<DOC>
<DOCNO>
813
</DOCNO>
<TITLE>
the motion of rolling symmetrical missiles referred
to a body-axis system .
</TITLE>
<AUTHOR>
nelson,r.l.
</AUTHOR>
<BIBLIO>
naca tn.3737, 1956.
</BIBLIO>
<TEXT>
  the linearized equations of motion have been derived for a rolling
missile having slight aerodynamic asymmetries .  time histories of
rolling-missile motions referred to a body-axis system have been prepared
to show the types of missile motions that can be encountered .
the motions resulting from a trim change and a pulse-rocket disturbance
are shown to be determined mainly by the ratio of rolling velocity to
pitching frequency .
  finally, the derived equations are used in establishing a technique
for the reduction of rolling-missile oscillation data .  it is shown
that the aerodynamic derivatives can be obtained from flight data if
four accelerations are measured .  the method is applied to the results
obtained from a flight test of a missile configuration .
</TEXT>
</DOC>
