Helicopter Forced Response Vibration Analysis Method RTVIB20

Abstract

This report describes a helicopter vibration analysis method. In the method the rotor forcing for a single main rotor is calculated by integrating the forces and moments at the rotor center, and then applying them to a rigid helicopter airframe. The vibrations (any place in the airframe) are calculated as the to the applied hub center forces and moments. The method of analysis allows for dissimilar blades in the main rotor to simulate various type of blade damage and the resulting increase vibrations transmitted into the airframe. The analysis method is generic and can be used to analyze any single main rotor helicopter. An application is made for the UH-60A helicopter, resulting from the loss of outboard sections of one blade of the rotor, and the resulting vibrations in the cockpit are calculated.

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Document Details

Document Type
Technical Report
Publication Date
Feb 01, 1993
Accession Number
ADA261809

Entities

People

  • Joseph Fries

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Aerodynamic Forces
  • Aircrafts
  • Airframes
  • Artillery
  • Classification
  • Commerce
  • Computer Programs
  • Computers
  • Frequency
  • Fuselages
  • Helicopters
  • Military Research
  • Outboard
  • Security
  • Standards
  • Structural Components

Fields of Study

  • Engineering
  • Physics

Readers

  • Aerodynamics.
  • Explosive Engineering.
  • Life Cycle Cost Analysis