An optimization procedure is developed to address the problem of minimizing the drive system weight of high speed proprotor aircraft which are required to demonstrate fixed-wing-like efficiencies in high speed forward flight and maintain acceptable hover figure of merit similar to helicopters. The optimization is performed using the method of feasible directions. A hybrid approximate analysis procedure is also used to reduce the computational effort of using exact analysis for every function evaluation necessary within the optimizer. The results compared to a reference rotor show significant weight reductions. The aerodynamic performance of the optimized rotor, analyzed at “off-design” points to judge the, strength of the optimization, problem formulation and the validity of the resulting design, shows-considerable improvements. The results are compared to the reference values and significant reduction in the weight is achieved.
- drive system
ASJC Scopus subject areas
- Computer Science Applications
- Industrial and Manufacturing Engineering
- Management Science and Operations Research
- Applied Mathematics
- Control and Optimization