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The Design of Stability Augmentation Systems for Decoupling Aircraft Responses

Report Number: AFFDL TR 72-63
Author: Pope, Rhall E.
Corporate Author: Air Force Flight Dynamics Laboratory
Laboratory: Air Force Flight Dynamics Laboratory
Date of Publication: 1972-06
Pages: 152
Contract: Laboratory Research - No Contract
Project: 8219
Task: 821904
AD Number: AD0747017

Tactical aircraft with STOL capability exhibit undesirable coupled response during the landing phase of flight. A simplified method for designing a stability augmentation system which eliminates the coupling effects is demonstrated. The method is based on Gilbert's decoupling theory which utilizes a feedback control law to obtain a set of single input, single output subsystems. The augmentation system can be designed to provide either command rate or command angle authority in the three rotational axes. Analyses is facilitated through the use of two computer programs, the first of which determines the class of control laws which will decouple a system. The second computer program determines, through transient response analysis, the values of the transfer function parameters required to satisfy response criteria. The results of a piloted simulation which analyzed several decoupled configurations is also presented.

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