Accession Number : AD0448911


Title :   PITCH-YAW-ROLL COUPLING,


Corporate Author : ADVISORY GROUP FOR AERONAUTICAL RESEARCH AND DEVELOPMENT PARIS (FRANCE)


Personal Author(s) : Cronvich, L L ; Amsler, B E


Report Date : Apr 1961


Pagination or Media Count : 22


Abstract : One of the most significant coupling problems in recent missile experience is that which results from interaction between the pitch, yaw and roll modes of motion. This paper discusses the geometric, aerodynamic and control system couplings and their mutual interactions which give rise to overall system stability problems. The supersonic aerodynamic static stability and control characteristics of a typical configuration which experiences aerodynamic coupling both in attitude and in control are discussed. It is noted that a primary cause of the coupling is the existence of significantly different energy levels on the windward and leeward sides of the configuration. The functional block diagram of a typical missile steering and roll control system is presented. Dynamic signal flow relationships for the system are developed including the effects of pitch, yaw and roll aerodynamic and geometric coupling terms. Based on this signal flow representation, linear relationships are presented showing the effect of various coupling derivatives on the overall steering-roll system stability. (Author)


Descriptors :   *GUIDED MISSILES , PITCH(INCLINATION) , ROLL , YAW , AIRFRAMES , FLIGHT CONTROL SYSTEMS , AUTOMATIC PILOTS , STABILITY , DEFLECTION , ANGLE OF ATTACK , PRESSURE , MOTION , EQUATIONS , VORTICES , ATTITUDE CONTROL SYSTEMS , FEEDBACK


Distribution Statement : APPROVED FOR PUBLIC RELEASE