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.

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