Optimization of a Generic Aircraft Control Surface (Patria)

This benchmark is originally developed by Patria Aerostructures. 

Requirements: TBD

Computational domain:
Control Surface Dimensions (figure 1):
Rectangular plan form with 3000mm x 1000mm dimensions
Triangular cross section with 1000mm chord and 200mm height

Cross Section (figure 2):
Uniform cross section along the span
The maximum number of the internal spars is limited to 10 spc
Spar locations and tilting to be freely chosen
Skin and spar thicknesses to be freely chosen
Fittings not included in the optimization, supports can be assumed ideally rigid
The control surface structure is closed with inner and outer end ribs

Fittings (figure 3):

Loads:
The aerodynamic loading is assumed to follow triangular shape on both the upper and lower surfaces as shown in figure 4.

The stacking sequence to be freely chosen
Allowed fiber orientations are shown in the figure 5

Boundary and/or initial conditions for computations: TBD
Material Parameters: Solid
Optimization: Objective is to minimize the mass.

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Defined by Petri Hepola, 2006.