Input-Output Invertibility and Sliding Mode Control for Close Formation Flying of Multiple UAVs

Citation data:

International Journal of Robust and Nonlinear Control, Vol: 10, Page: 779-797

Publication Year:
2000
Usage 14
Abstract Views 14
Repository URL:
https://digitalscholarship.unlv.edu/ece_fac_articles/206; https://digitalscholarship.unlv.edu/ece_fac_articles/598; http://ezproxy.library.unlv.edu/login?url=http://dx.doi.org/10.1002/1099-1239(200008)10:10<779::AID-RNC513>3.0.CO;2-6
Author(s):
Singh, Sahjendra N.; Pachter, Meir; Chandler, Phil; Banda, Siva; Rasmussen, Steve; Schumacher, Corey
Tags:
Control of UAVs; Drone aircraft; Feedback control systems; Feedback linearization; Formation control; Inverse control; Nonlinear systems; Variable structure control; Vehicles; Remotely piloted; Control of UAVs; Feedback linearization; Formation control; Inverse control; Nonlinear system; Variable structure control; Aerospace Engineering; Controls and Control Theory; Electrical and Computer Engineering; Multi-Vehicle Systems and Air Traffic Control; Navigation, Guidance, Control and Dynamics; Signal Processing; Space Vehicles; Systems and Communications; Systems Engineering and Multidisciplinary Design Optimization
article description
This paper treats the question of invertibility of input–output maps and the design of a robust control system for formation flying of multiple unmanned aerial vehicles (UAVs). In close formation, the wing UAV motion is affected by the vortex of the adjacent lead aircraft. The forces produced by these vortices are complex functions of relative position coordinates of the UAVs. In this paper, these forces are treated as unknown functions. For trajectory tracking, invertibility of certain input–output maps in the wind axes system are examined. Interestingly, in the wind axes system, the system is not invertible, but in a simplified co-ordinate system obtained from the wind axes system for which the velocity roll is zero, inverse control of separation co-ordinates is possible. Variable structure control laws are derived for separation trajectory control of wing aircraft in the simplified wind co-ordinate system and for the flight control of the lead aircraft. Simulation results for two UAVs are presented which show precise separation trajectory control in spite of the presence of unknown vortex forces, while the lead aircraft maneuvers. Furthermore, these results confirm that when the wing aircraft is positioned properly in the vortex of the lead aircraft, there is a reduction in the required flight power. Published in 2000 by John Wiley & Sons, Ltd.