Abstract
Airbus is currently developing the Next Generation Solar Array (NGSA) for telecommunication satellites. It is based on a hybrid array concept which combines a conventional rigid panel array with lightweight, semi-rigid lateral panels. The main figures of merit power/mass and power/volume can be doubled through this concept. Mechanically, the semi-rigid panels are the key new element. Through acoustic testing as well as sine vibration testing in air and in vacuum it was verified that these panels are suitable as cell support in stowed configuration. With the help of finite element modelling it is demonstrated that the semi-rigid panels are compatible with a free deployment. Electrically, the new array is to be equipped with a new generation of 4 junction solar cells with efficiencies above 30%. The increased radiation dose due to electric orbit raising has to be taken into account to arrive at the optimum shielding while still minimizing the array mass. By adjusting the ratio of rigid to semi-rigid panels and through the choice of solar cell type and mass, the NGSA can be tailored in a wide range to needs of a given platform. This is illustrated for the solar array to be flown on the new Airbus platform Eurostar Neo.
Highlights
Airbus is currently developing the new telecommunication platform Eurostar Neo, which is optimized to an even higher degree than its predecessor Eurostar 3000 for the payload
There, a backbone, resembling a conventional rigid panel array is combined with lightweight, semi-rigid lateral panels
This increase in power/mass and power/volume by a factor of two is especially attractive due to the fact that it is achieved by a solar array design that relies in large parts on components with extensive space heritage
Summary
Airbus is currently developing the new telecommunication platform Eurostar Neo, which is optimized to an even higher degree than its predecessor Eurostar 3000 for the payload. Their aerial mass is 5 times lower compared to the rigid panel and combined with the use of lightweight cells, the power to mass ratio of the array is improved significantly. In terms of radiation dose, a classical 15 year GEO mission with purely chemical transfer orbit is assumed and the endof-life (EOL) summer solstice (SS) power figures are computed Both mass and stowage volume figures are “real” figures in the sense that they include yoke, yoke hinge as well as all hinges and hold-down and release units. Using a lightweight 4J cell with a 10% increased EOL efficiency of 29% at 1015 1 MeV e- /cm[2] results in an identical 10% increase in power/mass and power/volume again, as shown in column 5
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