Design of flight control system for quad tilt-wing UAV

Authors :: Kenji Uchiyama
Takahito Mikami
Source :: 2015 International Conference on Unmanned Aircraft Systems (ICUAS).
Publication Year :: 2015
Publisher :: IEEE, 2015.
Abstract: Aircraft control system is designed to provide adequate stability during transition flight of a quad-tilt wing (QTW) UAV. The dynamic inversion method, which is a linearization method without an approximation algorithm, is applied to a control problem of the UAV, because of strong nonlinearity of its dynamical behavior. The validity of the proposed control system is verified through numerical simulation and experiment.

Subjects :: Nonlinear system
Engineering
Wing
Tilt (optics)
Computer simulation
Control theory
business.industry
Linearization
Control system
Stability (learning theory)
Approximation algorithm
ComputerApplications_COMPUTERSINOTHERSYSTEMS
business

Database :: OpenAIRE
Journal :: 2015 International Conference on Unmanned Aircraft Systems (ICUAS)
Accession number :: edsair.doi...........fe544e5196b3d68b6776d816df865304
Full Text :: https://doi.org/10.1109/icuas.2015.7152364