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A Flight Control System Providing A Simple-to-Fly, Constant Attitude Aircraft
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1971 by SAE International in United States
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Most light aircraft accidents occur during landing and takeoff because at these times the pilot must operate controls frequently and precisely and with more than average force. These operations are further complicated by the nose-high attitude of the aircraft, which interferes with a normal visual control reference. The purpose of the studies reported here was to design an aircraft that would fly at zero pitch angle and would require a minimum of pilot commands for satisfactory operation. Preliminary investigation showed that it would be possible to modify an existing airplane by providing a three-component control system, new wing with Fowler flaps for lift modulation, and additional longitudinal control power. The details of these modifications are described fully in this paper.