Correlation of Results of an OH-58A Helicopter Composite Tail Boom Test with a Finite Element Model.

Abstract

The results of testing an OH-58A composite tail boom and comparing its static and dynamic characteristics with those obtained from finite element analyses are presented in this report. Static load versus deflection data were used to verify the stiffness representation of the finite element model. Ground vibration test data were used to evaluate frequency and modal responses obtained from analysis. Discussions of each test configuration, including data analysis methodology and correlation results, are presented. Differences between measured static deflections and finite element analysis calculated deflections range from 6 to 12 percent. Natural frequency differences between test and analysis were less than 5 percent for the first and second elastic modes. Problems encountered during the testing and the impact on correlation are also discussed. Keywords: Helicopter; Composite; Primary structure; Finite element; Modeling; Correlation.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1985
Accession Number
ADA161062

Entities

People

  • Keith Hoff
  • Nick Calapodas

Organizations

  • United States Army Aviation and Missile Command

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms

DTIC Thesaurus Topics

  • Accelerometers
  • Actuators
  • Airframes
  • Army Aviation
  • Composite Materials
  • Dynamic Tests
  • Frequency
  • Fuselages
  • Horizontal Stabilizers
  • Instrumentation
  • Materials
  • Measurement
  • Modal Analysis
  • Resonant Frequency
  • Security
  • Static Tests
  • Tail Rotors

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Engineering
  • Computational Modeling and Simulation