A study has been conducted to analytically and experimentally determine the structural and thermal performance benefits of composite isogrid structures for a range of spacecraft applications. The analytical results indicated that an isogrid panel can be constructed to meet both the bending stiffness and mass requirements for a range of spacecraft applications, but with a slightly greater panel height compared to the conventional designs. Thermal analysis indicated that the isogrid concept offers the prospect of lower operating temperatures relative to that experienced with honeycomb panels. A comparative cost analysis has also been conducted between the isogrid and honeycomb sandwich constructions.
Composite isogrid structures for spacecraft components
1998
10 Seiten
Aufsatz (Konferenz)
Englisch
AIAA | 1975
|Filament winding of composite isogrid structures
British Library Online Contents | 2014
Continuous-Filament Isogrid Composite Panel
NTRS | 1985
|