Accession Number : AD0622615

Title :   FLIGHT TEST DETERMINATION OF LATERAL STABILITY AND CONTROL DERIVATIVES FOR A SINGLE ROTOR HELICOPTER. PART I. EQUATIONS OF MOTION, ANALYSIS TECHNIQUES, INSTRUMENTATION, AND FLIGHT SHAKEDOWN,

Corporate Author : CORNELL AERONAUTICAL LAB INC BUFFALO N Y

Personal Author(s) : Deazley,W. R. ; Schultz,E. R.

Report Date : AUG 1959

Pagination or Media Count : 132

Abstract : The lateral equations of motion were derived for the single rotor helicopter considering three rigid-body degrees of freedom. Means are presented for estimating the various physical and aerodynamic characteristics of the XHO3S-2 helicopter. Sample calculations are made in which the stability derivatives are found for the 70 mph case. Methods are presented for etracting the primary lateral aerodynamic stability derivatives from helicopter flight test data. Both steady-state and transient flight test methods were considered. The contributions of the various terms in the equations of motion to the lateral responses of the helicopter were studied on an analog computer. Both lateral cyclic pitch and tail rotor collective pitch step inputs were used for exciting the various lateral modes of the helicopter. Certain new instrumentation was developed to measure the necessary lateral variables. A complex strain gage installation measures the resolved lateral shear and moments in the rotor shaft. (Author)

Descriptors :   (*HELICOPTERS, STABILITY), CONTROL, FLIGHT TESTING, EQUATIONS, ROTARY WINGS, INSTRUMENTATION, DYNAMICS, AERODYNAMIC CHARACTERISTICS, PHYSICAL PROPERTIES

Distribution Statement : APPROVED FOR PUBLIC RELEASE