The increasing use of highly augmented digital flight-control systems in modern military helicopters prompted an examination of the influence of rotor dynamics and other high-order dynamics on control-system performance. A study was conducted at NASA Ames Research Center to correlate theoretical predictions of feedback gain limits in the roll axis with experimental test data obtained from a variable-stability research helicopter. Feedback gains, the break frequency of the presampling sensor filter, and the computational frame time of the flight computer were systematically varied. The results, which showed excellent theoretical and experimental correlation, indicate that the rotor-dynamics, sensor-filter, and digital-data processing delays can severely limit the usable values of the roll-rate and roll-attitude feedback gains.
Analytical and flight investigation of the influence of rotor and other high-order dynamics on helicopter flight-control system bandwidth
Ann. Forum of the Intern. Conf. on Basic Rotorcraft Res. ; 1985 ; Research Triangle Park, N. C., United States
1985-02-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
British Library Conference Proceedings | 1997
|British Library Conference Proceedings | 1997
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