PROGRAM FOR CALCULATION AND STUDY OF STABILITY AND COLTROL OF AIRPLANES

Abstract

For airplanes, two problems of stability and control are concerned each other. In opinion of flight mechanics, the airplane is a solid object moving under the influence of many factors which change the distribution of pressures around the object due to the state of atmosphere, the speed of object, and the requirement of control. This paper presents results of established program for calculating and studying the stability and control of airplanes by solving the small disturbance differential equations of motion with unknowns written in form of harmonic functions. Time response solutions of motions depend on variations of aerodynamic forces. General interface permits to directly input airplane aerodynamic dimensions, coefficients of aerodynamic derivative, and has branch interfaces managing control parameters. With a change of aerodynamic forces, we can correlatively obtain diagrams of response allowing analyses and choices suitable solutions on stability quality. The program can be connected to programs of aerodynamic calculations corresponding with different control objectives.