A MISSILE PROBLEM
The nonlinear aerodynamic model is described in the first subsection, while the linearized model is presented in the second one. The #<*> autopilot is synthesized in the third subsection.
a: angle of attack. q: pitch rotational rate.
6: actual tail deflection angle.
Sc: commanded tail deflection angle. rjc: commanded acceleration. rj: actual acceleration.
M: Mach number.
V: missile velocity.
Mass: missile mass.
Iy pitch moment of inertia.
Q: dynamic pressure.
S: reference area. d: missile diameter.