Failure of compression-loaded multidirectional composite laminates

Shuart, Mark J.

doi:10.2514/3.10255

Cited by 64 publications

(30 citation statements)

References 9 publications

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“…Initial fibre misalignment angles have been reported to be smaller in the through-the-thickness direction [25], but more recent results suggest they can be similar in magnitude [26]. The present model assumes that the initial fibre misalignment is equal in magnitude in the transverse direction, through the thickness direction, or in any direction between the two.…”

Section: Proposed 3d Kinking Modelmentioning

confidence: 98%

Physically-based failure models and criteria for laminated fibre-reinforced composites with emphasis on fibre kinking: Part I: Development

Pinho

Iannucci²,

Robinson³

2006

Composites Part A: Applied Science and Manufacturing

370

224

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Abstract3D failure criteria for laminated fibre-reinforced composites, based on a physical model for each failure mode and considering nonlinear matrix shear behaviour, are developed. Special emphasis is given to compression failure. The physical model for matrix compression failure is based on the Mohr-Coulomb criterion and also predicts the fracture angle. For fibre kinking, an initial fibre-misalignment angle is considered to trigger failure, due to further rotation during the compressive loading. The plane where the kinking takes place is predicted by the model, as well as the kink-band angle. Applications are presented that validate the model against experimental data.

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Section: Proposed 3d Kinking Modelmentioning

confidence: 98%

Physically-based failure models and criteria for laminated fibre-reinforced composites with emphasis on fibre kinking: Part I: Development

Pinho

Iannucci²,

Robinson³

2006

Composites Part A: Applied Science and Manufacturing

370

224

View full text Add to dashboard Cite

show abstract

“…These issues are covered in detail in [9, Volume III]. 9) from other publications, and case 10, a ± θ layup case of AS4/3502 material reported by [10,11]. Failure of a laminate comprised of unidirectional or [±θ] layups occurs at first ply failure.…”

Section: Two Step Process For Defining Correlations Factorsmentioning

confidence: 99%

Consistent Structural Integrity in Preliminary Design Using Experimentally Validated Analysis

Collier¹,

Yarrington²

2005

46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference

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Coupling analytical methods to experimental results forms the basis of consistent structural integrity by analysis. By establishing repeatable statistical variance from building block test data for unique failure modes, it is possible to identify correlation factors (CFs) that account not only for analysis inaccuracy, but also observed scatter in test results. Industry accepted failure analysis predictions then can be used to design more robustly and to avoid unanticipated design flaws discovered in final design, or worse yet lead to part failure. The CFs can be used to adjust the individual margins-of-safety to produce more consistent structural integrity in the design and dependability in weight predictions of an aerospace vehicle. Such a capability is most useful during preliminary design where 80% of the design decisions carry forward, including the uninformed ones that bring with them undesirable difficulties of meeting weight goals, passing structural testing on the first try, and costly certification. The presented approach has been implemented in the HyperSizer® automated design tool that results in significant design cycle time reduction with the ability to analyze orders of magnitude more design configurations. Substantial risk reduction in final design is achieved from the integration and use of correlated, higher fidelity tools earlier in the design process. Presented are summary results from a recent Long Range Strike Aircraft preliminary design that compares the traditional, zero-margin for all failure modes approach, vs. the presented approach that achieves the same % reliability for all potential failure modes. Included are identified areas of the vehicle sized the traditional zero-margin method that results in an unexpected and unacceptable low reliability even though it is 9% heavier then reliability based sizing.

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“…The second failure predictions were made for AS4/3502 angle-ply composites loaded under compression. Experimental data was obtained from [6]. The critical dilatational invariant value for the stress invariant criteria was obtained from a transverse tension test.…”

Section: Task 1: Formulation Of the Asymptotic Theory For Abruptly Chmentioning

confidence: 99%

COLLABORATIVE RESEARCH AND DEVELOPMENT (CR&D) Delivery Order 0055: Molecular Dynamics Modeling Support

Brietzman¹

2007

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YY)2. REPORT TYPE 3. DATES COVERED (From -To) AFRL/RXOB SPONSORING/MONITORING AGENCY REPORT NUMBER(S) AFRL-RX-WP-TM-2010-4128 DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution unlimited. The theory applies to zones containing strong spatial variance of local material properties. The method is used to recover the local field across ply interfaces for a pre-stressed multi-ply fiber reinforced composite. The results are shown to be in good agreement with direct numerical simulations for realistic fiber sizes and fiber-matrix elastic properties. We also demonstrate failure envelopes of composite systems using homogenization/dehomogenization micro-mechanical enhancement techniques.

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Failure of compression-loaded multidirectional composite laminates

Cited by 64 publications

References 9 publications

Physically-based failure models and criteria for laminated fibre-reinforced composites with emphasis on fibre kinking: Part I: Development

Physically-based failure models and criteria for laminated fibre-reinforced composites with emphasis on fibre kinking: Part I: Development

Consistent Structural Integrity in Preliminary Design Using Experimentally Validated Analysis

COLLABORATIVE RESEARCH AND DEVELOPMENT (CR&D) Delivery Order 0055: Molecular Dynamics Modeling Support

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