This paper presents an approach for determination of trimmed flight states of an over-actuated tilt-wing aircraft for linear controller synthesis. Tilt-wing aircraft combine efficient forward flight with vertical takeoff and landing capabilities and thus offer many advantages for unmanned aerial vehicle applications. The ability to cover a wide range of airspeeds comes along with significant changes in aerodynamics and consequently flight mechanics, which makes flight state control a challenging task. Proven gain-scheduling concepts for flight state control rely on pre-determined trimmed flight states. A new tilt-wing aircraft design for even more efficiency in forward flight features a tiltable wing and a tiltable tailplane. This results in over-actuation of the longitudinal motion and hence the determination of control device commands for trimmed flight becomes a multi-dimensional problem. This paper presents an approach to provide a distinct set of control device commands for each trimmed flight state, w.r.t. the specific tilt-wing configuration and user-defined constraints. The trimmed flight states and the corresponding control device commands are the basis for linear controller synthesis, which is applied for the entire flight envelope. The proposed approach has been successfully implemented for an unmanned tilt-wing demonstrator and evaluated in flight tests.
Trimmed Flight States of an Over-Actuated Tilt-Wing Aircraft for Linear Controller Synthesis
2023-08-16
2697001 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Wing Divergence of Trimmed Aircraft
NTIS | 1987
|Wing Divergence of Trimmed Aircraft
NTIS | 1986
|Flight testing experiments with tilt-wing aircraft
Engineering Index Backfile | 1959
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