Start Date
4-1987 7:52 AM
Description
The majority of existing large solar arrays are designed against the requirements imposed by communcations satellites in geostationary orbits. For example, high launcher costs per kilogramme of satellite mass dictate an ecomomic preference for lightweight array designs, and with no method of satellite retrieval from GEO, array deployment can use simple 'one shot' devices. This is not true for low earth orbit missions.
However, the introduction of the Space Shuttle and the manned space station programme, including Columbus has caused a change of emphasis inarraydesign. Stowage volume rather than mass is now the cost criterion. Furthermore, to fully use the Shuttle attributes and the Space Station design philosophy the ability to retract the array and restow for return to earth has also become a design driver. These factors lead to a more complex, but inherently more flexible array than its geostationary counterpart.
Large Flexible Solar Arrays
The majority of existing large solar arrays are designed against the requirements imposed by communcations satellites in geostationary orbits. For example, high launcher costs per kilogramme of satellite mass dictate an ecomomic preference for lightweight array designs, and with no method of satellite retrieval from GEO, array deployment can use simple 'one shot' devices. This is not true for low earth orbit missions.
However, the introduction of the Space Shuttle and the manned space station programme, including Columbus has caused a change of emphasis inarraydesign. Stowage volume rather than mass is now the cost criterion. Furthermore, to fully use the Shuttle attributes and the Space Station design philosophy the ability to retract the array and restow for return to earth has also become a design driver. These factors lead to a more complex, but inherently more flexible array than its geostationary counterpart.
Comments
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