Some embodiments include a high efficiency, lightweight solar sheet. Some embodiments include a solar sheet configured for installation on a surface of a UAV or on a surface of a component of a UAV. The solar sheet includes a plurality of solar cells and a polymer layer to which the plurality of solar cells are attached. Some embodiments include a kit for supplying solar power in a battery-powered or fuel cell powered unmanned aerial vehicle (UAV) by incorporating flexible solar cells into a component of a UAV, affixing flexible solar cells to a surface of a UAV, or affixing flexible solar cells to a surface of a component of a UAV. The kit also includes a power conditioning system configured to operate the solar cells within a desired power range and configured to provide power having a voltage compatible with an electrical system of the UAV.

A solar mobile electronic device includes: a power supply device, including a battery in electric connection with a first voltage display module and outputting a first output voltage, the first voltage display module measuring and displaying the magnitude of the first output voltage; a solar power supply device, including at least one solar panel and a voltage display and control device, the solar panel in electric connection with the voltage display and control device and converting solar energy to a second output voltage, the voltage display and control device configured with a second voltage adjusting module and a second voltage display and control module also in electric connection with the first voltage display module, the second voltage display and control module controlling and displaying the magnitude of the second output voltage through the second voltage adjusting module and having a dynamic comparison unit adapted to set a predetermined voltage value.

An aircraft comprising a hydrogen-containing envelope, a water-collection system for collecting water from the envelope, an electrolyser to convert the water collected using the water-collection system into hydrogen, and a hydrogen-replenishment system for replenishing the envelope with hydrogen generated using the electrolyser. In one embodiment, generated hydrogen is also supplied to a hydrogen-fueled propulsion system for propulsion of the aircraft.

A vehicle such as an aircraft on which a solar cell assembly is mounted on a surface of the space vehicle. The solar cell assembly may be prepared on an assembly fixture. The solar cell assembly may then be removed from the assembly fixture and positioned on a top surface of the streamlined body of the vehicle. In examples, the solar cell assembly comprises a first film, an array of solar cells on top of the first film, and a second silicone film deposited over the solar cells.

A system is presented. The system comprises sunlight sensors and GPS receivers in a region, an aerial vehicle, a solar panel, and a flight plan generator. The aerial vehicle is within the region. The aerial vehicle has a rechargeable battery. The solar panel is physically connected to the aerial vehicle and operably connected to the rechargeable battery. The flight plan generator is configured to create a flight plan within the region for the aerial vehicle based on measurements from the sunlight sensors within the region.

Various aspects provide for a solar assembly. The solar assembly may be a mechanical structure that allows many small solar cells to be integrated into the wing design of an aircraft without placing them on the surface area of the wing or the vehicle. Additional aspects may provide for an adjustable solar assembly. The adjustable solar assembly may be configured to be installed into a structure having a structural profile. When installed, the solar assembly may conform to the structural profile such that the structural profile is maintained. The solar assembly may further comprise an adjustable carrier system comprising a plurality of solar cells attached thereto. The adjustable carrier system may be configured to dynamically adjust the orientation of the solar cells so as to maintain an optimal angle with respect to an external light source.

An aircraft includes a substrate having a curvature to form a lift surface, a plurality of solar cells carried by, bonded to, and impressed into the substrate, and electrical connections between the solar cells carried by the substrate. The electrical connections coupled to link the solar cells together to provide power to the aircraft while in flight.

Autonomous craft capable of extended duration operations as lighter-than-air craft, having the ability to alight on the surface of a body of water and generate hydrogen gas for lift via electrolysis using power derived from a photovoltaic system, as well as methods of launching an unmanned aerial vehicle (UAV) having a deployable envelope from a surface of a body of water.

An aircraft system includes a wing member and a plurality of unmanned aircraft systems selectively connectable to the wing member. The wing member has a generally airfoil cross-section, a leading edge and a trailing edge. The unmanned aircraft systems have a connected flight mode while coupled to the wing member and an independent flight mode when detached from the wing member. In the connected flight mode, the unmanned aircraft systems are operable to provide propulsion to the wing member to enable flight. The unmanned aircraft systems are operable to be launched from the wing member to perform aerial missions in the independent flight mode and are operable to be recovered by the wing member and returned to the connected flight mode. Thereafter, in the connected flight mode, the unmanned aircraft systems are operable to be resupplied by the wing member.

A solar cell module for an unmanned aerial vehicle is disclosed. The solar cell module includes a carrier base and a solar cell unit. The carrier base is disposed on the unmanned aerial vehicle. The solar cell unit has a plurality of solar cells attached to the carrier body. A ratio of the power provided by the solar cell unit to the weight of the solar cell module is equal to or greater than 0.1 (W/g).