The pitch plane manoeuvring characteristics of a solid propellant missile under captive firing conditions are considered. Analysis techniques are used to establish the dynamic model of the suspended, lumped parameter representation of the vehicle, which is regulated directionally by thrust vectoring. Three-term feedback control is employed to confine the response of the system to both demanded input changes and external load disturbances from airstream turbulence and defensive projectile debris strikes. Simulated manoeuvring characteristics are computed for demonstration purposes.
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