Skip to main content Accessibility help
×
Home
Hostname: page-component-564cf476b6-lwxm7 Total loading time: 0.294 Render date: 2021-06-20T17:31:33.679Z Has data issue: true Feature Flags: { "shouldUseShareProductTool": true, "shouldUseHypothesis": true, "isUnsiloEnabled": true, "metricsAbstractViews": false, "figures": true, "newCiteModal": false, "newCitedByModal": true, "newEcommerce": true }

Predictive analysis of stitched aerospace structures for advanced aircraft

Published online by Cambridge University Press:  18 November 2019

B. Horton
Affiliation:
CRashworthiness for Aerospace Structures and Hybrids (CRASH) Lab, Department of Mechanical and Aerospace Engineering, University at Buffalo - The State University of New York, Buffalo, NYUSA
Y. Song
Affiliation:
CRashworthiness for Aerospace Structures and Hybrids (CRASH) Lab, Department of Mechanical and Aerospace Engineering, University at Buffalo - The State University of New York, Buffalo, NYUSA
D. Jegley
Affiliation:
Structural Mechanics and Concepts Branch, NASA Langley Research Center, Hampton, VAUSA
F. Collier
Affiliation:
Environmentally Responsible Aviation Project of the Aeronautics Research Mission Directorate, NASA Langley Research Center, Hampton, VAUSA
J. Bayandor
Affiliation:
CRashworthiness for Aerospace Structures and Hybrids (CRASH) Lab, Department of Mechanical and Aerospace Engineering, University at Buffalo - The State University of New York, Buffalo, NYUSA
Corresponding
E-mail address:

Abstract

In recent years, the aviation industry has taken a leading role in the integration of composite structures to develop lighter and more fuel efficient aircraft. Among the leading concepts to achieve this goal is the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept. The focus of most PRSEUS studies has been on developing an hybrid wing body structure, with only a few discussing the application of PRSEUS to a tube-wing fuselage structure. Additionally, the majority of investigations for PRSEUS have focused on experimental validation of anticipated benefits rather than developing a methodology to capture the behavior of stitched structure analytically. This paper presents an overview of a numerical methodology capable of accurately describing PRSEUS’ construction and how it may be implemented in a barrel fuselage platform resorting to high-fidelity mesoscale modeling techniques. The methodology benefits from fresh user defined strategies developed in a commercially available finite element analysis environment. It further proposes a new approach for improving the ability to predict deformation in stitched composites, allowing for a better understanding of the intricate behavior and subtleties of stitched aerospace structures.

Type
Research Article
Copyright
© Royal Aeronautical Society 2019 

Access options

Get access to the full version of this content by using one of the access options below.

Footnotes

A version of this paper was presented at the 31st ICAS Congress of the International Council of the Aeronautical Sciences in Belo Horizonte, Brazil in September 2018.

References

Pagano, N.J. and Pipes, R.B. Some observations on the interlaminar strength of composite laminates, International Journal of Mechanical Sciences, 1973, 15, (8), pp 679686. doi: 10.1016/0020-7403(73)90099-4.CrossRefGoogle Scholar
Cui, W. and Wisnom, M.R. A combined stress-based and fracture-mechanics-based model for predicting delamination in composites, Composites, 1993, 24, (6), pp 467474. doi: 10.1016/0010-4361(93)90016-2.CrossRefGoogle Scholar
Pinho, S., Darvizeh, R., Robinson, P., Schuecker, C. and Camanho, P. Material and structural response of polymer-matrix fibre-reinforced composites, Journal of Composite Materials, 2012, 46, pp 23132341. doi: 10.1177/0021998312454478.CrossRefGoogle Scholar
Talreja, R. Assessment of the fundamentals of failure theories for composite materials, Composites Science and Technology, 2014, 105, pp 190201. doi: 10.1016/j.compsrefch.2014.10.014.CrossRefGoogle Scholar
Forghani, A., Zobeiry, N., Poursartip, A. and Vaziri, R. A structural modelling framework for prediction of damage development and failure of composite laminates, Journal of Composite Materials, 2013, 47, pp 25532573. doi: 10.1177/0021998312474044.CrossRefGoogle Scholar
Lee, C.-S., Kim, J.-H., Kim, S., Ryu, D.-M. and Lee, J.-M. Initial and progressive failure analyses for composite laminates using puck failure criterion and damage-coupled finite element method, Composite Structures, 2015, 121, pp 406419. doi: 10.1016/j.compstruct.2014.11.011.CrossRefGoogle Scholar
Velicki, A. Damage Arresting Composites for Shaped Vehicles - Phase I Final Report, NASA/CR-2009-215932, Hampton, Virginia, 2009.Google Scholar
Lovejoy, A.E. and Leone, F.A. T-Cap Pull-Off and Bending Behavior for Stitched Structure, NASA/TM-2016-218971, Hampton, Virginia, 2016.Google Scholar
Jegley, D.C., Rouse, M., Przekop, A. and Lovejoy, A.E. Testing of a Stitched Composite Large-Scale Pressure Box, 57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, San Diego, California, 2016. doi: 10.2514/6.2016-2175.CrossRefGoogle Scholar
Jegley, D.C. The influence of restraint systems on panel behavior, Proceedings of 2011 Annual Conference on Experimental and Applied MechanicsSpringer, New York, NY, 2011, pp. 477–486, 2011. doi: 10.1007/978-1-4614-0222-0_58.CrossRefGoogle Scholar
Leone, F.A. Compressive Testing of Stitched Frame and Stringer Alternate Configurations, NASA/TM-2016-218974, Hampton, Virginia, 2016.Google Scholar
Jegley, D.C. and Velicki, A. Status of Advanced Stitched Unitized Composite Aircraft Structures, 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Grapevine, Texas, 2013. doi: 10.2514/6.2013-410.CrossRefGoogle Scholar
Vectran, Grasp the World of Tomorrow: Engineering Data, Kuraray America, Inc., Charlotte, NC, 1999.Google Scholar
Gower, H.L., Cronin, D.S. and Plumtree, A. Ballistic impact response of laminated composite panels, International Journal of Impact Engineering, 2008, 35, (9), pp 10001008. doi: 10.1016/j.ijimpeng.2007.07.007.CrossRefGoogle Scholar
Hoof, J. Van Maodelling of Impact Induced Delamination in Composite Materials, Dissertation, Carleton University Ottawa, 1999.Google Scholar
Matzenmiller, A., Lubliner, J. and Taylor, R.L. A constitutive model for anisotropic damage in fiber-composites, Mechanics of Materials, 1995, 20, (2), pp 125152. doi: 10.1016/0167-6636(94)00053-0.CrossRefGoogle Scholar
Behl, S., Joshi, R., Mehlig, N., Ali, K., Surti, T., Kim, D. and Tamijani, A. On the Study of PRSEUS - Structural Integrity and Wing Design for General Aviation Aircraft, 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Kissimmee, Florida, 2015. doi: 10.2514/6.2015-1872.CrossRefGoogle Scholar
Bergan, A.C. Test and Analysis of Stitched Composite Structures to Assess Damage Containment Capability, Dissertation, Drexel University, Philadelphia, PA, 2014.Google Scholar
Przekop, A., Jegley, D.C., Rouse, M. and Lovejoy, A.E. Finite Element Analysis and Test Results Comparison for the Hybrid Wing Body Center Section Test Article, NASA/TM-2016-218973, Hampton, Virginia, 2016.Google Scholar
Yovanof, N. and Jegley, D. Compressive Behavior of Frame-Stiffened Composite Panels, 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Denver, Colorado, pp 1–15, 2011. doi: 10.2514/6.2011-1913.CrossRefGoogle Scholar
Chang, F.-K. and Chang, K.-Y. A progressive damage model for laminated composites containing stress concentrations, Journal of Composite Materials, 1987, 21, pp 834855. doi: 10.1177/002199838702100904.CrossRefGoogle Scholar
Hallquist, J.O. LS-DYNA Theory Manual, Livermore Software Technology Corporation (LSTC), Livermore, CA, 2015.Google Scholar
Lemmen, P., Meijer, G.-J. and Rasmussen, E.A. Dynamic Behaviour of Composite Ship Structures (DYCOSS) - Failure Prediction Tool, 70th Shock and Vibration Symposium, Albuquerque, NM, 1999.Google Scholar
Horton, B. Comprehensive Multi-Scale Progressive Failure Analysis for Damage Arresting Advanced Aerospace Hybrid Structures, Dissertation, Virginia Tech, 2017.Google Scholar
Horton, B., Song, Y., Jegley, D.C. and Bayandor, J. High-fidelity computational methodology for stitched composite aerospace structures, Program Progress Report, 2018.Google Scholar
Horton, B., Song, Y., Jegley, D. and Bayandor, J. Numerical investigation of stringer-frame intersections for stitched aerospace structures, Program Progress Report, 2018.CrossRefGoogle Scholar
USDOT and FAA, Transport Airplane Cabin Interiors Crashworthiness Handbook, Adv Circ. 25-17A, Washington, DC, 2009.Google Scholar
Horton, B., Song, Y., Jegley, D. and Bayandor, J. Damage arrestment of aerospace stitched composites, Program Progress Report, 2018.Google Scholar
Caprino, G., Lopresto, V. and Santoro, D. Ballistic impact behaviour of stitched graphite/epoxy laminates, Composites Science and Technology, 1987, 67, pp 325335. doi: 10.1016/j.compsrefch.2006.04.015.CrossRefGoogle Scholar

Send article to Kindle

To send this article to your Kindle, first ensure no-reply@cambridge.org is added to your Approved Personal Document E-mail List under your Personal Document Settings on the Manage Your Content and Devices page of your Amazon account. Then enter the ‘name’ part of your Kindle email address below. Find out more about sending to your Kindle. Find out more about sending to your Kindle.

Note you can select to send to either the @free.kindle.com or @kindle.com variations. ‘@free.kindle.com’ emails are free but can only be sent to your device when it is connected to wi-fi. ‘@kindle.com’ emails can be delivered even when you are not connected to wi-fi, but note that service fees apply.

Find out more about the Kindle Personal Document Service.

Predictive analysis of stitched aerospace structures for advanced aircraft
Available formats
×

Send article to Dropbox

To send this article to your Dropbox account, please select one or more formats and confirm that you agree to abide by our usage policies. If this is the first time you use this feature, you will be asked to authorise Cambridge Core to connect with your <service> account. Find out more about sending content to Dropbox.

Predictive analysis of stitched aerospace structures for advanced aircraft
Available formats
×

Send article to Google Drive

To send this article to your Google Drive account, please select one or more formats and confirm that you agree to abide by our usage policies. If this is the first time you use this feature, you will be asked to authorise Cambridge Core to connect with your <service> account. Find out more about sending content to Google Drive.

Predictive analysis of stitched aerospace structures for advanced aircraft
Available formats
×
×

Reply to: Submit a response

Please enter your response.

Your details

Please enter a valid email address.

Conflicting interests

Do you have any conflicting interests? *