The following equations are the model of the roll dynamics of a missile ([Bryson, 1975]). See Figure
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Figure P11.36
Whereδ = aileron deflection
b = aileron effectiveness constant
u = command signal to the aileron actuator
( = roll angle, ( = roll rate
Using the specific value b = 10 s-1 and ( = 1 s, and assuming that the state variables δ,(, and ( can be measured, develop a linear state-feedback controller to keep ( near 0. The dominant roots should be s = - 10 ( 10j, and the third root should be s = - 20.
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