istics of encapsulated and composite LTES systems under heat cycle conditions corresponding to an actual orbit. Figure 11 shows a diagram of such a system loop. In the tests, radiation input energy is provided by electric heaters which are separated into several parts to simulate the calculated axial distribution of solar flux inside the receiver cavity. The energy flux transferred from the heater to the LTES components is about 8 kW of which circulated heat transfer fluid removes 5 kW thermal energy continuously. Designed inlet and outlet temperatures are about 800 K and 1100 K respectively. The temperature distribution is measured by thermocouples
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