The need for light weight, low cost spacecraft primary structures has been demonstrated in a variety of existing and proposed programs. Historically, spacecraft designers have used composite materials in secondary structures as a substitute for aluminium to satisfy specific design requirements that could not be met by standard alloys. To expand this trend to primary load carrying structures, and to develop confidence in an all composite spacecraft bus, the Naval Center For Space Technology (NCST) at the Naval Research Laboratory (NRL), has designed and built a light weight, low cost composite spacecraft primary structure. The system was designed to meet all the structural requirements derived for the Clementine program flight vehicle structure. An additional program goal was to minimize the cost of the composite structure. Cost savings were realized through effective material selection, reduced part count, inexpensive manufacturing tooling, and simplified assembly fixturing. The final design is modular and scaleable, providing for the possibility of direct insertion into other programs.
Development of a low cost all composite satellite bus primary structure
Entwicklung einer kostengünstigen, nur aus Verbundwerkstoffen bestehenden Primärstruktur für einen wiederverwendbaren Trägersatelliten
1995
13 Seiten, 13 Bilder, 7 Tabellen, 5 Quellen
Conference paper
English
Development of a Low Cost All Composite Satellite Bus Primary Structure
British Library Conference Proceedings | 1995
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