We perform preliminary and certification loads analysis for part 23 aircraft. Based on lifting line theory, classical methods from NACA, Roskam and Torenbeek and approved methods from the part 23 regulations.
We develop the aircraft mass properties to provide appropriate aircraft distributed masses suitable for use in the loads analysis.
Our loads generation process includes landing loads generation, a check on the design speeds, V-n diagram generation, powerplant loads derivation and control surface loads generation per the part 23 appendix method
We consider the complete aircraft in a quasi steady state with the external aerodynamic and ground loads reacted by the distributed mass properties of the aircraft for a range of mass configurations.
The loads generation process includes a full report including the referenced methods and derivations for all the key parameters for the loads analysis.
We also generate nodal loads with loads and moments at key nodes resolved around the selected elastic axes for the flying surfaces and the fuselage. These can be produced for the whole aircraft for balanced load cases or for individual major subassemblies as required. We export this as a .dbf file you can easily add to your finite element model and connect with RBE3 elements to your existing mesh.