Relevant bibliographies by topics / Composite wing rib post

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Conference papers

Academic literature on the topic 'Composite wing rib post'

Author: Grafiati
Published: 4 June 2021
Last updated: 17 February 2022

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Journal articles on the topic "Composite wing rib post"

1

Hu, Zheng, and Olexii Vambol. "TOPOLOGICAL DESIGNING AND ANALYSIS OF THE COMPOSITE WING RIB." Aerospace technic and technology, no. 6 (November 27, 2020): 4–14. http://dx.doi.org/10.32620/aktt.2020.6.01.

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The composite structures in the aerospace industry for in recent decades are widely applied however, at the beginning of the 21st century composites are growing rapidly. The largest companies in the aerospace industry are increasing the volume of composites application of in the structures, and nowadays the volume of composites reaches 50%. The different elements of aircraft and even highly loaded structures such as spars, ribs, skin, etc., are currently made from composites. First of all, this is due to the possibility of a significant reduction in the weight of the structure, as well as a de
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Yang, Kang, Yi-lin Guo, Dong-hui Li, et al. "Design and static testing of wing structure of a composite four-seater electric aircraft." Science and Engineering of Composite Materials 27, no. 1 (2020): 258–63. http://dx.doi.org/10.1515/secm-2020-0023.

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AbstractBecause of its light weight, high strength, designable, composite materials are more and more widely used in the field of aerospace, especially in the field of general aviation. In this paper, the structural design and analysis of the composite wing (include wing beam, rib, skin, leading edge and trailing edge) of a four-seater electric aircraft were carried out. The finite element numerical analysis model of the composite wing was established, and the deformation and strain distribution of the composite wing under the limited load required by airworthiness regulations were calculated.
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Yang, Kang, Liguo Zhang, Shude Ji, Yumei Yue, and Wang Ji. "Static Testing and Analysis of Composite Wing of a Two-Seater Aircraft Powered by Li-Ion Battery Electric Propulsion." Advanced Composites Letters 25, no. 6 (2016): 096369351602500. http://dx.doi.org/10.1177/096369351602500601.

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The present paper studied the strength and deformation characteristics of a composite wing of a two-seater aircraft powered by Li-ion battery electric propulsion. In order to get the airworthiness certificate, the static testing is indispensable. The primary wing structure component includes upper and lower skins, leading edge, trailing edge, a root rib and main spar. The main purpose of static testing is to examine the bending strength of the wing. The testing results are in good agreement with the FE analysis results and the bending strength of wing is strong enough to support the limit load
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Гребеников, А. Г., Ю. В. Дьяченко, В. В. Коллеров, И. В. Малков, Н. И. Москаленко та В. А. Урбанович. "КОНСТРУКТИВНО-ТЕХНОЛОГІЧНІ ОСОБЛИВОСТІ НЕСУЧИХ ПОВЕРХОНЬ ВЕРТОЛЬОТА З ПОЛІМЕРНИХ КОМПОЗИЦІЙНИХ МА-ТЕРІАЛІВ". Open Information and Computer Integrated Technologies, № 84 (2 липня 2019): 4–49. http://dx.doi.org/10.32620/oikit.2019.84.01.

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The analysis of both foreign and domestic experience in the use of polymer composite materials in the structures of the lifting surfaces of a helicopter (blades, wing, stabilizer, fin), as well as the technological features of the manufacture of such structures is performed. The design and technological and operational advantages and disadvantages of composite blades compared to all-metal blades are noted. The load-carrying structures of the composite main rotor blades of a helicopter, as well as the schemes of special joints of the MR blade and the polymer composite materials package are cons
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Krupa, Eduardo P., Jonathan E. Cooper, Alberto Pirrera, and Raj Nangia. "Improved aerostructural performance via aeroservoelastic tailoring of a composite wing." Aeronautical Journal 122, no. 1255 (2018): 1442–74. http://dx.doi.org/10.1017/aer.2018.66.

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ABSTRACTThis paper investigates the synergies and trade-offs between passive aeroelastic tailoring and adaptive aeroelastic deformation of a transport composite wing for fuel burn minimisation. This goal is achieved by optimising thickness and stiffness distributions of constitutive laminates, jig-twist shape and distributed control surface deflections through different segments of a nominal “cruise-climb” mission. Enhanced aerostructural efficiency is sought both passively and adaptively as a means of aerodynamic load redistribution, which, in turn, is used for manoeuvre load relief and minim
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Gantois, K., and A. J. Morris. "Incorporation of manufacturing information into an MDO environment." Aeronautical Journal 103, no. 1026 (1999): 383–88. http://dx.doi.org/10.1017/s0001924000064605.

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Abstract The Paper describes a metal and composite recurrent cost model of a large civil aircraft wing structure for a multidisciplinary design, analysis and optimisation (MDO) environment. The work was part of a recent European MDO project (BE95-2056) which investigated methods for the integration of structures, aerodynamics, dynamics and manufacturing cost at the preliminary design stage. The paper discusses the cost modelling approach, which is based on parametric and process cost model methods, and the integration of the cost models into an MDO process. Results for the cost models are show
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Goonewardene, L. A., M. A. Price, M. F. Liu, R. T. Berg, and C. M. Erichsen. "A study of growth and carcass traits in dehorned and polled composite bulls." Canadian Journal of Animal Science 79, no. 3 (1999): 383–85. http://dx.doi.org/10.4141/a98-121.

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Phenotypically dehorned (genetically horned) and polled bulls were similar for birth, weaning weight, pre- and post-weaning ADG, carcass weight, grade fat, marbling, rib-eye area, cutability and carcass grade. Polled bulls had higher (P < 0.02) fat over the rib-eye compared with dehorned. The similarity in growth and a majority of carcass traits between polled and horned, would suggest that breeding for polledness may be recommended to eliminate horns. Key words: Dehorned, polled, growth, carcass traits, bulls
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8

Sivakumar, V., Khooshboo P. Dani, and Suddapally Sriram. "Prediction of Stress Intensity Factor on Precracked Composite Wing Rib Made up of Carbon-Epoxy IM7-8552." Journal of Failure Analysis and Prevention 16, no. 4 (2016): 635–46. http://dx.doi.org/10.1007/s11668-016-0130-1.

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Breen, John E., Michael E. Kreger, Christopher D. White, and Gordon C. Clark. "Field evaluation and model test of a composite wing-girder bridge." Canadian Journal of Civil Engineering 14, no. 6 (1987): 753–62. http://dx.doi.org/10.1139/l87-113.

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This paper presents the key observations and conclusions from the evaluation of an innovative "loose-fit" composite, post-tensioned concrete wing-girder bridge proposed for an elevated interstate highway expansion in an urban environment. The evaluation program included both testing to destruction of a 1/2-scale model of a partial span as well as construction monitoring and field testing at service load levels of a full-scale prototype two-span bridge. Results of both construction measurements and loading tests were compared with analytical predictions. Laboratory tests showed the composite be
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10

Latif, R. F., M. K. A. Khan, A. Javed, S. I. A. Shah, and S. T. I. Rizvi. "A semi-analytical approach for flutter analysis of a high-aspect-ratio wing." Aeronautical Journal 125, no. 1284 (2020): 410–29. http://dx.doi.org/10.1017/aer.2020.71.

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AbstractWe present a hybrid, semi-analytical approach to perform an eigenvalue-based flutter analysis of an Unmanned Aerial Vehicle (UAV) wing. The wing has a modern design that integrates metal and composite structures. The stiffness and natural frequency of the wing are calculated using a Finite Element (FE) model. The modal parameters are extracted by applying a recursive technique to the Lanczos method in the FE model. Subsequently, the modal parameters are used to evaluate the flutter boundaries in an analytical model based on the p-method. Two-degree-of-freedom bending and torsional flut
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Dissertations / Theses on the topic "Composite wing rib post"

1

Harman, David Edward. "An economic evaluation of the robotic tufting process considering the application of a novel composite wing rib post." Thesis, University of Plymouth, 2013. http://hdl.handle.net/10026.1/10847.

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This thesis aims to establish a greater understanding of the effects of the single-sided robotic tufting process on component manufacturing costs and weight, and subsequently determine whether potential economic benefits can be realised through its implementation. To complete this assessment, the study uses the novel composite rib post application of the Next Generation Composite Wing (NGCW) project as an example case, investigating the component’s manufacturing cost, performance and weight relative to those of a non-tufted rib post with the same initial fabric layup, and a prepreg rib post wi
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Swanson, Gary D. "Structural efficiency study of composite wing rib structures." Thesis, This resource online, 1987. http://scholar.lib.vt.edu/theses/available/etd-04292010-020010/.

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Books on the topic "Composite wing rib post"

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Zafer, Gürdal, Starnes James H, Langley Research Center. Structural Mechanics Branch., and NASA-Virginia Tech Composites Program, eds. Structural efficiency study of composite wing rib structures. Structural Mechanics Branch, National Aeronautics and Space Administration, Langley Research Center, 1988.

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Conference papers on the topic "Composite wing rib post"

1

Sofla, A. Y. N., S. A. Meguid, and K. T. Tan. "Novel Morphing Wing Design Using Antagonistic Shape Memory Alloy Actuation." In ASME 2010 International Mechanical Engineering Congress and Exposition. ASMEDC, 2010. http://dx.doi.org/10.1115/imece2010-38851.

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A wing shear concept is adopted here to design and fabricate morphing wing for an unmanned aerial vehicle. The concept uses a parallelogram wing-box that consists of several composite rib shells that are hinged to two active spars. Antagonistic shape memory actuation is used to flex the spars and consequently shape morph the wing between straight and curved shapes.
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2

Sunuwar, Nitam, and Jung-Ryul Lee. "Wave Rich Laser Ultrasonic Wavenumber Imaging for Laser Ultrasonic Propagation Imaging System With Air-Coupled Transducer." In ASME 2013 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/smasis2013-3088.

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Interest in ultrasonic guided wave based Structural Health Monitoring and a nondestructive evaluation system has grown in recent years, especially to monitor thin plate like structures. However, an effective signal processing and imaging algorithms are essential to achieve necessary performance. This paper describes wave rich laser ultrasonic wavenumber imaging method (UWI) method for damage visualization. Ultrasonic waves were generated by a scanning laser source and acquired using a capacitance air coupled transducer (ACT). However, the inherent existence of multiple Lamb wave modes in signa
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