A hybrid design method, focused on reducing vibration while minimizing control effort, is developed. In this integrated active-passive approach, trailing edge flap controller design is combined with blade structural optimization. An aeroelastic model is developed for a helicopter rotor with a trailing edge flap. The objective function, which includes vibratory hub loads and active flap control inputs, is minimized by an integrated optimal control/structural optimization process. It is demonstrated that both the hub vibratory loads and active flap control effort can be reduced. The study shows that retrofitting an active flap to a baseline blade or to an optimal passive blade configuration might not be an effective design approach. The active-passive hybrid method can outperform these configurations by achieving more vibration reduction with less control effort. The hybrid design procedure can reduce the required active flap deflections by about 30-60% in the whole flight range. An analysis and parametric study of the hybrid design of rotor blades with trailing edge flaps is conducted. The off-design condition for hybrid approaches is examined and the robustness of the hybrid design is addressed. The physical understandings of the hybrid design are explored.
All Science Journal Classification (ASJC) codes
- Materials Science(all)
- Aerospace Engineering
- Mechanics of Materials
- Mechanical Engineering