A Flight Control System Providing A Simple-to-Fly, Constant Attitude Aircraft

Format:

Conference/Event

Author/Creator:

Smetana, Frederick O., author.

Conference Name:

National Business Aircraft Meeting and Engineering Display (1971-03-24 : Wichita, Kansas, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1971

Summary:

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

Notes:

Vendor supplied data

Publisher Number:

710393

Access Restriction:

Restricted for use by site license