AN INVESTIGATION OF THE EFFECT OF SIMPLIFIED EQUATIONS OF MOTION AND VARIOUS INPUTS ON AUTOMATIC-THROTTLE DEVICES.
NAVAL POSTGRADUATE SCHOOL MONTEREY CALIF
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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