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Matrix Load Analysis Method for Flexible Aircraft Structures
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English
Abstract
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.
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Authors
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Citation
Martin, G., "Matrix Load Analysis Method for Flexible Aircraft Structures," SAE Technical Paper 810610, 1981, https://doi.org/10.4271/810610.Also In
References
- Johnson W. S. “An Aeroelastic Procedure for Flap-Type Control Surfaces.” Journal of Aerospace Sciences 28 985 987 1961
- Raymond Bisplinghoff L. Holt Ashley Halfman Robert L. “Aeroelasticity” Addison-Wesley Publishing Co
- Irving Abel, NASA TND-5538 “Evaluation of a Technique for Determining Airplane Aileron Effectiveness and Roll Rate by Using an Aeroelastically Scaled Model.” Nov 1969 Langley Research Center - Langley Station Hampton, Va