The feasibility of using carbon fiber reinforced plastics (CRP) for primary wing structures of aircraft was investigated. Strength and stiffness of CRP were determined with regard to application in wing spars and torsion boxes. Production methods for glass fiber reinforced plastic composites were extended to CRP structures and the experience gained was applied to the fabrication of the inner CRP wing part of the SB-10 glider. The investigations have shown that strength and fabrication problems of primary glider structures, using (CRP) composites, can be overcome.
Applicability of Carbon Fibers in Heavily Stressed Aircraft Components Untersuchungen ueber die Anwendung von Kohlenstoff-Fasern in Hochbeanspruchten Flugzeugbauteilen
1973
109 pages
Report
No indication
English
Logistikgerechte Überholung von Flugzeugbauteilen
TIBKAT | 1993
|Logistikgerechte Überholung von Flugzeugbauteilen
Tema Archive | 1993
|