A satellite single-axis attitude control system can be represented by the block diagram in Figure 1. The variables
k,a
, and
b
are controller parameters, and
J
is the spacecraft moment of inertia. Suppose the nominal moment of inertia is slug (
:ft^(2)

Question

A satellite single-axis attitude control system can be represented by the block diagram in Figure 1. The variables

k,a

, and

b

are controller parameters, and

J

is the spacecraft moment of inertia. Suppose the nominal moment of inertia is slug (

:ft^(2)

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