High-Frequency Vibration Response of Metal Honeycomb Sandwich Structure

Article Preview

Abstract:

ARMOR TPS panel is above the whole ARMOR TPS, and the metal honeycomb sandwich structure is the surface of the ARMOR TPS panel. So the metal honeycomb sandwich structure plays an important role in the ARMOR TPS, while it bears the flight dynamic pressure and stands against the flight dynamic calefaction. So the active environment of metal honeycomb sandwich structure is very formidable. We have to discuss any extreme situation, for reason of making sure aerial vehicle is safe. And high-frequency vibration is one of active environment. In this paper we have analyzed high-frequency vibration response of metal honeycomb sandwich structure. We processed high-frequency vibration experiment by simulating true aerial environment. Sequentially we operated high-frequency vibration experiment of metal honeycomb sandwich structure with cracks, notches and holes. Then finite-element analysis was performed by way of validating the experiment results. Haynes214 is a good high temperature alloy material of both face sheet and core at present, so we choose it in this paper.

You might also be interested in these eBooks

Info:

Periodical:

Advanced Materials Research (Volumes 79-82)

Pages:

1727-1730

Citation:

Online since:

August 2009

Export:

Price:

Permissions CCC:

Permissions PLS:

Сopyright:

© 2009 Trans Tech Publications Ltd. All Rights Reserved

Share:

Citation:

[1] John T Dorsey, Carl C Poteet, Roger R Chen, Kathryn E Wurster, Metallic Thermal Protection System Technology Development: Concepts, Requirements And Assessment Overview. AIAA 200220502, 40th Aerospace Sciences Meeting & Exhibit, 14217, January (2002).

DOI: 10.2514/6.2002-502

Google Scholar

[2] HAN Jie-cai; CHEN Gui-qing; MENG Song-he; LI Xiao-hai, New-typed ARMOR thermal protection systems[J].Journal of Astronautics,2004,(03):350-353.

Google Scholar

[3] Blosser M L. Development of Metallic Thermal Protection Systems for the Reusable Launch Vehicle NASA Technical Memorandum, 110296.

Google Scholar

[4] Rasky D J, Milos F S, Squire T H. Thermal protection system materials and costs for future reusable launch vehicles . Journal of Spacecraft and Rockets, 2001, 38(2) : 294~296.

DOI: 10.2514/2.3686

Google Scholar

[5] Qiuming Zhang, Xiaodong He. Microstructural evolution and mechanical properties of a nickel-based honeycomb sandwich. Mater Charact 2009; 178- 182.

DOI: 10.1016/j.matchar.2008.08.013

Google Scholar

[6] Shi Liping Li Yao He Xiaodong, Research on Metal Thermal Protection System, Aerospace Materials & Technology, 2005, (3): 21-23. Telephone: 0451-86402323, 13766870730. Email: kongxianghao_27@sina. com.

Google Scholar