Experimental study on the compression-after-impact behavior of foam-core sandwich panels

Abstract

This paper presents the experimental results pertaining to the deformation, failure mode, failure mechanism and residual strength for the compression-after-impact tests of woven polymer-based foam-core sandwich panels. Sandwich panels with impact-type damage, inflicted via low-velocity impact, were tested to failure in compression. The optical strain measurement system ARAMIS was used to obtain the complete non-uniform strain and displacement fields of the damaged face-sheet. Consequently, damage in the face-sheets was characterized by fractography. It has been found that the dominant damage mechanism is kink band in the impacted face-sheets due to fiber plastic micro-buckling. Besides, the effects of impactor diameter, impact energy, face-sheet thickness and foam core thickness on the residual strength under in-plane compressive loading were studied. This study will be useful for characterizing and predicting the residual compressive strength and understanding the failure mechanism of woven polymer-based foam-core sandwich panel.

Keywords

Compression after impact sandwich panels digital image correlation residual strength failure mechanism

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References

Abrate S. Impact on composite structures. New York: Cambridge University Press,1998.

Zenkert D. The handbook of sandwich construction. 2nd ed. London: EMAS Chameleon Press, 1997.

Tomblin JS, Lacy T, Smith B, et al. Review of damage tolerance for composite sandwich airframe structures. Report No.DOT/FAA/AR-99/49, Federal Aviation Administration, 1999.

NASA. Standard Tests for Toughened Resin Composites. NASA reference publication 1092, ACEE composites project office, Langley research center (Hampton,Va), 1982.

Boeing. Advanced composite compression tests. Boeing specification support standard BSS 7260, Rev.C, The Boeing Co., (Seattle, WA), 1988.

Tomblin JS, Raju KS, Liew J, et al. Impact damage characterization and damage tolerance of composite sandwich airframe structures. Report No.DOT/FAA/AR-00/44, Federal Aviation Administration, 2001.

Tomblin JS, Raju KS, Acosta JF, et al. Impact damage characterization and damage tolerance of composite sandwich airframe structures C phase II. Report No.DOT/FAA/AR-02/80, Federal Aviation Administration, 2002.

Tomblin JS, Raju KS and Arosteguy G. Damage resistance and tolerance of composite sandwich panels-scaling effects. Report No.DOT/FAA/AR-03/75, Federal Aviation Administration, 2004.

Gilioli A, Sbarufatti C, Manes A, et al. Compression after impact test (CAI) on NOMEX honeycomb sandwich panels with thin aluminum skins. Compos Part B 2014; 67: 313-325.

10.

Moody

Harris

Vizzini

. Composite sandwich panels scaling and curvature effects on the damage tolerance of impacted. J Sand Struct Mater 2002; 4: 71–82.

11.

Davies

GAO

Hitchings

Besant

. Compression after impact strength of composite sandwich panels. Compos Struct 2004; 63: 1–9.

12.

Samarah

Weheba

Lacy

. Response surface characterization of the mechanical behavior of impact-damaged sandwich composites. J Appl Stat 2006; 33: 427–437.

13.

Leijten

Bersee

HEN

Bergsma

. Experimental study of the low-velocity impact behaviour of primary sandwich structures in aircraft. Compos Part A 2009; 40: 164–175.

14.

Zhou

Hill

. In-plane compressive strength of honeycomb sandwich panels impact damage and energy-absorbing characteristics and residual. J Sand Struct Mater 2009; 11: 329–356.

15.

Raju

Smith

Tomblin

. Impact damage resistance and tolerance of honeycomb core sandwich panels. J Compos Mater 2008; 42: 385–412.

16.

Nettles

Jackson

. Launch vehicles compression after impact testing of sandwich composites for usage on expendable. J Compos Mater 2010; 44: 707–738.

17.

Shipsha

Zenkert

. Compression-after-impact strength of sandwich panels with core crushing damage. Appl Compos Mater 2005; 12: 149–164.

18.

Edgren

Bull

. Compressive failure of impacted NCF composite sandwich panels-characterisation of the failure Process. J Compos Mater 2004; 38: 495–514.

19.

Bull

Edgren

. Compressive strength after impact of CFRP-foam core sandwich panels in marine applications. Compos Part B 2004; 35: 535–541.

20.

Zhang

Wang

. The residual compressive strength of impact-damaged sandwich structures with pyramidal truss cores. Compos Struct 2013; 105: 188–198.

21.

Wang J, Waas AM and Wang H. Experimental study on the low velocity impact behaviour of foam core sandwich materials. In: AIAA/ASME/ASCE/AHS/ASC structures, structural dynamics and materials conference, Hawaii, 2012, pp.1–13.

22.

Wang

Waas

Wang

. Experimental and numerical study on the low-velocity impact behavior of foam-core sandwich panels. Compos Struct 2013; 96: 298–311.

23.

ASTM. Standard test method for compressive residual strength properties of damaged polymer matrix composite plates. Philadelphia, PA: American Society for Testing and Materials, 2007. ASTM D7137/D7137M-07.