Accession Number : AD0763957
Title : Helicopter Gust Response Including Unsteady Aerodynamic Stall Effects.
Descriptive Note : Final rept.,
Corporate Author : UNITED AIRCRAFT CORP STRATFORD CONN SIKORSKY AIRCRAFT DIV
Personal Author(s) : Bergquist,Russell R.
Report Date : MAY 1973
Pagination or Media Count : 57
Abstract : The Sikorsky/UARL Normal Mode Rotor Aeroelastic Analysis (Computer Program Y-200) was modified to provide the capability of predicting the gust-response characteristics of pure and compound, single-rotor helicopters, including the effects of unsteady aerodynamics on rotor blade stall. The analysis was applied to examine the effects or rotor configuration, flight condition, and gust profile variables on rotor response characteristics. Only the short-term, controls-fixed response was investigated. The results were used to assess the accuracy of the gust-alleviation factor relation given by MIL-S-8698 (ARG) and USAAVLABS Technical Report 69-1 and to provide a basis for developing a more accurate relation. In addition, the impact of the gust on other quantities of interest such as blade vibratory moments and forces was briefly studied. Finally, an assessment of the relative importance of some of the assumptions in the analysis was also made. (Modified author abstract)
Descriptors : (*HELICOPTERS, GUST LOADS), ROTOR BLADES(ROTARY WINGS), AERODYNAMIC LOADING, BENDING, STALLING, VIBRATION, NUMERICAL ANALYSIS
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE