Accession Number : AD0621548

Title :   AN INVESTIGATION OF THE EFFECT OF SIMPLIFIED EQUATIONS OF MOTION AND VARIOUS INPUTS ON AUTOMATIC-THROTTLE DEVICES.

Descriptive Note : Master's thesis,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF

Personal Author(s) : Evans,Ronald E. ; Schuppe,Robert H.

Report Date : 1964

Pagination or Media Count : 142

Abstract : This is the second in a series of investigations of automatic-throttle compensation systems. Landing condition speed instabilities are usually associated with modern supersonic aircraft design. The full airframe equations of motion give accurate results but are much too complicated. The simplification of assuming a zero moment of inertia is made. To test the validity, analog computer results are compared with those obtained with the full equations. Attempts are made to gain a better response by sensing different automatic-throttle input variables. (Author)

Descriptors :   (*AIRSPEED, CONTROL), (*FIGHTER AIRCRAFT, AIRSPEED), MOTION, STABILITY, AIRFRAMES, SWEPT WINGS, FLIGHT CONTROL SYSTEMS, SIMULATION, ANALOG COMPUTERS, NAVAL AIRCRAFT

Distribution Statement : APPROVED FOR PUBLIC RELEASE