Blade and Hub Loads of Ballistically Damaged Helicopter Rotors

Abstract

The effects of (simulated) ballistic damage on helicopter rotor blade response and rotor hub loads are investigated. A finite element formulation based on Hamilton's principle is used for structural analysis, and aerodynamic loads are calculated using quasisteady aerodynamic theory. Each blade is as being composed of elastic beams undergoing flap bending, lag bending, elastic twist, and axial deflections. Dynamic responses of multi-blade rotor systems are calculated from nonlinear periodic normal mode equations using a finite element in time scheme. Results are calculated for the SA349/2 Gazelle helicopter for both undamaged and damaged blade configurations. Blade damage effects are determined in terms of blade mode shapes and frequencies, aeroelastic response, and rotor hub loads. Blade dissimilarity due to ballistic damage can induce a large 1/rev vibratory component on the rotor hub.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1993
Accession Number
ADA270663

Entities

People

  • Ki C. Kim

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Aerodynamic Configurations
  • Aircrafts
  • Airfoils
  • Airframes
  • Dynamic Response
  • Engineering
  • Equations
  • Flight
  • Frequency
  • Geometry
  • Helicopter Rotors
  • Helicopters
  • Mach Number
  • Military Research
  • Structural Properties
  • Tail Rotors

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Aerospace Engineering
  • Structural Dynamics.