Abstract
This report discusses the use of eigenspace techniques for the design of an active flutter suppression system for a hypothetical research drone. One leading edge and two trailing edge aerodynamic control surfaces and four sensors (accelerometers) are available for each wing. Full state control laws are designed by selecting feedback gains which place closed loop eigenvalues and shape closed-loop eigenvectors so as to stabilize wing flutter and reduce gust loads at the wing root while yielding acceptable robustness and satisfying constraints on rms control surface activity. These controllers are realized by state estimators designed using an eigenvalue placement/eigenvector shaping technique which results in recovery of the full state loop transfer characteristics.
| Original language | English (US) |
|---|---|
| Title of host publication | NASA Contractor Reports |
| State | Published - Jun 1 1987 |