This paper develops and applies Quantitative Feedback Theory (QFT) in the discrete domain by employing the w' bilinear transformation. The application is to the AFTI/F-16 aircraft (a/c) with 3 outputs: pitch rate (q), roll rate (p), and yaw rate (r) and driven with 6 inputs: 2 flaperons, 2 horizontal tails, vertical canard pair, and rudder. The sampling frequency of the system is given apriori as 377 rps (80 Hz). An effective 3x3 plant is developed by means of a 6x3 surface weighting matrix which is chosen to achieve a minimum-phase (m.p.) 3x3 continuous plant. Quantitative performance tolerances are assigned to the nine system transfer functions, to be achieved over three subsonic and one supersonic flight conditions and as many surface failures as possible, without any failure identification. Sampling renders the system effectively non-minimum phase (n.m.p.) with inherent limitations on the achievable feedback benefits.
QFT digital flight control design as applied to the AFTI/F-16
Entwicklung einer digitalen Flugregelung unter Beruecksichtigung der quantitativen Rueckkopplungs-Theorie (QFT) - Anwendung bei der AFTI/F-16
1987
8 Seiten, 6 Bilder, 20 Quellen
Aufsatz (Konferenz)
Englisch
AFTI/F-16 digital flight control system experience
NTRS | 1984
|Design Implications from Afti/F-16 Flight Test
NTIS | 1984
|AFTI/F-111 performance flight test summary
Tema Archiv | 1987
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