Airframe Modeling

Vous avez une question, contacter notre assistance par E-mail : admin@clicours.com

The nonlinear model of the R’m’B describes the longitudinal (or pitch) dynamics System of a highly manoeuvrable missile airframe around its center of mass. The state dynamics vector x of the missile (see Fig. 4.1)1 is its angle of attack α (in rad) and pitch rotational rate q (in rad·s −1 ). The command is the elevator deflection angle δ (in rad), the output is the vertical acceleration η (in g’s) and its Mach number M is considered as an internal time varying parameter.The missile is considered to be operating during the terminal target inter-Mach trajectory cepting phase with its engine thrust equal to zero and the Mach profile given by the following nonlinear differential equation: dM dt = 1 vs ¡ −|η|sin|α| + AxM2 cos α ¢ , with M(0) = M0. (4.10)..