THE RESPONSE OF A BISYMMETRIC AIRCRAFT TO SMALL COMBINED PITCH, YAW,AND ROLL CONTROL ACTIONS.

摘要

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 pitch/yaw 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)