Abstract
A control system is designed for vibratory load reduction as well as for aeroelastic control of composite rotor blades using segmented piezoelectric (PZT) actuators. The finite-state induced inflow model is used to calculate the aerodynamic loads. A composite box beam theory is used to model the primary load carrying structure in the rotor blade. In this theory, a higher order displacement field is used to model the individual walls of the composite box beam with surface bonded piezoelectric actuators. Based on these techniques, an integrated rotor vibratory load analysis technique is developed by coupling an unsteady aerodynamic model with the rotor blade dynamic model. Dynamic deformations of the blade in all three directions, flap, lead-lag and torsion are analyzed. Blade dynamic responses are solved in the modal domain. The nonlinear aerodynamic model is linearized for linear control system design. A pole placement technique is used to design the control system for vibratory load reduction. Significant reductions are observed in the modal responses of rotor with the closed loop control.
| Original language | English (US) |
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| Title of host publication | Collection of Technical Papers - AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference |
| Publisher | AIAA |
| Pages | 2425-2433 |
| Number of pages | 9 |
| Volume | 4 |
| State | Published - 1999 |
| Event | Proceedings of the 1999 AIAA/ASME/ASCE/AHS/ASC Structrures, Structural Dynamics, and Materials Conference and Exhibit - St. Louis, MO, USA Duration: Apr 12 1999 → Apr 15 1999 |
Other
| Other | Proceedings of the 1999 AIAA/ASME/ASCE/AHS/ASC Structrures, Structural Dynamics, and Materials Conference and Exhibit |
|---|---|
| City | St. Louis, MO, USA |
| Period | 4/12/99 → 4/15/99 |
ASJC Scopus subject areas
- Architecture