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Record Details

Record 77 of 42365
Description of a tilt wing mathematical model for piloted simulation
Author and Affiliation:
Totah, Joseph J.(NASA Ames Research Center, Moffett Field, CA, United States)
Abstract: A tilt-wing mathematical model that was used in a piloted six-deg-of-freedom flight simulation application is presented. Two types of control systems developed for the model - a conventional programmed-flap wing-tilt control system and a geared-flap wing-tilt control system - are discussed. The objective of this effort was to develop the capability to study tilt-wing aircraft. Experienced tilt-wing pilots subjectively evaluated the model using programmed-flap control to assess the quality of the simulation. The objective was met and the model was then applied to study geared-flap control to investigate the possibility of eliminating the need for auxiliary pitch control devices. This was performed in the moving-base simulation environment, and the vehicle responses with programmed-flap and geared-flap control were compared.
Publication Date: May 01, 1991
Document ID:
19920031821
(Acquired Nov 22, 1995)
Accession Number: 92A14445
Subject Category: AIRCRAFT STABILITY AND CONTROL
Document Type: Preprint
Publisher Information: United States
Financial Sponsor: NASA; United States
Organization Source: NASA Ames Research Center; Moffett Field, CA, United States
Description: 16p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: CONTROL SYSTEMS DESIGN; FLIGHT SIMULATION; MATHEMATICAL MODELS; PITCH (INCLINATION); TILT WING AIRCRAFT; FLIGHT SIMULATORS; HOVERING; TAIL ROTORS; V/STOL AIRCRAFT
Imprint And Other Notes: AHS, Annual Forum, 47th, Phoenix, AZ, May 6-8, 1991, Paper. 16 p.
Availability Source: Other Sources
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