A space-grade solar array includes relatively small cells with integrated wiring embedded into or incorporated directly onto a printed circuit board. The integrated wiring provides an interface for solar cells having back side electrical contacts. The single side contacts enable the use of pick and place (PnP) technology in manufacturing the space-grade solar array. The solar cell is easily and efficiently packaged and electrically interconnected with other solar cells on a solar panel such as by using PnP process. The back side contacts are matched from a size and positioning standpoint to corresponding contacts on the printed circuit board.

A space-grade solar array includes relatively small cells with integrated wiring embedded into or incorporated directly onto a printed circuit board. The integrated wiring provides an interface for solar cells having back side electrical contacts. The single side contacts enable the use of pick and place (PnP) technology in manufacturing the space-grade solar array. The solar cell is easily and efficiently packaged and electrically interconnected with other solar cells on a solar panel such as by using PnP process. The back side contacts are matched from a size and positioning standpoint to corresponding contacts on the printed circuit board.

Disclosed is a circulation type space-based solar power system, the system including: one or more solar modules; a conveyor belt on which the solar modules are attached, whereby the solar modules move between a solar power generating position and a recovery position, the solar modules receiving sunlight to generate solar power in the solar power generating position, and not receiving sunlight in the recovery position; a driver moving the conveyor belt; and a protective plate blocking cosmic rays incident to the solar modules located in the recovery position. The system can generate solar power for a long time by moving the solar modules between the solar power generating position and the recovery position. While some of the solar modules generate solar power, the remaining solar modules having damage are recovered.

Disclosed is a circulation type space-based solar power system, the system including: one or more solar modules; a conveyor belt on which the solar modules are attached, whereby the solar modules move between a solar power generating position and a recovery position, the solar modules receiving sunlight to generate solar power in the solar power generating position, and not receiving sunlight in the recovery position; a driver moving the conveyor belt; and a protective plate blocking cosmic rays incident to the solar modules located in the recovery position. The system can generate solar power for a long time by moving the solar modules between the solar power generating position and the recovery position. While some of the solar modules generate solar power, the remaining solar modules having damage are recovered.

A method of fabricating a four junction solar cell by identifying the composition and band gaps of the upper first, second and third subcells that maximizes the efficiency of the solar cell at a predetermined time after initial deployment by simulation; fabricating one or more four-junction test solar cells in accordance with the identified composition and band gaps of the upper first, second and third subcells; performing one or more optical or electrical tests on the fabricated one or more four-junction test solar cells; based on results of the tests, determining one or more properties of at least one of the upper first, second or third subcells to be modified in subsequent fabrication of four-junction solar cells, including the band gap, doping level and profile, and thickness of each of the subcell layers; and fabricating a further four-junction solar cell in accordance with the modified properties of at least one of the upper first, second or third subcells to optimize the efficiency of the solar cell at the predetermined time.

A spacecraft (10), comprising a body (12), a solar array (30) with a support panel (32) which is connected to the body, and a thermal radiator (50) that is connected to the body and which includes a radiator substrate (52) that is thermally coupled to the body via at least one heat link (64). The solar array and thermal radiator are configured to be transitioned from a stowed state wherein the support panel and the radiator substrate are held fixed in an overlapping arrangement along and near the body, to a deployed state wherein the solar array is unfolded with the support panel positioned at a distance from the body and the radiator substrate is folded away from the body and the solar array.

Preferably, the solar array and thermal radiator are flexible, to allow them to be kept in an overlapping and temporarily bent shape in the stowed state.

A spacecraft (10), comprising a body (12), a solar array (30) with a support panel (32) which is connected to the body, and a thermal radiator (50) that is connected to the body and which includes a radiator substrate (52) that is thermally coupled to the body via at least one heat link (64). The solar array and thermal radiator are configured to be transitioned from a stowed state wherein the support panel and the radiator substrate are held fixed in an overlapping arrangement along and near the body, to a deployed state wherein the solar array is unfolded with the support panel positioned at a distance from the body and the radiator substrate is folded away from the body and the solar array.

Preferably, the solar array and thermal radiator are flexible, to allow them to be kept in an overlapping and temporarily bent shape in the stowed state.

A method of manufacturing a solar cell assembly by providing a substrate; depositing on the substrate a sequence of layers of semiconductor material forming a solar cell; mounting a permanent laminate supporting member with a thickness of 50 microns or less on top of the sequence of layers; utilizing the laminate structure for supporting the epitaxial sequence of layers of semiconductor material forming a solar cell during the processes of removing the substrate and depositing and lithographically patterning a plurality of metal grid lines disposed on the top surface of the first solar subcell, and attaching a cover glass over at least the grid lines of the solar cell.

A method of manufacturing a solar cell assembly by providing a substrate; depositing on the substrate a sequence of layers of semiconductor material forming a solar cell; mounting a permanent laminate supporting member with a thickness of 50 microns or less on top of the sequence of layers; utilizing the laminate structure for supporting the epitaxial sequence of layers of semiconductor material forming a solar cell during the processes of removing the substrate and depositing and lithographically patterning a plurality of metal grid lines disposed on the top surface of the first solar subcell, and attaching a cover glass over at least the grid lines of the solar cell.

A monolithic metamorphic multi-junction solar cell comprising a first III-V subcell and a second III-V subcell and a third III-V subcell and a fourth Ge subcell, wherein the subcells are stacked on top of each other in the indicated order, and the first subcell forms the topmost subcell, and a metamorphic buffer is formed between the third subcell and the fourth subcell and all subcells each have an n-doped emitter layer and a p-doped base layer, and the emitter layer of the second subcell is greater than the base layer.