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rotorcraft system identification techniques for handling qualities and stability and control evaluationAn integrated approach to rotorcraft system identification is described. This approach consists of sequential application of (1) data filtering to estimate states of the system and sensor errors, (2) model structure estimation to isolate significant model effects, and (3) parameter identification to quantify the coefficient of the model. An input design algorithm is described which can be used to design control inputs which maximize parameter estimation accuracy. Details of each aspect of the rotorcraft identification approach are given. Examples of both simulated and actual flight data processing are given to illustrate each phase of processing. The procedure is shown to provide means of calibrating sensor errors in flight data, quantifying high order state variable models from the flight data, and consequently computing related stability and control design models.
Document ID
19790034143
Document Type
Conference Proceedings
Authors
Hall, W. E., Jr.
(Systems Control, Inc. Palo Alto, CA, United States)
Gupta, N. K.
(Systems Control, Inc. Palo Alto, CA, United States)
Hansen, R. S.
(Systems Control, Inc. Palo Alto, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1978
Subject Category
AIRCRAFT STABILITY AND CONTROL
Report/Patent Number
AHS 78-30
Meeting Information
In: American Helicopter Society, Annual National Forum(Washington, DC)
Funding Number(s)
CONTRACT_GRANT: NAS1-14549
Distribution Limits
Public
Copyright
Other