Provided is a method for relocating a solar power unit in response to a redeployment event. A first location of a deployed solar power unit may be determined. A processor may detect a redeployment event for the solar power unit at the first location. In response to the redeployment event, the processor may determine a new location for the solar power unit. The method may further comprise relocating the solar power unit to the new location.

An electric vehicle charging system capable of generating electricity by solar energy comprises a fixed solar panel (1) fixed on a roof, a movable solar panel (2), a solar panel state control device (3) and an intelligent voltage conversion and control module (4). The solar panel state control device is connected to the intelligent voltage conversion and control module, and controls stretched and contracted states of the movable solar panel, output voltages of the solar panel fixed on the roof and the movable solar panel are connected in parallel, and then are connected to the intelligent voltage conversion and control module, and the intelligent voltage conversion and control module controls the solar panel to generate a maximum conversion rate and a maximum charging power under different light intensities in different time periods, realizes docking with the electric vehicle, and controls charging.

An electric power generation system is disclosed to produce electrical energy. The electric power generation system includes a solar awning that is ideally carried by a vehicle that is operable under its own power or towed behind a lead vehicle. The solar awning has a solar base attached to the roof of the vehicle and a pair of solar arms that are hingedly connected to respective opposite sides of the solar base. Each of the solar base and the pair of solar arms has an array of solar panels that convert solar energy to electrical energy. The solar awning is folded from an open configuration for maximum exposure to the sun at which the solar arms lie side-by-side the solar base to a closed configuration for minimum exposure to the sun at which the solar arms rotate downwardly from the solar base to lie alongside the vehicle.

A solar array structure, such as for a spacecraft, uses thin solar array panels that, when in a stowed configuration, are stiffened by being bent or curved in one direction to be shaped like a section of a cylinder and placed within a rigid structural frame. As a curved solar panel is not as efficient as a flat panel directly facing the sun, the solar array panels are curved in their stowed configuration for launch only, but flatten after deployment by use of a partially flexible structural frame, where a rectangular frame is made of two opposing rigid sides and two opposing flexible sides, with a thin flexible solar panel attached to rigid sides only. The rigid sides are compressed during stowage to curve the panel before hold-down tensioning. The structure and panels return to their flat free state configuration after release.

A solar array structure, such as for a spacecraft, uses thin solar array panels that, when in a stowed configuration, are stiffened by being bent or curved in one direction to be shaped like a section of a cylinder and placed within a rigid structural frame. As a curved solar panel is not as efficient as a flat panel directly facing the sun, the solar array panels are curved in their stowed configuration for launch only, but flatten after deployment by use of a partially flexible structural frame, where a rectangular frame is made of two opposing rigid sides and two opposing flexible sides, with a thin flexible solar panel attached to rigid sides only. The rigid sides are compressed during stowage to curve the panel before hold-down tensioning. The structure and panels return to their flat free state configuration after release.

Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to, based on the satellite exiting the launch vehicle, enable release of magnets or locks of an array, a release controller to control the release of the magnets or the locks of the array based on a release sequence to autonomously deploy the solar array, and a sequence analyzer to adapt the release sequence during execution of the release sequence, wherein adapting the release sequence includes changing an order in which the magnets or the locks of the array are released based on a degree to which the solar array is unfolded.

Satellites having autonomously deployable solar arrays are disclosed. A disclosed example satellite includes a solar array, a sensor to detect that the satellite has exited a launch vehicle, a processor to, based on the satellite exiting the launch vehicle, enable release of magnets or locks of an array, a release controller to control the release of the magnets or the locks of the array based on a release sequence to autonomously deploy the solar array, and a sequence analyzer to adapt the release sequence during execution of the release sequence, wherein adapting the release sequence includes changing an order in which the magnets or the locks of the array are released based on a degree to which the solar array is unfolded.

A solar array structure for a spacecraft is based on a modular approach, allowing for arrays to be designed, and designed to be modified, and manufactured in reduced time and with reduced cost. The embodiments for the solar array are formed of multiple copies of a “bay” of a multiple strings of solar array cells mounted on semi-rigid face-sheet structural elements. The bays are then placed into frame structures made of tubes connected by nodes to provide an easily scalable, configurable, and producible solar array wing structure. This allows for rapid turnaround of program specific designs and proposal iterations that is quickly adaptable to new/future PhotoVoltaic (PV) technologies and that can create uniquely shaped (i.e., not rectangular) arrays, allowing for mass production with simple mass producible building blocks.

A solar array structure for a spacecraft is based on a modular approach, allowing for arrays to be designed, and designed to be modified, and manufactured in reduced time and with reduced cost. The embodiments for the solar array are formed of multiple copies of a “bay” of a multiple strings of solar array cells mounted on semi-rigid face-sheet structural elements. The bays are then placed into frame structures made of tubes connected by nodes to provide an easily scalable, configurable, and producible solar array wing structure. This allows for rapid turnaround of program specific designs and proposal iterations that is quickly adaptable to new/future PhotoVoltaic (PV) technologies and that can create uniquely shaped (i.e., not rectangular) arrays, allowing for mass production with simple mass producible building blocks.

The embodiments are apparatuses, systems and methods of water management and icicle prevention for solar carports, and are designed to catch drips between rows of, and water run-off from, the low side of inclined photovoltaic modules arranged to form the roof of the solar carport or canopy.