Joaquim
R.R.A. Martins

MDO Lab, UTIAS

http://mdolab.utias.utoronto.ca

**High-Fidelity
Aero-Structural Design Optimization of Aircraft Configurations**

An integrated aero-structural design method for aerospace
vehicles is presented.
The approach combines an aero-structural solver, a coupled aero-structural adjoint solver, a geometry engine, and a gradient-based
optimization algorithm. The aero-structural solver ensures accurate solutions
by using high-fidelity models for the aerodynamics, structures, and coupling
procedure.

The coupled aero-structural adjoint solver is used to
calculate the sensitivities of aerodynamic and structural cost functions with
respect to both aerodynamic shape and structural variables. These sensitivities
are compared with those given by the complex-step derivative approximation and
finite differences. The proposed method is shown to be both accurate and
efficient, exhibiting a significant cost advantage when the gradient of a small
number of functions with respect to a large number of design variables is
required.

The optimization of a supersonic business jet configuration demonstrates the
usefulness of computing aero-structural sensitivities using the coupled-adjoint method.