Flight control design to improve aircraft performance by reducing the flutter and dynamic loads margins

L.Benassi

DOI Number: N/A

Conference number: IFASD-2017-014

In order to ensure the maximum possible aircraft performance, the flight control laws of a modern combat aircraft were designed by minimising the flutter and dynamic loads safety margins. Based on a recent development programme, this paper shows the design principles that led to such improved aircraft performance and it identifies the changes in the design process which are necessary to ensure safety of flight from a Structural Dynamics and Aeroelasticity point of view. Fitness for purpose was demonstrated by flight test and analysis, whose results validated the method, which is now considered for all new store integration programmes.
This work would not have been possible without the fundamental technical contributions of several colleagues at Airbus Defence and Space, Leonardo and BAE Systems.

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Aeroelasticity, Dynamic Loads, flight control system., Structural coupling

In Categories: 1. IFASD 2017, 1.Events, Aeroservoelasticity

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