Fault tolerant robust flight control using surface actuator hinge moments Conference Paper

abstract

• A robust, flight control law is investigated to provide fault tolerance for air vehicles experiencing inertial state measurement sensor degredation. The method is particularly useful on low cost, precision weapons pursuing dynamic targets. Observation techniques are facilitated by representing the surface actuator aerodynamic induced hinge moment by a function that is Lipschitz within the actuator sweep angle. A stable output feedback flight control law, requiring only acutator angular position and current measurements, is designed to handle the hinge moment effects and track a predetermined angle-of-attack reference trajectory. Benefits include improved effectiveness, improved reliability without additional hardware, and a cost and weight savings. Simulations are conducted on a tactical missile interceptor to evaluate the controller at various operating conditions in the flight envelope. 2008 AACC.

name of conference

• 2008 American Control Conference

authors

• Pagilla, Prabhakar

published proceedings

• 2008 AMERICAN CONTROL CONFERENCE, VOLS 1-12

author list (cited authors)

• Ratliff, R. T., & Pagilla, P. R.

citation count

• 1

complete list of authors

• Ratliff, Ryan T||Pagilla, Prabhakar R

publication date

• June 2008

publisher

• Institute of Electrical and Electronics Engineers (IEEE)  Publisher

published in

• Proceedings of the ... American Control Conference. American Control Conference  Journal

keywords

• 40 Engineering
• 4001 Aerospace Engineering
• 4007 Control Engineering, Mechatronics And Robotics

Digital Object Identifier (DOI)

• 10.1109/ACC.2008.4586722

International Standard Book Number (ISBN) 13

• 978-1-4244-2078-0

start page

• 1612

end page

• +

URL

• http://dx.doi.org/10.1109/acc.2008.4586722