Development of Control Contraction Metric based methods on non-conventional aircraft configuration

Abstract

Control Contraction Metrics (CCMs) can be described as a non-linear control technique based in
differential dynamics on the framework of differential geometry. This work presents preliminary
results on applying CCMs to the control of a Blended Wing Body (BWB) aircraft configuration,
in particular, regarding flight conditions involving high angle of attack and medium Reynolds
number regimes. These preliminary results show that in absence of conventional stability
equilibrium points, proper CCMs may allow effective control on aircraft dynamics given the
adequate operational conditions. These conditions and configuration are expected to be present
in new concepts of Remotely Piloted Aircraft Systems (RPAS), extending their applications
from planetary exploration to support the development of new transportation concepts in
commercial airliners. Methods described, data, and results, are expected to be of application
for EXperimental Aircraft for European Leadership in Aviation (EXAELIA) project, a Horizon
Europe international effort to de-risk and develop new concepts of passsenger aircraft to face
aerospace industry challenges by 2050.
This work has been funded by the European Union under GA No. 101191922. Views
and opinions expressed are however those of the author only and do not necessarily reflect those
of the European Union or the European Climate, Infrastructure and Environment Executive
Agency. Neither the European Union nor the granting authority can be held responsible for
them.