22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-4.10.R1
THE DESIGN OF AN AUTOMATIC FLIGHT CONTROL SYSTEM FOR A HYPERSONIC TRANSPORT AIRCRAFT
D. McLean (1), Z. Zaludin (2)
(1) University of Southampton, UK;
(2) Universiti Putra, Malaysia
Keywords: hypersonic transport aircraft, aircraft dynamics, stability, automatic flight control
system, mathematical model
The design of an automatic flight control system
for a hypersonic transport aircraft (HST) is
presented. It uses a mathematical model of the
longitudinal motion of an HST flying at Mach
8.0 and at a height of 85000 feet. Included in
the model were the non-linear dynamics
associated with the propulsion system. Since the
basic aircraft is dynamically unstable, closedloop
stabilization was required. Normally, the
required degree of closed-loop stability is
determined from published flying qualities
specifications which are unavailable, however,
for this type of aircraft. Consequently, a set of
dynamic parameters for the closed-loop
stabilization system was proposed which
corresponded with notionally acceptable flying
qualities. Using these parameters it was
possible to use an analytical procedure to
determine a corresponding state weighting
matrix to be used in a quadratic performance
index which, when minimized, provided a
feedback control law that ensured the controlled
HST had the specified flying qualities.
The effectiveness of the system is
demonstrated from results obtained by digital
simulation, including the propulsion system.
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