Application of optimal control to structural load alleviation control systems
Feedback laws based upon optimal control theory were derived. and these resulted in a reduction of the structural loads on the wing of a simulated aircraft. Various models of the aircraft dynamics were used. the most complete being of order 79. This model included rigid body motion, structural flexi...
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| Format: | Default Thesis |
| Published: |
1980
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| Online Access: | https://hdl.handle.net/2134/17213 |
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