Optimization of the Wing Structure of a Future Supersonic Transport Aircraft

The paper deals with a structural optimization of the main wing structure of a 2^nd generation supersonic commercial transport using the optimization tool STARS to determine a first pre-design. The optimization revealed drastic design changes in stiffness and mass distribution relative to the initial design estimation. Large parts of the forward wing are determined by minimum thickness while the largest cover thickness moved from inboard to far outboard on the rear wing. In addition sensitivity investigation on material allowables are carried out and showed that an increase of 10% of the design allowables of the CFRP material results in a reduction of about 5% total wing weight. In addition, investigation on the elastic behavior indicate the need for further provisions.