Nondestructive evaluation of composite material damage using vibration reciprocity measurements
by Zwink, Brandon R., M.S.M.E., PURDUE UNIVERSITY, 2010, 158 pages; 1479736

Abstract:

Composite structures used in modern military aircraft are subject to a range of loading conditions such as foreign object impacts, which can produce sub-surface damage involving delamination, ply cracking, and honeycomb core crushing. Current damage detection methods such as ultrasound and tap testing must be applied locally and the inspection results are highly dependent on the experience of the operator. The U.S. Marine Corps is interested in developing methods of damage detection for composite materials that are field expedient and less dependent on the operator’s experience.

A vibration-based method was investigated for detecting damage in composite materials based on a measurement of the nonlinear forced response that damaged materials are assumed to exhibit. A damage feature was extracted for a structural component by quantifying the degree to which the reciprocity between two input-output structural paths fail due to the nonlinearities associated with damage.

Experimental results were obtained from carbon fiber composite samples as well as fiber reinforced plastic samples subjected to various levels of damage. It was determined that reciprocity measurements could be used to identify the presence of laminate-to-core disbonding beneath sensor locations in fiber reinforced plastic composite material. It was also found that reciprocity measurements were capable of identifying damage due to impact energies of 8 ft·lbf beneath sensor locations in carbon fiber composite material.

A static nonlinear theoretical model was used to develop a better understanding of why reciprocity fails for networks of nonlinear components. In addition, simulations of a tuned dynamic nonlinear theoretical model were shown to exhibit the same qualitative results as in the experiments that were performed on damaged composite material.

The benefits of this method were that it was less dependent on reference measurements from the undamaged component, that it was likely to be more robust to environmental and boundary conditions than methods based on the use of linear modal parameters for damage detection, and that it was less susceptible to operator error when compared to traditional methods such as tap testing and ultrasonic.

 
AdviserDouglas E. Adams
SchoolPURDUE UNIVERSITY
SourceMAI/ 49-01, p. , Sep 2010
Source TypeThesis
SubjectsAerospace engineering; Mechanical engineering
Publication Number1479736
Adobe PDF Access the complete dissertation:
 

» Find an electronic copy at your library.
  Use the link below to access a full citation record of this graduate work:
  http://gateway.proquest.com/openurl%3furl_ver=Z39.88-2004%26res_dat=xri:pqdiss%26rft_val_fmt=info:ofi/fmt:kev:mtx:dissertation%26rft_dat=xri:pqdiss:1479736
  If your library subscribes to the ProQuest Dissertations & Theses (PQDT) database, you may be entitled to a free electronic version of this graduate work. If not, you will have the option to purchase one, and access a 24 page preview for free (if available).

About ProQuest Dissertations & Theses
With over 2.3 million records, the ProQuest Dissertations & Theses (PQDT) database is the most comprehensive collection of dissertations and theses in the world. It is the database of record for graduate research.

The database includes citations of graduate works ranging from the first U.S. dissertation, accepted in 1861, to those accepted as recently as last semester. Of the 2.3 million graduate works included in the database, ProQuest offers more than 1.9 million in full text formats. Of those, over 860,000 are available in PDF format. More than 60,000 dissertations and theses are added to the database each year.

If you have questions, please feel free to visit the ProQuest Web site - http://www.proquest.com - or call ProQuest Hotline Customer Support at 1-800-521-3042.