DESIGN OF A LATERAL RIDE COMFORT CONTROL SYSTEM FOR STOL AIRCRAFT.

被引：0
作者：
Byrne, John Edwin
机构：
来源：
UTIAS Technical Note (University of Toronto, Institute for Aerospace Studies) | 1983年 / 247期
关键词：
CONTROL SYSTEMS; OPTIMAL; -; Theory;
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摘要：
A wide comfort control system is designed for a STOL aircraft to reduce lateral acceleration levels. The control laws are designed using both stat feedback and gust feedforward loops based on a rigid aircraft model. Control law performance is evaluated using root-mean-square values calculated from the spectral response of the aircraft with a Von Karman gust spectrum input. The turbulent gust input is based upon Etkin's four-point model which includes linear gust spatial gradients. The control laws are compared with the aircraft response with controls fixed and with an industry available autopilot.
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