Relevant bibliographies by topics / Aircraft panel

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Aircraft panel'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Aircraft panel"

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Chenxi, L. I., H. U. Ying, and H. E. Liyan. "Exploration and optimization on the usage of micro-perforated panels as trim panels in commercial aircrafts." Noise Control Engineering Journal 68, no. 1 (2020): 87–100. http://dx.doi.org/10.3397/1/37687.

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Micro-perforated panels (MPPs), as an alternative to porous materials for sound absorption, have been commonly used in electronic industries and aircraft engines but are barely used in aircraft cabins. The effect of MPPs on the sound insulation and absorption properties of aircraft cabin panels has been investigated in this article. Theoretical modeling has been conducted on an aircraft cabin panel structure with a trim panel replaced by an MPP trim panel, using the transfer matrix method and the classic MPP theory. It is indicated by the theoretical results that, although the sound transmissi
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Zhang, Li, Kai Xiang Li, and Xia Sheng Sun. "Study of Piezoelectric Vibration Damping Based on the SSDI Technology for Aircraft Panels." Applied Mechanics and Materials 422 (September 2013): 105–12. http://dx.doi.org/10.4028/www.scientific.net/amm.422.105.

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In this paper, the typical aircraft panel is excited by the noise induced in traveling wave tube, the vibratory phenomenon of the typical aircraft panel is researched in detail. The piezoelectric vibration of the aircraft panels is damped by Synchronized Switch Damping on Inductor technology (SSDI technology). The acceleration parameters of the structure are controlled and the effect of structural damping is achieved.
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Anonymous. "Panel to allocate aircraft time." Eos, Transactions American Geophysical Union 69, no. 51 (1988): 1652. http://dx.doi.org/10.1029/eo069i051p01652-06.

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Sanchez-Carmona, Alejandro, and Cristina Cuerno-Rejado. "Composite stiffened panel sizing for conceptual tail design." Aircraft Engineering and Aerospace Technology 90, no. 8 (2018): 1272–81. http://dx.doi.org/10.1108/aeat-05-2017-0129.

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Purpose A conceptual design method for composite material stiffened panels used in aircraft tail structures and unmanned aircraft has been developed to bear compression and shear loads. Design/methodology/approach The method is based on classical laminated theory to fulfil the requirement of building a fast design tool, necessary for this preliminary stage. The design criterion is local and global buckling happen at the same time. In addition, it is considered that the panel does not fail due to crippling, stiffeners column buckling or other manufacturing restrictions. The final geometry is de
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TUDOSIE, Alexandru Nicolae. "CONTROL LAWS FOR AN AIRCRAFT SUPERSONIC INLET WITH MOBILE PANEL." SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE 19, no. 1 (2017): 231–42. http://dx.doi.org/10.19062/2247-3173.2017.19.1.26.

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Malinowski, Pawel, Tomasz Wandowski, and Wieslaw Ostachowicz. "Guided Waves for Aircraft Panel Monitoring." Key Engineering Materials 558 (June 2013): 107–15. http://dx.doi.org/10.4028/www.scientific.net/kem.558.107.

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The reported research concerns experimental investigation toward the monitoring of an aircraft panel. Guided wave propagation phenomena were used to obtain information about the state of the monitored structure. A curved aluminium panel with rivets was investigated. Piezoelectric transducer was used to excite guided waves in chosen structural element. The generated signal was amplified before applying it to the transducer in order to ensure measurable amplitude of excited guided waves. Measurement of the wave field was realized using laser scanning vibrometer that registered the velocity respo
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Cervi, B. "Knockout punch [aircraft body panel production]." Engineering & Technology 3, no. 11 (2008): 70–71. http://dx.doi.org/10.1049/et:20081110.

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Li, Xiao Ge, Kai Fu Zhang, and Yuan Li. "The Modeling of Multi-State Deformation in Aircraft Panel Automated Riveting System." Applied Mechanics and Materials 224 (November 2012): 123–27. http://dx.doi.org/10.4028/www.scientific.net/amm.224.123.

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Automatic drilling and riveting process, in order to improve the quality of drilling and riveting aircraft panel deformation are needed for compensation. Due to panels in automatic drilling and riveting process with more posture, therefore, solving panel deformation of plates under more posture is important. This paper establishes aircraft panel in the automatic drilling riveting process multiple posture deformation model. Firstly, simplify the manner of support, locate and clamping between the panel and the splints, supportive of integral panel at each location are calculated using three-mome
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Lu, Cong, Deng-Sheng Huo, and Zi-Yue Wang. "Assembly variation analysis of the aircraft panel in multi-stage assembly process with N-2-1 locating scheme." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 233, no. 19-20 (2019): 6754–73. http://dx.doi.org/10.1177/0954406219869040.

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The flexible aircraft panel parts are easy to deform during the assembly process, the deformation can directly affect the assembly accuracy of the aircraft panel, and further affect the assembly quality of the aircraft fuselage. In order to evaluate the assembly accuracy of the aircraft panel in multi-stage assembly process with N-2-1 locating scheme, this paper proposes an assembly variation analyzing approach, considering the effect of the contact force between the panel skin and the fixture components on the deformation of the panel in the assembly process. The mathematical models are estab
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Ju, Jin San, Xiao Chuan You, Xiu Gen Jiang, and Jin Zhao Zhuang. "Fracture Analysis for Damaged Aircraft Fuselage Using Substructure Method." Advanced Materials Research 33-37 (March 2008): 29–34. http://dx.doi.org/10.4028/www.scientific.net/amr.33-37.29.

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This paper primarily describes the development and application of substructure computational analysis techniques to determine stress intensity factors for the damaged panels subjected to fatigue internal pressure. A program based on substructure analysis technique has been developed for the fracture analysis of curved aircraft panels containing cracks. This program may create whole model which consists of substructure superelements and obtain fracture parameter of the crack by expanding results in superelement automatically. For instance, a typical test curved panel model consists of 7 frames
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Dissertations / Theses on the topic "Aircraft panel"

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Liu, Bilong. "Acoustical Characteristics of Aircraft Panels." Doctoral thesis, Stockholm, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-4102.

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Tarkian, Mehdi, and Zaldivar Tessier Francisco Javier. "Aircraft Parametric 3D Modelling and Panel Code of Analysis for Conceptual Design." Thesis, Linköping University, Department of Management and Engineering, 2007. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-10607.

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<p>Throughout the development of this report there will be a brief explanation of what the actual Aircraft Design Process is and in which stages the methodology that the authors are proposing will be implemented as well as the tools that will interact to produce this methodology.</p><p>The proposed tool will be the first part of a methodology that, according to the authors, by integrating separate tools that are currently used in different stages of the aeronautical design, will promote a decrease in the time frame for the initial stages of the design process.</p><p>The first part of the metho
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Carneal, James P. "Active structural acoustic control of double panel systems including hierarchical control approaches." Diss., Virginia Tech, 1996. http://hdl.handle.net/10919/38017.

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Rudd, Jeffrey Roy. "COMPRESSIVE STRENGTH TO WEIGHT RATIO OPTIMIZATION OF COMPOSITE HONEYCOMB THROUGH ADDITION OF INTERNAL REINFORCEMENTS." University of Akron / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=akron1145900147.

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Lynch, Colum James. "A finite element study of the postbuckling behaviour of a typical aircraft fuselage panel." Thesis, Queen's University Belfast, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.343003.

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Harper, Christopher K. 1978. "Correction of pseudo-attitude information and partial panel flight test in general aviation aircraft." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/89356.

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Mahnken, Brian W. "Active structural acoustic control of aircraft interior flow noise via the use of active trim panels." Thesis, This resource online, 1996. http://scholar.lib.vt.edu/theses/available/etd-11012008-063701/.

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Giblette, Ted N. "Rapid Prediction of Low-Boom and Aerodynamic Performance of Supersonic Transport Aircraft Using Panel Methods." DigitalCommons@USU, 2019. https://digitalcommons.usu.edu/etd/7603.

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The Utah State University Aerolab developed and tested a set of tools for rapid prediction of the loudness of a sonic boom generated by supersonic transport aircraft. This work supported a larger effort led by Texas A&M to investigate the use of adaptive aerostructures in lowering sonic boom loudness at off design conditions. Successful completion of this effort will improve the feasibility of supersonic commercial transport over land. Funding was provided by a NASA University Leadership Initiative grant to several universities, including Utah State University, as well as industry partners to
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Ling, Yu. "Nonlinear Response of a Skin Panel under Combined Thermal and Structural Loading." Miami University / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=miami1344731818.

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Guillermo-Monedero, Daniel. "A Comparison of Euler Finite Volume and Supersonic Vortex Lattice Methods used during the Conceptual Design Phase of Supersonic Delta Wings." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1576713976622162.

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Books on the topic "Aircraft panel"

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Seemann, Ralf. A Virtual Testing Approach for Honeycomb Sandwich Panel Joints in Aircraft Interior. Springer Berlin Heidelberg, 2020. http://dx.doi.org/10.1007/978-3-662-60276-8.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Report of the Fluid Dynamics Panel Working Group 11 rotary-balance testing for aircraft dynamics. AGARD, 1991.

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Hoeg, J. G. Technical evaluation report on the Flight Mechanics Panel symposium on aircraft ship operations. Agard, 1992.

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Development, North Atlantic Treaty Organization Advisory Group for Aerospace Research and. Composite repair of military aircraft structures: Papers presented at the 79th Meeting of the AGARD Structures and Materials Panel, held in Seville, Spain 3-5 October 1994. AGARD, 1995.

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Development, North Atlantic Treaty Organization Advisory Group for Aerospace Research and. Fuels and combustion technology for advanced aircraft engines: Papers presented at the Propulsion and Energetics Panel 81st Symposium held in Fiuggi, Italy, 19th-14th May 1993. AGARD, 1993.

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Ko, William L. Thermostructural behavior of a hypersonic aircraft sandwich panel subjected to heating on one side. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1997.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Combat automation for airborne weapon systems: man/machine interface trends and technologies: Copies of papers presented at the joint Flight Mechanics Panel and Guidance and Control Panel Symposium, held in Edinburgh, Scotland, United Kingdom from 19th-22nd October 1992. AGARD, 1993.

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Rotary-balance testing for aircraft dynamics: Report of the Fluid Dynamics Panel Working Group 11. AGARD, 1990.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Improvement of combat performance for existing and future aircraft: Papers presented at the Flight Mechanics Panel Symposium held in Istrana AFB, Treviso, Italy, from 14 to 17 April 1986. AGARD, 1986.

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Eckford, Duncan J. Aircraft operations on repaired runways: Report of Working Group 22 of the Structures and Materials Panel. AGARD, 1990.

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Book chapters on the topic "Aircraft panel"

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van Wijngaarden, Martijn. "Flat and Curved Panel Manufacturing." In Smart Intelligent Aircraft Structures (SARISTU). Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_30.

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Breuer, Ulf Paul. "Tailored Wing Design and Panel Case Study." In Commercial Aircraft Composite Technology. Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-31918-6_8.

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Baschke, Manuel, and Delf Sachau. "Adaptive Support of an Aircraft Panel." In Shock & Vibration, Aircraft/Aerospace, and Energy Harvesting, Volume 9. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-15233-2_8.

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Güemes, Alfredo, Julian Sierra, Frank Grooteman, et al. "Methodologies for the Damage Detection Based on Fiber-Optic Sensors. Applications to the Fuselage Panel and Lower Wing Panel." In Smart Intelligent Aircraft Structures (SARISTU). Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_19.

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Bach, Martin, Nicolas Dobmann, and Maria Moix-Bonet. "Damage Introduction, Detection, and Assessment at CFRP Door Surrounding Panel." In Smart Intelligent Aircraft Structures (SARISTU). Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_52.

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Sasal, Feride Nur, Aysun Dogangun Akın, Ayhan Kılıc, et al. "Manufacturing of Nano-treated Lower Panel Demonstrators for Aircraft Fuselage." In Smart Intelligent Aircraft Structures (SARISTU). Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_55.

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Wyen, Travis A., Joshua J. Schoettelkotte, Ricardo A. Perez, and Thomas G. Eason. "Experimental Modal Analysis of an Aircraft Fuselage Panel." In Shock & Vibration, Aircraft/Aerospace, Energy Harvesting, Acoustics & Optics, Volume 9. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-54735-0_17.

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Premalatha, K. R. Srilatha, and Vidyadhar Y. Mudkavi. "Analysis of Propeller by Panel Method for Transport Aircraft." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-9601-8_34.

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Seemann, Ralf. "Development of novel sandwich panel joints." In A Virtual Testing Approach for Honeycomb Sandwich Panel Joints in Aircraft Interior. Springer Berlin Heidelberg, 2019. http://dx.doi.org/10.1007/978-3-662-60276-8_8.

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Altkvist, Christina, Jonas Wahlbäck, Juergen Tauchner, and Christoph Breu. "Design and Manufacturing of WP135 Side Panel for Validation of Electrical Structure Network (ESN) Technologies." In Smart Intelligent Aircraft Structures (SARISTU). Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-22413-8_56.

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Conference papers on the topic "Aircraft panel"

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Hirsch, S. M., and J. Q. Sun. "Active Segmented Trim Panels for Aircraft Interior Noise Control: Theory and Experiments." In ASME 1999 Design Engineering Technical Conferences. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/detc99/vib-8112.

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Abstract An active segmented trim panel for use as a secondary source for noise control in aircraft is designed, analyzed and tested. It consists of a rectangular segment of aircraft trim panel which is suspended by a flexible support. This support converts the stiff composite trim panel into flexibly-mounted pistons which can be driven by light-weight and low-profile force actuators. The active segmented trim panel offers an acoustic source of lower profile and lower mass, and requires only a simple modification of materials already installed on aircraft. This paper presents a summary of rece
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HAJELA, P., and R. GLOWASKY. "Application of piezoelectric elements in supersonic panel flutter suppression." In Aircraft Design and Operations Meeting. American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-3191.

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Gerner, Christian, Delf Sachau, and Harald Breitbach. "Aircraft interior ANC with flat panel speakers." In Smart Structures and Materials, edited by Eric H. Anderson. SPIE, 2004. http://dx.doi.org/10.1117/12.538623.

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Henry, James K., and Robert L. Clark. "Smart aircraft panels: the effects of internal pressure loading on panel dynamics." In 1999 Symposium on Smart Structures and Materials, edited by Norman M. Wereley. SPIE, 1999. http://dx.doi.org/10.1117/12.350772.

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Taki, Toshimi, and Tomohiro Kitagawa. "Postbuckling strength of composite stiffened panel under shear load." In Aircraft Engineering, Technology, and Operations Congress. American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-3934.

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da Rocha, Joana, Afzal Suleman, and Fernando Lau. "Prediction of Turbulent Flow-Induced Noise in Aircraft Cabins." In ASME 2010 International Mechanical Engineering Congress and Exposition. ASMEDC, 2010. http://dx.doi.org/10.1115/imece2010-39231.

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Flow-induced noise in aircraft cabins can be predicted through analytical models or numerical methods. However, the analytical methods existent nowadays were obtained for simple structures and cabins, in which, usually, a single panel is excited by the turbulent flow, and coupled with an acoustic enclosure. This paper discusses the development of analytical models for the prediction of aircraft cabin noise induced by the external turbulent boundary layer (TBL). The coupled structural-acoustic analytical model is developed using the contribution of both structural and acoustic natural modes. Wh
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Hahn, Andrew, and Rob McDonald. "Geometry Needs of Conceptual Aircraft Design - Panel Discussion." In 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-662.

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"Aircraft interior noise control by anisotropic trim panel." In 15th Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-4379.

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Aydin, Enes, and Altan Kayran. "Comparative Study of Post-Buckling Load Redistribution in Stiffened Aircraft Panel With and Without Material Nonlinearity." In ASME 2018 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/imece2018-86346.

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In this article, a comparative study is presented on the post-buckling load redistribution in stiffened aircraft panels modeled with and without material nonlinearity. In the first part of the study, a baseline stiffened panel is generated for further investigation of the material nonlinearity on the post-buckling behavior and on the effective width of the stiffened panel. In this respect, a stiffener section which provides classical clamped edge condition is designed by matching the compression buckling coefficient determined by the finite element analysis closely with the analytically determ
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Pai, P. F., Byeong-Seok Kim, and Jaycee H. Chung. "Dynamics-based damage inspection of an aircraft wing panel." In NDE for Health Monitoring and Diagnostics, edited by Andrew L. Gyekenyesi and Peter J. Shull. SPIE, 2003. http://dx.doi.org/10.1117/12.484111.

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Reports on the topic "Aircraft panel"

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Doyle, Jesse D., Nolan R. Hoffman, and M. Kelvin Taylor. Aircraft Arrestor System Panel Joint Improvement. U.S. Army Engineer Research and Development Center, 2021. http://dx.doi.org/10.21079/11681/41342.

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Aircraft Arresting Systems (AAS) for military applications utilize sacrificial panels made of Ultra-High Molecular Weight polyethylene (UHMWPE) that are embedded into the pavement beneath the AAS cable to protect the pavement from cable damage. Problems have been observed with the materials and practices used to seal the UHMWPE panel joints from water and debris. Data obtained from laboratory and field studies were used make improvements to current practice for sealing UHMWPE panel joints. The study evaluated four joint-sealant materials, eight alternative surface treatment and preparation tec
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Bly, Peter. Development of expedient ultra-high molecular weight aircraft arresting system panel installation procedures. Engineer Research and Development Center (U.S.), 2020. http://dx.doi.org/10.21079/11681/37536.

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Brown, E. R. Evaluation of Ultra High Molecular Weight (UHMW) Polyethylene Panels for Aircraft Arresting Systems. Defense Technical Information Center, 2009. http://dx.doi.org/10.21236/ada508608.

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Del Grande, N. K., K. W. Dolan, P. F. Durbin, M. R. Gorvad, and A. B. Shapiro. Dual-band infrared (DBIR) imaging inspections of Boeing 737 and KC-135 aircraft panels. Office of Scientific and Technical Information (OSTI), 1993. http://dx.doi.org/10.2172/10117407.

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