A study on the aeroelastic response and control of three-degree-of-freedom flapped-wing systems operating in an incompressible, subcritical flight speed and exposed to sonic boom loads, is presented. Kalman filter (KF) and sliding-mode observer (SMO) were both implemented to prevent system instability and reduction in performance due to spillover effects. The linear-quadratic- Gaussian (LQG) control strategy using SMO was used, and the feedback control was implemented via the estimated states. The feedback control system makes use of one measurement, which enables computation with less effort, and simulates the worse problem due to sensor failure.
ASJC Scopus subject areas
- Control and Systems Engineering
- Aerospace Engineering
- Space and Planetary Science
- Electrical and Electronic Engineering
- Applied Mathematics