Composite curved frames for helicopter fuselage structureThis paper presents the results of analysis and testing of composite curved frames. A major frame was selected from the UH-60 Black Hawk helicopter and designed as a composite structure. The curved beam effects were expected to increase flange axial stresses and induce transverse bending. A NASTRAN finite element analysis was conducted and the results were used in the design of composite curved frame specimens. Three specimens were fabricated and five static tests were conducted. The NASTRAN analysis and test results are compared for axial, transverse, and Web strains. Results show the curved beam effects are closely predicted by a NASTRAN analysis and the effects increase with loading on the composite frames.
Document ID
19850039245
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rich, M. J. (Sikorsky Aircraft Stratford, CT, United States)
Lowry, D. W. (United Technologies Corp. Sikorsky Aircraft Div., Stratford, CT, United States)