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Alternative approach to aeroservoelastic design and clearance

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3 Author(s)
Taylor, R. ; Dept. of Aeronaut. & Automotive Eng. & Transport Studies, Loughborough Univ. of Technol., UK ; Pratt, R.W. ; Caldwell, B.D.

The in-flight interaction between an aircraft's flight control system (FCS), structural dynamics and unsteady aerodynamics has been of concern to aircraft designers for many years. Frequently, due to a limited understanding of the array of complex issues involved, a very conservative approach is essential to achieve a FCS which will obtain flight clearance. The paper examines the impact of the nonlinear nature of the servo-hydraulic actuation system on the aeroservoelastic interaction. A method of predicting the occurrence of a limit cycling condition in such a system is presented, with comparisons made to experimental results. In addition, the paper demonstrates how an application of actuator performance limits can be used to predict a maximum level of structural response. Finally, the possibility of reducing the current clearance requirements from a consideration of this maximum structural response is discussed

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Control Theory and Applications, IEE Proceedings -  (Volume:143 ,  Issue: 1 )