ADM Aeolus is an Earth Explorer Core Mission of the European Space Agency (ESA). The satellite is provided with a deployable solar array fully equipped with European state of the art Triple Junction (TJ) GaAs solar cells. The structural part and mechanisms of the ADM Aeolus Solar Array (SA) is a derivate of the Dutch Space FRED solar array concept. This FRED type solar array has already been used on Jules Verne (Automated Transfer Vehicle) and Giove-A. Both satellites has been successfully launched and the Solar Arrays are working nominally.. The ADM Aeolus spacecraft (S/C) is powered by two deployable wings. Each of them composed by three panels and with a panel size of 1.1 times 2.2 m2, so that the total area is about 14.5 m2. European TJ solar cells (27 % efficiency class) embodying an integral protection diode were selected to meet the power budget, necessary for the installed payload. The principal one is an Atmospheric LAser Doppler INstrument (ALADIN), a novel system whose development is a strategic goal for ESA. This SA program is a challenging development in terms of solar cell qualification because of the extensive characterisation and qualification campaign performed for the cell and the integral diode components. Especially for protection diode a long duration high temperature test was performed in order to simulate and cover all lifetime stresses. Main drivers for PVA design are the power requirement at the end of life and the requested protection against atomic oxygen erosion. This paper describes : WHITE SQUARE. The results achieved during the qualification phase, from bare cell level to the coupon level, WHITE SQUARE. The design activity, mainly focused on the prediction of EOL performances, WHITE SQUARE. The acceptance phase at panel levels, which has verified the suitability of the design assumption and manufacturing workmanship.
The ADM Aeolus solar array
2008
6 Seiten, 2 Quellen
Conference paper
Storage medium
English
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