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A Theory for Longitudinal Short-Period Pilot Induced Oscillations.

ADA056982

Publication Date	1977
Personal Author	Smith, R. H.
Page Count	146
Abstract	This report presents a theory for longitudinal, short-period, pilot-induced oscillations (PIO). The theory explains how the airplane's pitch attitude and normal acceleration modes can couple with pilot dynamics to produce large-amplitude, uncontrollable oscillations. The effects of control system dynamics and feel system nonlinearities are encompassed by this theory. It is concluded that an airplane's potential for PIO can be determined based entirely on linear systems analysis; the prediction of fully-developed PIO frequency and amplitude requires that all significant nonlinearities be considered. The theory postulates that PIO can develop either as a result of closed loop control of pitch attitude or from abrupt control or atmospheric inputs of size sufficient to excite a lightly damped, dominant, stick-free airplane mode. A number of PIO case histories are examined; it is shown that these confirm the proposed theory. The implications of the theory to flight test and to simulation are discussed. A generalized definition for PIO is given which permits distinctions to be made between pilot-vehicle system oscillations due only to attitude control and those due to attitude plus path control modes. It is suggested that the theory can be easily extended to the study of lateral-directional PIO. A bibliography of PIO source material is included with this report. (Author)
Keywords	Flight control systems Flight simulation Closed loop systems Oscillation Theory Models Dynamics Manual operation Pilots Behavior Mathematical analysis Attitude(Inclination) Pitch(Inclination) Acceleration Flight testing Bibliographies PIO(Pilot Induced Oscillation) Pilot dynamics Pilot induced oscillation Pilot models
Source Agency	Non Paid ADAS
NTIS Subject Category	51B - Aeronautics 92B - Psychology
Corporate Authors	Systems Research Labs Inc Dayton Ohio
Document Type	Technical Report
Title Note	Interim rept. Nov 75-Apr 77.
NTIS Issue Number	197822
Contract Number	F33615-77-C-3011

A Theory for Longitudinal Short-Period Pilot Induced Oscillations.

A Theory for Longitudinal Short-Period Pilot Induced Oscillations.
ADA056982

Publication Date	1977
Personal Author	Smith, R. H.
Page Count	146
Abstract	This report presents a theory for longitudinal, short-period, pilot-induced oscillations (PIO). The theory explains how the airplane's pitch attitude and normal acceleration modes can couple with pilot dynamics to produce large-amplitude, uncontrollable oscillations. The effects of control system dynamics and feel system nonlinearities are encompassed by this theory. It is concluded that an airplane's potential for PIO can be determined based entirely on linear systems analysis; the prediction of fully-developed PIO frequency and amplitude requires that all significant nonlinearities be considered. The theory postulates that PIO can develop either as a result of closed loop control of pitch attitude or from abrupt control or atmospheric inputs of size sufficient to excite a lightly damped, dominant, stick-free airplane mode. A number of PIO case histories are examined; it is shown that these confirm the proposed theory. The implications of the theory to flight test and to simulation are discussed. A generalized definition for PIO is given which permits distinctions to be made between pilot-vehicle system oscillations due only to attitude control and those due to attitude plus path control modes. It is suggested that the theory can be easily extended to the study of lateral-directional PIO. A bibliography of PIO source material is included with this report. (Author)
Keywords	Flight control systems Flight simulation Closed loop systems Oscillation Theory Models Dynamics Manual operation Pilots Behavior Mathematical analysis Attitude(Inclination) Pitch(Inclination) Acceleration Flight testing Bibliographies PIO(Pilot Induced Oscillation) Pilot dynamics Pilot induced oscillation Pilot models
Source Agency	Non Paid ADAS
NTIS Subject Category	51B - Aeronautics 92B - Psychology
Corporate Authors	Systems Research Labs Inc Dayton Ohio
Document Type	Technical Report
Title Note	Interim rept. Nov 75-Apr 77.
NTIS Issue Number	197822
Contract Number	F33615-77-C-3011