DocumentCode
1142210
Title
C-17 flight control system overview
Author
Kowal, Brian W. ; Scherz, Carl J. ; Quinlivan, Richard
Volume
7
Issue
7
fYear
1992
fDate
7/1/1992 12:00:00 AM
Firstpage
24
Lastpage
31
Abstract
The basic requirements that drove the design of the McDonnell Douglas C-17 airlifter are examined. The background behind the deep stall avoidance, probability of loss of control, all-engine-out control, and safe go-around requirements is explained, and the overall flight control system (FCS) design is presented, focusing on features that satisfy the above-mentioned requires. Specific failure modes and their design safeguards are reviewed. The early flight test results are presented. Minor anomalies encountered and their effect on the final flight control design are discussed.<>
Keywords
aerospace computer control; aircraft control; computer interfaces; digital control; military systems; redundancy; McDonnell Douglas C-17 airlifter; actuator interface; databus architecture; failure; flight control; flight test; integrated digital fly by wire control; loss of control; probability; redundancy; robustness; Aerospace control; Aircraft; Control systems; Elevators; Engines; Mechanical systems; Redundancy; Robustness; Stability; System testing;
fLanguage
English
Journal_Title
Aerospace and Electronic Systems Magazine, IEEE
Publisher
ieee
ISSN
0885-8985
Type
jour
DOI
10.1109/62.149790
Filename
149790
Link To Document