Design of Sandwich Composites with Multi-Functional Facesheets

2001 ◽  
Vol 702 ◽  
Author(s):  
Uday K. Vaidya ◽  
Selvum Pillay ◽  
Helena Ricks ◽  
Shane Bartus ◽  
Chad Ulven ◽  
...  

ABSTRACTSandwich composites find increasing use as flexural load bearing lightweight sub-elements in air / space vehicles, rail / ground transportation, marine and sporting goods. The core materials in these applications is usually balsa, foam or honeycombs, while laminated carbon or glass are used as facesheets. A limitation of traditional sandwich configurations is that the space in the core becomes inaccessible once the facesheets are bonded in place. Significant multi-functional benefits can be obtained by making either the facesheets or the core, space accessible. Multi-functionality is generally referred to as value added to the structure that enhances functions beyond traditional load bearing. Such functions may include sound / vibration damping, ability to route wires or embed sensors. The present work considers traditional core materials of nomex and aluminum honeycombs that possess functional space accessible facesheets, and their low velocity impact (LVI) response.

1999 ◽  
Author(s):  
Uday K. Vaidya ◽  
Mohan V. Kamath ◽  
Mahesh V. Hosur ◽  
Anwarul Haque ◽  
Shaik Jeelani

Abstract In the current work, sandwich composite structures with innovative constructions referred to as Z-pins, or truss core pins are investigated, in conjunction with traditional honeycomb and foam core sandwich constructions, such that they exhibit enhanced transverse stiffness, high damage resistance and furthermore, damage tolerance to impact. While the investigations pertaining to low velocity impact have appeared recently in Vaidya et al. 1999, the current paper deals with compression-after-impact studies conducted to evaluate the residual properties of sandwich composites “with” and “without” reinforced foam cores. The resulting sandwich composites have been investigated for their low velocity (< 5 m/sec) impact loading response using instrumented impact testing at energy levels ranging from 5 J to 50 J impact energy. The transverse stiffness of the cores and their composites has also been evaluated through static compression studies. Compression-after-impact studies were then performed on the sandwich composites with traditional and pin-reinforcement cores. Supporting vibration studies have been conducted to assess the changes in stiffness of the samples as a result of the impact damage. The focus of this paper is on the compression-after-impact (CAI) response and vibration studies with accompanying discussion pertaining to the low velocity impact.


2013 ◽  
Vol 710 ◽  
pp. 136-141
Author(s):  
Li Jun Wei ◽  
Fang Lue Huang ◽  
Hong Peng Li

Sandwich composite laminates structure is a classic application of composite material on actual aircraft structural. Dealing with low-velocity impact damage and residual compressive strength of sandwich composite laminates, explicit finite element method of ABAQUS/Explicit software was adopted to simulate low-velocity impact and compression process. Impact response and invalidation on compression between sandwich composite laminates with different core materials and regular composite laminates were compared. The simulation results indicated that softer core materials can absorb more impact energy, reduce the structure damage and enhance the residual compressive strength after impact.


2005 ◽  
Vol 70 (3) ◽  
pp. 374-381 ◽  
Author(s):  
Brian Freeman ◽  
Eric Schwingler ◽  
Mohammad Mahinfalah ◽  
Ken Kellogg

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