Matrix Load Analysis Method for Flexible Aircraft Structures

An integrated loads and stress analysts program has been written to shorten the time involved in analyzing the effect of flexibility on load distribution. The program was set up to efficiently interface with NASTRAN although any other similar structural analysis program could be used. The required matrices, coupling the aerodynamic and structural response to applied loads, are constructed automatically in the computer program.

Comparisons are presented between the program output and experimental data for an actual flight article verifying the method presented.