THE RESPONSE OF A BISYMMETRIC AIRCRAFT TO SMALL COMBINED PITCH, YAW, AND ROLL CONTROL ACTIONS.
An abridged Doctoral thesis,
RAND CORP SANTA MONICA CALIF
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The linearized equations of motion of a rolling bisymmetric aircraft are formulated using body axes. It is shown that a the rate of change of angle of attack is a vector b a linearized form of the downwash-lag terms is valid only if the downwash-roll angle be small and c such a linearized form must use the vector relations of a. As a result, stability criteria are derived which are independent of the rolling of the reference axis system. The complete solution to the equations is presented for a stepped pitchyaw control action at constant roll rate. The complete solution is likewise given for a variable roll rate, valid only for a simplified system in which the Magnus Effect is neglected. Author