Response of composite plates with inclined elliptical notches and subjected to axial compression

Ambur, Damodar R.; McGowan, David M.

doi:10.2514/6.1999-1276

Cited by 6 publications

(3 citation statements)

References 7 publications

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“…The STAGS post-buckling capability was used on bladestiffened and PRSEUS panels. 1,[3][4][5][6][7][8][9][11][12][13][1][2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18]20 Examples of these specimens are shown in Fig. 6 …”

Section: A Predicting Post-bucking Behaviormentioning

confidence: 99%

“…Buckling analyses are typically conducted on compression-loaded specimens to determine the bifurcation buckling load and initial mode shape but nonlinear analysis is often required to determine how much load the structure will carry and quantify its post-buckling behavior since stitched structure has demonstrated an ability to support load beyond buckling. 4,6,[11][12][13][14][15][16][17][18][19][20] Nonlinear analysis can be conducted until collapse is reached and this result is compared to test data.…”

Section: Modeling and Analyzing Stitched Structures In Stagsmentioning

confidence: 99%

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The Use of the STAGS Finite Element Code in Stitched Structures Development

Jegley

Lovejoy

2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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In the last 30 years NASA has worked in collaboration with industry to develop enabling technologies needed to make aircraft more fuel-efficient and more affordable. The focus on the airframe has been to reduce weight, improve damage tolerance and better understand structural behavior under realistic flight and ground loading conditions. Stitched structure is a technology that can address the weight savings, cost reduction, and damage tolerance goals, but only if it is supported by accurate analytical techniques. Development of stitched technology began in the 1990's as a partnership between NASA and Boeing (McDonnell Douglas at the time) under the Advanced Composites Technology Program and has continued under various titles and programs and into the Environmentally Responsible Aviation Project today.These programs contained development efforts involving manufacturing development, design, detailed analysis, and testing. Each phase of development, from coupons to large aircraft components was supported by detailed analysis to prove that the behavior of these structures was well-understood and predictable. The Structural Analysis of General Shells (STAGS) computer code was a critical tool used in the development of many stitched structures. As a key developer of STAGS, Charles Rankin's contribution to the programs was quite significant. Key features of STAGS used in these analyses and discussed in this paper include its accurate nonlinear and post-buckling capabilities, its ability to predict damage growth, and the use of Lagrange constraints and follower forces.

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Section: A Predicting Post-bucking Behaviormentioning

confidence: 99%

Section: Modeling and Analyzing Stitched Structures In Stagsmentioning

confidence: 99%

The Use of the STAGS Finite Element Code in Stitched Structures Development

Jegley

Lovejoy

2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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“…where is the applied stress and is the load angle. Different forms of functions f 1 and f 2 were introduced [3,12] for evaluating the stress function F and stress components. In order to avoid unnecessary lengthiness, in the framework of linear anisotropic elasticity, a complex stress function F similar the one presented by Daost and Hoa [3] is used in this study.…”

Section: Basic Relationsmentioning

confidence: 99%

Stress Analysis of Composite Plates with a Quasi-Square Cutout Subjected to Uniaxial Tension

Rezaeepazhand

Jafari

2009

Journal of Reinforced Plastics and Composites

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Perforated plates and shells with variously shaped cutout are often used in engineering structures. Despite the importance of the effects of cutout on the load-bearing capacity and stress concentration of such plates little research has focused on stress analysis of plates with special shaped cutout. This study investigates problems associated with the maximum stresses in perforated composite plates with quasi-square shaped cutouts. Analytical solution based on Lekhnitskii’s theory of anisotropic plate is utilized for stress analysis of composite plates with central square shaped cutout. The solution is capable of considering large variety of cutout shapes and loading conditions analytically. Parametric studies were conducted to investigate the effects of variation in cutout bluntness and orientation, material properties, and loading direction on the location and the value of the maximum stress in a flat composite plate subjected uni-axial tension load. Based on results presented herein, the maximum normalized stress of perforated composite plates can be significantly changed by using proper combination of material properties, fiber orientation, loading angle, cutout bluntness, and orientation.

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Techniques for Damage Tolerance and Structural Integrity of Composite Structures

Razi

Ambur

2010

Encyclopedia of Aerospace Engineering

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This section discusses the importance of damage tolerance and how different damage conditions are addressed in the structural design process to assure structural integrity and safety of composite aircraft structures. The regulatory requirements from the Federal Aviation Regulations (FAR) and Joint Aviation Regulations (JAR) for damage‐tolerant design of aircraft structures are presented. Analysis and testing methods used for validation and certification are also summarized.

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Response of composite plates with inclined elliptical notches and subjected to axial compression

Cited by 6 publications

References 7 publications

The Use of the STAGS Finite Element Code in Stitched Structures Development

The Use of the STAGS Finite Element Code in Stitched Structures Development

Stress Analysis of Composite Plates with a Quasi-Square Cutout Subjected to Uniaxial Tension

Techniques for Damage Tolerance and Structural Integrity of Composite Structures

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