Impact Detection for a Fiberglass Composite Rotor Blade

  • Budde C
  • Adams D
  • Meckl P
  • 13

    Readers

    Mendeley users who have this article in their library.
  • 6

    Citations

    Citations of this article.

Abstract

In this paper, a method is presented for impact identification that uses limited sensor application to characterize an unknown impact's location and force amplitude upon an operational composite helicopter blade and to determine the errors associated with the use of static frequency data for impact identification in rotating bodies. There have not been prior investigations into the use of limited sensor application or the error associated with using static frequency data for impact characterization in rotating bodies. Analytical modeling demonstrates that errors in estimated impacts due to centrifugal stiffening occur at the resonance and antiresonance frequencies of a rotating blade. The impact characterization method is shown to estimate the correct location of an impact 50%, 92%, and 99% with an average force estimate error of 4.6%, 4.6%, and 2.5% for symmetric, asymmetric and full-sized composite helicopter blades, respectively.

Get free article suggestions today

Mendeley saves you time finding and organizing research

Sign up here
Already have an account ?Sign in

Find this document

Authors

  • Carson Budde

  • Douglas Adams

  • Peter Meckl

Cite this document

Choose a citation style from the tabs below

Save time finding and organizing research with Mendeley

Sign up for free