Accession Number : AD0855529
Title : Analog Simulation of Automatic Glide Slope Control Using Wing Lift Spoilers as Direct Lift Control.
Descriptive Note : Thesis,
Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA
Personal Author(s) : Lloyd, Robert C. ; Swift, James K.
Report Date : JUN 1968
Pagination or Media Count : 145
Abstract : The use of wing lift spoilers as a means of changing lift without changing angle of attack was studied for use in the landing approach task. The vehicle used was the F-8 type fighter. Automatic glide slope controllers were proposed using an elevator glide slope coupler in conjunction with an automatic power compensator for comparison with an automatic direct lift control system. The system gains were optimized for gust disturbances and initial offsets from glide slope. An analog computer simulation program including a manual control phase was used to determine arbitrary measures of effectiveness of the proposed systems. (Author)
Descriptors : (*JET FIGHTERS, LANDING AIDS), (*GLIDE PATH SYSTEMS, FLIGHT CONTROL SYSTEMS), (*AERODYNAMIC CONTROL SURFACES, LIFT), SPOILERS, MATHEMATICAL MODELS, ANALOG COMPUTERS, AUTOMATIC, GUSTS, ANGLE OF ATTACK, NAVAL AIRCRAFT, EQUATIONS OF MOTION, THESES.
Subject Categories : Attack and Fighter Aircraft
Terminal Flight Facilities
Air Navigation and Guidance
Distribution Statement : APPROVED FOR PUBLIC RELEASE