Active control of an aeroelastic structure /
A Kalman estimator, coupled with a full-state feedback
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| Format: | Thesis eBook |
| Language: | English |
| Published: |
[Place of publication not identified] :
[publisher not identified] ;
1996.
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| Subjects: | |
| Online Access: | Link to OAKTrust copy |
| Summary: | A Kalman estimator, coupled with a full-state feedback above the open loop flutter velocity. active control system. An excellent correlation between aerodynamic theory provides a base for full-state feedback combined with a personal-computer based active control control law, is developed to stabilize the system above the control. Incorporation of unsteady aerodynamic theory, developed with linear theory. Each theoretical model is hardening are included to examine nonlinear control behavior. Kalman estimator and full-state feedback, the linear and Linear and nonlinear aeroelastic response is modeled with an modeled with an approximation to Theodorsen's classical nonlinear systems are stabilized at velocities which are 100% open loop flutter velocity. Coulomb damping and pitch pitch motion of a wing. The addition of a control surface, simulated using Matlab[] and the experimental model of the system, extends the stable flight region. Linear, steady The nonlinear model is tested using the control laws theory and experiment is achieved for the models. Using a unique test apparatus that allows for prescribed plunge and unsteady theory, makes the model more realistic and complex. |
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| Item Description: | "Major subject: Aerospace Engineering". Vita. |
| Physical Description: | xi, 103 leaves : illustrations ; 28 cm. Also available online. Issued also on microfiche from Lange Micrographics. |
| Bibliography: | Includes bibliographical references. |