ABSTRACT
We now generalize the eigenstructure assignment flight control design methodology to include the design of low-order dynamic compensators of any given order , 0 ≤ ≤ n− r. Recall that n and r are the dimensions of the aircraft state and output vectors, respectively. Consider the linear time-invariant aircraft described by Equations 16.1 and 16.2 with a linear time-invariant dynamic controller specified by
z˙(t) = Dz(t)+Ey(t), (16.21) u(t) = F(z)+Gy(t), (16.22)
where the controller state vector z(t) is of dimension , 0 ≤ ≤ n− r. It is convenient to model the aircraft and compensator by the composite system originally proposed
by Johnson and Athans [10]. Thus, define
˙¯x = A¯x¯ + B¯u¯, (16.23) y¯ = C¯x¯, (16.24) u¯ = F¯y¯, (16.25)
where
x¯ = [x z
] , A¯ =
[ A|0 0|0
] , B¯ =
[ B|0 0|I
] , C¯ =
[ C|0 0|I
] , F¯ =
[ G|F E|D
] .
