a back portion that are bonded together. The front portion includes an electrical insulation layer and a front face sheet layer that is bonded to the electrical insulation layer. The back portion includes a honeycomb core layer and a back face sheet layer that is bonded to the honeycomb core layer. A channel is defined in the honeycomb core layer. The solar panel also includes a first wire that is positioned at least partially in the channel.

A method for producing a solar panel includes producing a tile. Producing the tile includes bonding an electrical insulation layer and a front face sheet layer together to produce a front portion of a substrate. Producing the tile also includes bonding the front portion of the substrate and a cell together. Producing the tile also includes bonding the front portion of the substrate and a wire together. The method also includes bonding a honeycomb core layer and a back face sheet layer to produce a back portion of the substrate. The method also includes bonding the tile and the back portion of the substrate together to produce the solar panel.