
Estimation of Dynamic Systems: Applications 491
be put into a state-space form. In this section we present this approach to estimate
C
D
0
, C
L
0
,andC
m
0
, using measurements of angle of attack, velocity, angular rate, and
pitch angle. The longitudinal equations of motion are shown in example 6.5. The
state vector, x, consists of v
1
, v
3
,
ω
2
,
θ
, C
D
0
, C
L
0
,andC
m
0
. Note that the horizontal
and vertical positions, x and z, are not required in this formulation. See §A.10 for a
full description of the equations of motion for an aircraft.
Several partial derivatives are required in the EKF. These may be computed nu-
merically using the method described in example