Calculation of Airloads for a Flexible Wing via NASTRAN.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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This thesis describes the use of the NASTRAN program Level 17.0 in the calculation of flexible wing airloads and stresses. The problems of interfacing aerodynamic and structural models are discussed with assumptions needed to solve them. Two different methods of transferring the aerodynamic forces into a structural load vector are presented. A Direct Matrix Abstraction Program was developed for use in these calculations. This sequence is limited to the use of one doublet-lattice panel for the aerodynamic model and requires several new data blocks for execution. Although these data blocks were input with the bulk data deck to test the sequence, a new preliminary module has been constructed to build them internally. The results of this investigation show that NASTRAN can be used in calculating the airloads and stresses for a flexible wing. This new sequence has extended the capability of NASTRAN to allow for the application of internally generated steady airloads to the structural model. Author
- Numerical Mathematics
- Computer Programming and Software
- Fluid Mechanics