This assumes that Cp, P, a are constant over temperature and that the entire energy supplied by the laser heats up only a small surficial layer. As seen in Appendix I, equation (5) can be rewritten as: 3.2 Solar Panels These are made from the bonding of solar cells on to suitable substrates of aluminium or CFRP honeycomb. Individual cells are connected in series and in parallel to provide required power output under the varying solar illumination conditions characteristic of the orbit of the mission. These panels are large, protrude outside the spacecraft and will definitely be exposed to directed radiation from a laser stationed in space. While alternative power sources exist, solar panels continue to be the most cost- effective technology for use in civilian missions. The heart of the panel is a solar cell. A typical silicon cell used for space applications is shown in Fig. 1. The cell consists of a N by P type of device with a n layer on top which is about 0.15 um thick. The total cell thickness is about 250 um. A cover glass made of cerium doped glass with an anti-reflection coarting on the lower side is bonded onto the cell. The cover glass serves to protect the cell from radiation damage. The anti-reflection
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