Rotational Motion

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Stability and Control
Rotational Motion
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Stability and Control
An aircraft is stable if it returns to its
initial equilibrium flight conditions when it
is perturbed. There are two main types of
aircraft instability
An aircraft with static instability uniformly
departs from an equilibrium condition
An aircraft with dynamic instability oscillates
about the equilibrium condition with increasing
amplitude.
There are two modes of aircraft control one
moves the aircraft between equilibrium states,
the other takes the aircraft into a
non-equilibrium (accelerating) state.
Control is directly opposed to stability.
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Longitudinal Static Stability
cg
Time 0.0
Tail Force
Aircraft encounters gust Nose pitches up
Resulting Motion
Tail Force
Time 1.0
Airflow Direction
Time 2.0
Tail Force
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Lateral Static Stability
Time 0.0
Lift Vectors
Dihedral Angle
View Downstream
Weight
Aircraft rolls slightly to the right
Time 1.0
Resulting Motion
Weight
Lift Vectors
Dihedral Angle
Time 2.0
Weight
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