The NASA/Army research plan for developing the logic elements for helicopter rotor design optimization by integrating appropriate disciplines and accounting for important interactions among the disciplines is discussed. The optimization formulation is described in terms of the objective function, design variables, and constraints. The analysis aspects are discussed, and an initial effort at defining the interdisciplinary coupling is summarized. Results are presented on the achievements made in the rotor dynamic optimization for vibration reduction, rotor structural optimization for minimum weight, and integrated aerodynamic load/dynamics optimization for minimum vibration and weight.
Integrated multidisciplinary design optimization of rotorcraft
AIAA/AHS/ASEE 1989 Aircraft Design and Operations Meeting ; 1989 ; Seattle, WA, United States
1989-07-01
Conference paper
No indication
English