Use of the pseudo-inverse for design of a reconfigurable flight control system

Abstract

Abstract : Reconfiguration of the flight control system is achieved using generic inputs and transformation matrices for single primary control surface failure. Pseudo-inverse is used to evaluate appropriate transformation matrices. Design is tested against non-linear six degree-of-freedom model of the A-7D by simulating failure flights. System was found to provide desirable flying qualities upon reconfiguration. (Author)