An optimization procedure is developed to address the problem of aeroelastic stability of high speed prop-rotor aircraft. A composite box beam is used as a perturbational stiffness model and the objective function to be minimized is the perturbational weight. An optimization algorithm, which used the method of feasible directions, is coupled with a hybrid approximate analysis to reduce the computational expense of exact analyses for every function evaluation. The results, compared to a reference rotor which is unstable in both hover and high speed cruise, show significant improvements in the aeroelastic stability without large weight penalties.
ASJC Scopus subject areas
- Modeling and Simulation
- Computer Science Applications