An advanced control system for a next generation transport aircraftThe use of modern control theory to develop a high-authority stability and control system for the next generation transport aircraft is described with examples taken from work performed on an advanced pitch active control system (PACS). The PACS was configured to have short-period and phugoid modes frequency and damping characteristics within the shaded S-plane areas, column force gradients with set bounds and with constant slope, and a blended normal-acceleration/pitch rate time history response to a step command. Details of the control law, feedback loop, and modal control syntheses are explored, as are compensation for the feedback gain, the deletion of the velocity signal, and the feed-forward compensation. Scheduling of the primary and secondary gains are discussed, together with control law mechanization, flying qualities analyses, and application on the L-1011 aircraft.
Document ID
19830060461
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rising, J. J. (Lockheed-California Co. Burbank, CA, United States)
Davis, W. J (Lockheed-California Co. Burbank, CA, United States)
Grantham, W. D. (NASA Langley Research Center Hampton, VA, United States)