Application of stochastic optimal reduced state feedback gain computation procedures to the design of aircraft gust alleviation controllersA stochastic linear model that accounts for process parameter and initial uncertainty, measurement noise, and a restricted number of measurable outputs was used to determine feedback gains useful for reducing the vertical acceleration which results from the presence of a vertical wind gust. Considered in the study were the influence of various feedback configurations, the effects of sensor noise, flight condition changes, and initialization procedures. Results showed that for sixth order linearized longitudinal motion, a controller with feedback on three states could be designed for effective gust alleviation taking into account both sensor noise and flight condition variation.
Document ID
19800030652
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Sobel, K. (Rensselaer Polytechnic Inst. Troy, NY, United States)
Kaufman, H. (Rensselaer Polytechnic Institute, Troy, N.Y., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1979
Subject Category
Aircraft Stability And Control
Meeting Information
Meeting: A link between science and applications of automatic control