Francesco Saltari, Franco Mastroddi, Cristina Riso, Guido De Matteis, Sara Colaianni

DOI Number: N/A

Conference number: IFASD-2017-175

This paper focuses on the application of a flexible-aircraft model for the synthesis of a robust full-state control law to suppress the body-freedom flutter instability of a flyingwing vehicle. This phenomenon is typically observed in tailless configurations as a result of the coupling between a relatively high-frequency short-period mode and a low-frequency first aeroelastic mode. Therefore, it can be captured and controlled only using a unique formulation of flight dynamics and aeroelasticity. Fully coupled equations of rigid-body motion and structural dynamics are obtained by assuming a body reference frame that verifies the practical mean-axis constraints. The equations are linearized around steady maneuvers and recast in a state-space form that simultaneously includes rigid-body, elastic, and aerodynamic state variables. The state-space model is completed with controls associated to aerodynamic surfaces and implemented for complex configurations described in terms of a finite element method structural model and a doublet lattice method aerodynamic model. Openand closed-loop results for the stability and response of a reference flying-wing vehicle are presented and discussed to demonstrate the suitability of the integrated model to the control of flexible aircraft.

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In Categories: 1.Events, Highly Flexible Aircraft Structures, IFASD 2017
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