Accession Number : AD0015982
Title : STUDY OF AUTOMATIC CONTROL SYSTEMS FOR HELICOPTERS. PART IV. EQUATIONS OF MOTION FOR A NOMINALLY-HOVERING HELICOPTER WITH ROTOR RPM DEGREE OF FREEDOM
Corporate Author : HONEYWELL INC HOPKINS MINN
Personal Author(s) : WARSETT,PAUL
Report Date : JUN 1953
Pagination or Media Count : 1
Abstract : A helicopter for the single main-rotor type and employing a tail rotor for torque compensation was considered in the development of equations which define the motions of a helicopter experiencing transient disturbances from steady-state hovering. The influence of simultaneous transients in rotor rpm was included in the treatment. On the basis of a linearized analysis, 9 equations were developed in describing the 9 different types of motion involved. The forces acting on the main rotor which produced longitudinal and lateral motion were shown to be independent of transient disturbances in rpm. This indicated that without a tail rotor there would be complete absence of coupling between rotor rpm and the rolling and pitching motions of the helicopter. The existence of coupling between yawing and vertical motions and between longitudinal and lateral motions was found only as a consequence of the transient effects on the tail rotor in the hovering regime. The converse problem of the influence of helicopter motion on rotor rpm is examined in an appendix. (See also AD-18 276, Confidential, AD-12 062).
Descriptors : , COMPENSATION, EQUATIONS, HELICOPTERS, HOVERING, LINEARITY, MOTION, PITCH(MOTION), STEADY STATE, SYNCHRONISM, TAIL ROTORS, TORQUE, TRANSIENTS, VERTICAL ORIENTATION, YAW.
Distribution Statement : APPROVED FOR PUBLIC RELEASE