Abstract:
The use of subscale models has been common practice in the industry and has helped
engineers gain more confidence in their design processes. However, each subscale model
is developed for a specifc test, and consequently, different types of models are needed for
observing aerodynamic, structural and aeroelastic characteristics of a full-scale aircraft.
Yet, traditional aircraft design methods face serious challenges when a novel aircraft de-
sign emerges and a proof-of-concept is needed for investigating this multi-disciplinary
problem. An example of such a problem is the development of aircraft configurations
with high aspect ratio wings for which the disciplines of aeroelastic and flight mechanics are strongly interconnected. Moreover, if the prediction of dynamic behaviour is of
interest, a method that utilises system identification for analysing experimental data is
of importance. Therefore, this thesis aims to develop a methodology to investigate the
complex flight dynamic behaviour of flexible aircraft by combining techniques for developing subscale models and methods with the field of system identification. This aim is
achieved through three objectives: 1) assessment of system identification methods for
subscale flexible aircraft, 2) theoretical development of subscale modelling in terms of
scaling laws and aeroelastic simulation framework and, 3) wind tunnel testing of the
subscale model. Aspects of System Identification have been explored through use-cases
where experimental data for a rigid aircraft both in full-scale and subscale configuration
is used. The results highlight the fact that in testing a subscale model, dynamics are more
prone to exhibit non-linear behaviour when compared to the full-scale model. It followed
by the application of system identification for a flexible aircraft based on a simulation
framework. This study emphasised the need for non-linear identification methods, such
as an output error method, to characterise a flexible aircraft system. The work continues
with the exploration of scaling laws applied to a simple aerofoil that is free to pitch and
plunge. These results build the foundation for the development of a subscale high aspect
ratio wing for wind tunnel experiments. The work highlights the trade-o s and compromises faced during the development of a dynamically subscaled model and the practice
of system identification. The main contribution lies in the development of a low-cost
methodology in building a subscale model that allows the use of dynamically scaled models at the early design stages. This practice provides the designer with a means to de-risk
novel aircraft concepts as early as possible and in doing so, reduce overall development
costs.