The present invention concerns a method for designing a deployment mechanism
for a flight surface on an airborne body, including the steps of determining a
stowed position of the flight surface, determining a deployed position of the flight
surface, identifying a first rotation axis and respective rotation angle and a
second rotation axis and respective rotation angle about and through which the
flight surface is rotatable in sequence to move the flight surface from the stowed
position to the deployed position, or vice versa, and using the identified first
and second rotation axes and rotation angles to determine a single equivalent rotation
axis and angle, about and through which the flight surface can be rotated from
the stowed position to the deployed position, or vice versa.
