Flight Dynamics Modeling of a Supersonic Aircraft Concept

摘要

Nonlinear six-degree-of-freedom flight modeling of a new supersonic aircraft concept was implemented using MATLAB. For the mathematical model, force and moment coefficient data were presented in look up tables as they were available from wind tunnel tests of a scaled model of the aircraft. The aerodynamic and engine data were used in linear interpolations for a range of Mach numbers. Damping derivatives were obtained using empirical DATCOM methods. Programming routines for trim and numerical integration were included in. this investigation. Time history variation of state variables shows aircraft motion for given flight conditions. The modeling procedure described should be useful for the preliminary dynamic modeling of the supersonic aircraft.