Accession Number:

AD0605062

Title:

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

Descriptive Note:

An abridged Doctoral thesis,

Corporate Author:

RAND CORP SANTA MONICA CALIF

Personal Author(s):

Report Date:

1956-12-27

Pagination or Media Count:

34.0

Abstract:

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

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE