A Study for Damage Mode of Composite Aircraft Structure with Advanced Composite Materials

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More and more advanced composite materials are used in mainly supporting structure of civil aviation; its airworthiness safety should be the focus of the research. Damage assessment is the key step in the general composite repair procedure. In this paper, the ANSYS calculating method is validated on the basis of classic laminate theory which could be used to calculate composite strength. In one case, it is applied to simulation and modeling of the B767 landing gear door. The case shows that composite damage mode such as low velocity impact damage, curing and fatigue could be evaluated with finite element method, the result of evaluation is provided as a means to composite damage assessment. Thereafter, the finite element method can be used for structural health monitoring to advanced composites.

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Periodical:

Edited by:

B. Xu and H.Y. Li

Pages:

100-104

Citation:

Y. Gao et al., "A Study for Damage Mode of Composite Aircraft Structure with Advanced Composite Materials", Advanced Materials Research, Vol. 583, pp. 100-104, 2012

Online since:

October 2012

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$38.00

[1] U. S. Department of Transportation, Federal Aviation Administration: Composite Aircraft Structure. AC NO. 20-107B. (2009).

[2] Yao Weixing, Himmel N: A New Cumulative Fatigue Damage Model for Fiber-reinforced Plastics. Composites Science and Technology. (2000), pp.59-64.

DOI: https://doi.org/10.1016/s0266-3538(99)00100-1

[3] European Aviation Safety Agency: LIBCOS-Load upon impact behavior of composite structure. (2009), p.24.

[4] Eric C. Lundgren: Design and Maintainability Considerations Regarding the Effects of Suborbital Flights on Composite Constructed Vehicles. Aerospace report NO. ATR-2010(5569)-1. (2010).

[5] Schonberg, W. P: Protecting Earth-Orbiting Spacecraft Against Micro-Meteoroid/Orbital Debris Impact Damage Using Composite Structural Systems and Materials: An Overview. Advances in Space Research, vol. 45. (2010). pp.709-720.

DOI: https://doi.org/10.1016/j.asr.2009.11.014

[6] Berner, J.: Bolted Repair in Composite Structure: 787 Wing/Empennage/Landing Gear. FAA Workshop, Chart Package. (2009).

[7] Seneviratne, W. P., Tomblin, J. S: Durability & Damage Tolerance Testing and Analysis Protocols for Composite Structures: Life Factor, Load-Enhancement Factors, and Fatigue Life. FAA/EASA/Industry Composite Damage Tolerance & Maintenance Workshop, Chart Package, Tokyo, Japan. (2009).

[8] Shyprykevich, P: FAA R&D in Composite Sandwich Structures. FAA Damage Tolerance & Maintenance Workshop. (2006).