A new direct matrix abstract program for NASTRAN written to calculate internal stresses and airloads for a flexible wing is described. The difficulties encountered in interfacing the doublet lattice solution to the aerodynamic problem to the finite element solution to the structural problem are discussed. A brief numerical example is included.
A new capability for elastic aircraft airloads via NASTRAN
1982-11-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
Flight Testing the UH-60A Airloads Aircraft
British Library Conference Proceedings | 1994
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