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Flight Evaluation of an Aircraft with Side and Center Stick Controllers and Rate-Limited AileronsAs part of an ongoing government and industry effort to study the flying qualities of aircraft with rate-limited control surface actuators, two studies were previously flown to examine an algorithm developed to reduce the tendency for pilot-induced oscillation when rate limiting occurs. This algorithm, when working properly, greatly improved the performance of the aircraft in the first study. In the second study, however, the algorithm did not initially offer as much improvement. The differences between the two studies caused concern. The study detailed in this paper was performed to determine whether the performance of the algorithm was affected by the characteristics of the cockpit controllers. Time delay and flight control system noise were also briefly evaluated. An in-flight simulator, the Calspan Learjet 25, was programmed with a low roll actuator rate limit, and the algorithm was programmed into the flight control system. Side- and center-stick controllers, force and position command signals, a rate-limited feel system, a low-frequency feel system, and a feel system damper were evaluated. The flight program consisted of four flights and 38 evaluations of test configurations. Performance of the algorithm was determined to be unaffected by using side- or center-stick controllers or force or position command signals. The rate-limited feel system performed as well as the rate-limiting algorithm but was disliked by the pilots. The low-frequency feel system and the feel system damper were ineffective. Time delay and noise were determined to degrade the performance of the algorithm.
Document ID
19970004404
Acquisition Source
Armstrong Flight Research Center
Document Type
Contractor Report (CR)
Authors
Deppe, P. R. (Calspan Advanced Technology Center Buffalo, NY United States)
Chalk, C. R. (Calspan Advanced Technology Center Buffalo, NY United States)
Shafer, M. F. (National Aeronautics and Space Administration. Hugh L. Dryden Flight Research Center Edwards, CA United States)
Date Acquired
September 6, 2013
Publication Date
November 1, 1996
Subject Category
Aircraft Stability And Control
Report/Patent Number
NAS 1.26:198055
NASA-CR-198055
Report Number: NAS 1.26:198055
Report Number: NASA-CR-198055
Accession Number
97N12596
Funding Number(s)
PROJECT: RTOP 505-64-30
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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