Helicopter Gust Response Including Unsteady Aerodynamic Stall Effects

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.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1973
Accession Number
AD0763957

Entities

People

  • Russell R. Bergquist

Organizations

  • United Technologies Corporation

Tags

DTIC Thesaurus Topics

  • Aerodynamic Configurations
  • Aerodynamic Forces
  • Aircraft Equipment
  • Aircrafts
  • Airframes
  • Bending Moments
  • Computer Programs
  • Dynamic Response
  • Fixed Wing Aircraft
  • Frequency
  • Helicopter Rotors
  • Helicopters
  • Physical Properties
  • Rotary Wing Aircraft
  • Standards
  • Steady State
  • Unsteady Aerodynamics

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Control Systems Engineering.