Abstract: A solar panel for a spacecraft has a base with a face, and at least one row of solar cells and at least one elongated reflector are mounted on the face of the base. The reflectors and the rows are mounted generally parallel to each other in an alternating fashion. The reflector has first and second reflecting sides when the reflector is in a deployed position. The reflector is mounted so that the first side of the reflector is adjacent to a row of solar cells and reflects radiation incident on the first side onto the adjacent row of solar cells when the reflector is in a deployed position. Preferably, a plurality of rows and a plurality of reflectors are mounted on the face of the base, with at least one of the reflectors being disposed between two adjacent rows of solar cells.

Abstract: A solar panel for a spacecraft has a base with a face, and at least one row of solar cells and at least one elongated reflector are mounted on the face of said base. The reflectors and the rows are mounted generally parallel to each other in an alternating fashion. The reflector has a first and a second reflecting side when the reflector is in a deployed position. The reflector is mounted so that the first side of the reflector is adjacent to a row of solar cells and reflects radiation incident on the first side onto the adjacent row of solar cells when said reflector is in a deployed position. Preferably, a plurality of rows and a plurality of reflectors are mounted on the face of the base, with at least one of the reflectors being disposed between two adjacent rows of solar cells.

Abstract: A crankset for a bicycle in which the crankshaft separates into two pieces. The separation point is approximately midway between the support bearings for the crankshaft, creating two crankarm/spindle portions. Dowel pins and a bolt are used to connect the two portions. The crankarm/spindle portions are constructed in a tubular fashion, with the tubular element bent to accommodate the transition from the crank arm to the spindle. Additionally, the crankarm/spindle portions are preferably fabricated from composite materials, to offer a lightweight yet strong and stiff crankset.

Abstract: An improved solar panel for a spacecraft. The solar panel has a rigid base, at least one row of solar cells, and at least one elongated, collapsible, self-deploying reflector. Preferably, a plurality of rows and the reflectors are mounted on the face of the base and are generally parallel to each other in an alternating fashion. The deployed reflector forms a triangular shape having a first and second reflecting side that reflects radiation onto adjacent rows of solar cells. The collapsible reflector has a reflector sheet and an erector that deploys the sheet to form the triangular shape. The sheet is mounted to the base along its two lengthwise edges. The erector is mounted to the base beneath the sheet and adjacent to one of the sheet's lengthwise edges. The erector has a rigid erector arm that tilts upwardly to engage the underside of the sheet and to deploy the sheet into the triangular shape.