TY - GEN
T1 - Control allocation with actuator dynamics for aircraft flight controls
AU - Ahmad, Hammad
AU - Young, Trevor M.
AU - Toal, Daniel
AU - Omerdic, Edin
PY - 2007
Y1 - 2007
N2 - This paper addresses the control allocation to several aircraft flight controls to produce required body axis angular accelerations. Control law is designed to produce the virtual control effort signals, which are then distributed by solving a sequential least squares problem using active set method to the flight control surfaces to generate this effort. Two cases are described: in the first case the control law and allocation for the healthy aircraft is implemented, and in the second case, jamming of one control surface is introduced at time zero. In this case, it was shown how the controller and allocation compensate for this failure without changing the control law. To implement this system it was assumed that there is a good fault identification system onboard. Normally aircraft are over-actuated and in the case of a control failure this over actuation is more pronounced due to coupling of aircraft dynamics. Instead of using one-to-one mapping between control allocator and control surfaces, actuator dynamics was included in the system. The discrepancy in the optimal signal from control allocation due to this additional dynamics was compensated using the scheme mentioned in this paper. Each gain corresponding to the actuator is tuned using genetic algorithms (GA). The controller and allocation design are implemented on a nonlinear B747 model with actuator dynamics.
AB - This paper addresses the control allocation to several aircraft flight controls to produce required body axis angular accelerations. Control law is designed to produce the virtual control effort signals, which are then distributed by solving a sequential least squares problem using active set method to the flight control surfaces to generate this effort. Two cases are described: in the first case the control law and allocation for the healthy aircraft is implemented, and in the second case, jamming of one control surface is introduced at time zero. In this case, it was shown how the controller and allocation compensate for this failure without changing the control law. To implement this system it was assumed that there is a good fault identification system onboard. Normally aircraft are over-actuated and in the case of a control failure this over actuation is more pronounced due to coupling of aircraft dynamics. Instead of using one-to-one mapping between control allocator and control surfaces, actuator dynamics was included in the system. The discrepancy in the optimal signal from control allocation due to this additional dynamics was compensated using the scheme mentioned in this paper. Each gain corresponding to the actuator is tuned using genetic algorithms (GA). The controller and allocation design are implemented on a nonlinear B747 model with actuator dynamics.
UR - http://www.scopus.com/inward/record.url?scp=84885082460&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/record.url?scp=37249063803&partnerID=8YFLogxK
U2 - 10.2514/6.2007-7828
DO - 10.2514/6.2007-7828
M3 - Conference contribution
AN - SCOPUS:84885082460
SN - 1563479087
SN - 9781563479083
T3 - Collection of Technical Papers - 7th AIAA Aviation Technology, Integration, and Operations Conference
SP - 1415
EP - 1428
BT - Collection of Technical Papers - 7th AIAA Aviation Technology, Integration, and Operations Conference
PB - American Institute of Aeronautics and Astronautics Inc.
T2 - 7th Aviation Technology, Integration, and Operations Conf., ATIO, 2nd Centre of Excellence for Integrated Aircraft Technology (CEIAT) Int. Conf. on Innovation and Integration in Aerospace Sciences and the 17th Lighter-Than-Air Systems Technol. Conf.
Y2 - 18 September 2007 through 20 September 2007
ER -