XXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXXX''"> Introduction
Panel Aerodynamics (App. A) has discussed the aerodynamic methods contained in FlightLoads while
Splines (App. B) has detailed how the aerodynamic and structural models are connected. This appendix completes the description of the computationally intensive portion of MSC.FlightLoads and Dynamics by documenting how these components are used in a static aeroelastic analysis.
As depicted in
Aeroelasticity, the static aeroelastic analysis consists of three methods:
• Flexible Increments
• Flexible Trim
• Rigid Trim
After setting up the governing matrix equations, this appendix provides a discussion of these three methods. In this discussion, the term "unit solutions" is used interchangeably with the "Flexible Increments" method.
A very useful by-product of the aeroelastic analysis is the production of stability derivative and hinge moment data. This information is created within MSC.Nastran and is printed within the output (.f06) file. Although the information is not available as part of FlightLoads postprocessing, its value motivates the documentation of it here. (The dimensional equivalents can be obtained from the Load Summation tool of the Loads Browser).