At high angles-of-attack (AOA) flow separations can produce non-linear and time varying aerodynamic loads, which cannot be predicted with great certainty. Such loads make control system development extremely difficult. A control system has thus been developed which can accomplish on-line reduction of the a-priori uncertainties pertaining to the effective control of the aircraft. The self-organising control system was developed to suppress unacceptable pitch-up tendencies of an aircraft at high AOA, without the use of AOA measurement. The final control system demonstrated good performance for a variety of inputs although performance was not as good in turbulence.
Self-Organizing Control System for Non-Linear Aircraft Dynamics
1985
12 pages
Report
Keine Angabe
Englisch
Aerodynamics , Avionics , Self organizing systems , Aerodynamic loading , Flight control systems , Flow separation , Nonlinear systems , Flight maneuvers , Angle of attack , High angles , Algorithms , Adaptive control systems , On line systems , Turbulence , Digital simulation , Great britain , Foreign technology , NATO furnished , Component reports
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