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

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)

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1964
Accession Number
AD0621548

Entities

People

  • Robert H. Schuppe
  • Ronald E. Evans

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircraft Design
  • Aircrafts
  • Airframes
  • Analog Computers
  • Automatic
  • Compensation
  • Computers
  • Equations
  • Equations Of Motion
  • Inertia
  • Instability
  • Moment Of Inertia
  • Supersonic Aircraft

Readers

  • Aerodynamics/Aeronautics.
  • Calculus or Mathematical Analysis
  • Robotics and Automation.

Technology Areas

  • Hypersonics