Control Surface Modelling for Fast Simulation of Large Flexible Aircraft

摘要

Environmental and performance target for aviation has led to wing structures that exploit the benefits of light-weight material and higher aspect ratios. These structures can no longer be assumed to be rigid and aeroelastic effects are becoming a more important feature in the design process. In this paper, the CA~2LM framework is presented as a tool able to assess a wide range of flexible aircraft dynamics, from loads to handling qualities. A wide range of control surface models have been implemented in order to assess aircraft dynamics at different flight conditions. Ailerons and spoilers have been used for gust load alleviation while folding wing tips are presented over manoeuvring conditions. Results presented show the effectiveness of spoilers and ailerons, which are able to reduce the first peak of both wing-root bending and torsion moments by 10%. Reduction is significant also for the vertical load factor. Folding wingtip deflection results show the capabilities of such novel control effectors to actively control the bank attitude of the aircraft.