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Journal articles on the topic 'Semi-monocoque'

Author: Grafiati

Published: 28 June 2021

Last updated: 29 July 2025

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1

Singhanart, Thanyarat, Kulanun Chutisemachai, Kiatnathee Dilokthonsakun, Jintasarn Sanchai, and Kasemphan Siriployngam. "On the Use of Composite-Steel Joint for Semi-Monocoque Frame Design." Applied Mechanics and Materials 619 (August 2014): 23–27. http://dx.doi.org/10.4028/www.scientific.net/amm.619.23.

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The design of semi-monocoque frame by using the composite-steel joint is considered in this paper. The frame is designed with weight less than 30kg and torsional stiffness more than 1200 Nm/deg. In order to design the semi-monocoque frame, the analysis of the composite-steel joint has to be clearly investigated. Therefore, the stress analysis of composite-steel joint is performed and then the frame is designed. The double lab joint with two holes is tested and verified by the experiments. The carbon-fiber fabric laminated with the KEVLAR fabric composite laminate is used for composite part. Fr

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2

kedarnath, G. "Modelling and Analysis of Aircraft Fuselage Semi monocoque Structure." INTERNATIONAL JOURNAL OF SCIENTIFIC RESEARCH IN ENGINEERING AND MANAGEMENT 09, no. 06 (2025): 1–9. https://doi.org/10.55041/ijsrem49875.

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Abstract - The structural integrity and performance of an aircraft fuselage are critical factors in aerospace engineering. This project focuses on the modelling and analysis of a semi-monocoque aircraft fuselage structure, a widely used design due to its high strength-to-weight ratio and efficient load distribution. The study involves creating a finite element model (FEM) of the fuselage to simulate real-world loading conditions, including aerodynamic forces, internal pressurization, and structural stresses. Various materials and geometries are considered to optimize weight, strength, and dura

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3

Yusuf Kafi, Kafi, Sri Hastuti, and Nani Mulyaningsih. "OPTIMASI KETEBALAN STRUKTUR CHASSIS SEMI-MONOCOQUE BUS LISTRIK MENGGUNAKAN STATIC STRUCTURAL ANALYSIS." JURNAL FOUNDRY 6, no. 2 (2023): 9–19. http://dx.doi.org/10.62944/jf.v6i2.71.

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ABSTRAKPada pengembangan bus listrik medium menggunakan chassis tipe semi-monocoque masih memiliki permasalahan yaitu kelebihan massa pada strukturnya. Chassis merupakan suatu kerangka yang menopang seluruh komponen diatasnya, sehingga chassis harus kuat dan massanya kecil (ringan) untuk meningkatkan efisiensi dari kendaraan. Oleh karena itu untuk mengurangi massa struktur dapat dilakukan optimasi ukuran salah satunya pada ukuran tebal profil chassis kendaraan. Tujuan dari penelitian ini untuk menganalisis pengaruh variasi tebal profil chassis semi-monocoque bus listrik medium terhadap kekuata

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4

Alonso, L., C. Bedoya, B. Lauret, and F. Alonso. "F²TE³: a Transparent Semi-Monocoque VIP Envelope." Applied Mechanics and Materials 71-78 (July 2011): 594–97. http://dx.doi.org/10.4028/www.scientific.net/amm.71-78.594.

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This article examines a new lightweight, slim, high energy efficient, light-transmitting, self-supporting envelope system, providing for seamless, free-form designs for use in architectural projects. The system exploits vacuum insulation panel technology. The research was based on envelope components already existing on the market and patents and prototypes built by independent laboratories, especially components implemented with silica gel insulation, as this is the most effective transparent thermal insulation there is today. The tests run on these materials revealed that there is not one th

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5

Farrow, Ian. "Design, Build and Test of a Semi-Monocoque Wing Structure." International Journal of Mechanical Engineering Education 30, no. 1 (2002): 73–89. http://dx.doi.org/10.7227/ijmee.30.1.7.

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6

K., Ravindranath Tagore Rachumalla Pallavi. "RANDOM VIBRATION ANALYSIS OF SANDWICH COMPOSITE BEAMS." INTERNATIONAL JOURNAL OF ENGINEERING SCIENCES & RESEARCH TECHNOLOGY 5, no. 9 (2016): 769–79. https://doi.org/10.5281/zenodo.155243.

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In this thesis, a sandwich composite for Semi-monocoque construction in aircraft fuselage is analyzed for its strength under different loading conditions using different materials for Stringers balsa wood, syntactic foams, and honeycombs and Carbon Fiber reinforced thermoplastics is used as skin material. 3D modeling is done in Pro/Engineer. Static, Modal and Random Vibration analysis is done on the beam using finite element analysis software Ansys.

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7

Katrňák, Tomáš, Jaroslav Juračka, and Ivo Jebáček. "RESEARCH OF EFFECTS OF DEFECTS ON STABILITY FAILURES OF SEMI-MONOCOQUE STIFFENERS." Aviation 23, no. 3 (2020): 83–90. http://dx.doi.org/10.3846/aviation.2019.11903.

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This article presents further results of the research of effects of model defects on the local buckling of compressed stiffeners in nonlinear finite element (FE) analyses. The main outcomes are confirmation of trends for 10 sets of profile dimensions, final validations of various sets of FE simulations, and designs of practical types of defects with appropriate ratio values. A single node defect and then complex types of defects with alternating distributions of node shifts along one edge, two free flange edges, one flange surface and both flange surfaces are analyzed in this research project.

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8

Dababneh, Odeh, and Altan Kayran. "Design, analysis and optimization of thin walled semi-monocoque wing structures using different structural idealization in the preliminary design phase." International Journal of Structural Integrity 5, no. 3 (2014): 214–26. http://dx.doi.org/10.1108/ijsi-12-2013-0050.

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Purpose – In modeling an aircraft wing, structural idealizations are often employed in hand calculations to simplify the structural analysis. In real applications of structural design, analysis and optimization, finite element methods are used because of the complexity of the geometry, combined and complex loading conditions. The purpose of this paper is to give a comprehensive study on the effect of using different structural idealizations on the design, analysis and optimization of thin walled semi-monocoque wing structures in the preliminary design phase. Design/methodology/approach – In th

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9

Barca, Iga, Marek Rośkowicz, and Jan Godzimirski. "Selection of materials for repairing punctures of metal skin of semi-monocoque structures using composite patches." Technologia i Automatyzacja Montażu 120, no. 2 (2023): 19–32. http://dx.doi.org/10.7862/tiam.2023.2.3.

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For repairing punctures of skin of semi-monocoque structures under field conditions, simple methods are sought to guarantee the reliability of the repaired structure. Therefore, adhesive joints and composite materials are being increasingly used in repairs. During repairs using adhesion, an important aspect that affects the quality of the joint is the selection of the adhesive and the quality of surface preparation of the parts to be joined. This is necessary to get the right bond strength and durability of the joint in working environments characterized by extreme temperatures and exposure to

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10

Webster, J. M., T. Schmidt, and J. Mew. "A Holographic Interferometric Technique for the Detection and Computerized Recognition of Structural Faults in Semi-Monocoque Structures." Imaging Science Journal 46, no. 1 (1998): 16–20. http://dx.doi.org/10.1080/13682199.1998.11736438.

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11

S. Mohamed Ali, J., Hasna Nur Fadhila, Burhani M. Burhani, and Miah Mohammed Riyadh. "Educational Software for Stress Analysis of Idealized Closed Thin Walled Sections." International Journal of Engineering & Technology 7, no. 4.36 (2018): 368. http://dx.doi.org/10.14419/ijet.v7i4.36.28144.

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Aerospace structures are typically semi-monocoque structures that are made up of thin-walled closed section reinforced with stiffeners. Stress analysis of such closed thin-walled structures which are statically indeterminate is tedious and time consuming. An educational software which can aid students in carrying out stress analysis of such idealized thin-walled closed sections has been developed. The software enables students to select different types of wing torsion box sections with stiffeners, which may be subjected to bending, shear or torsional loads and evaluate the resulting stresses o

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12

Niemann, S., B. Kolesnikov, H. Lohse-Busch, et al. "The use of topology optimisation in the conceptual design of next generation lattice composite aircraft fuselage structures." Aeronautical Journal 117, no. 1197 (2013): 1139–54. http://dx.doi.org/10.1017/s0001924000008745.

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Abstract Conventional commercial aircraft fuselages use all-aluminium semi-monocoque structures where the skin carries the external loads, the internal fuselage pressurisation and is strengthen using frames and stringers. Environmental and economic issues force aircraft designers to minimise weight and costs to keep air transport competitive and safe. But as metal designs have reached a high degree of perfection, extraordinary weight and cost savings are unlikely in the future. Carbon composite materials combined with lattice structures and the use of topology optimisation have the potential t

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13

Tsaro, Dii Christian. "Aerodynamics of politics and stability of statecraft in the Nigerian project." African Journal of Social Issues 6, no. 1 (2024): 41–59. http://dx.doi.org/10.4314/ajosi.v6i1.3.

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The study on aerodynamics of politics and stability of statecraft in the Nigerian project sought to explain the stability of statecraft in the Nigerian project from the perspective of aerodynamic stability of an aircraft. The purpose was to examine the stability of statecraft in the Nigerian project from the backdrop of aerodynamic stability of an aircraft in flight. Its adopted methodology was hinged on the conceptual and historical frameworks as well as strategies of inquiry such as grounded theory. The study was anchored on the systems approach theory for its theoretical framework. It estab

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14

Гребеников, А. Г., И. В. Малков, В. А. Урбанович, Н. И. Москаленко та Д. С. Колодийчик. "КОНСТРУКТИВНО-ТЕХНОЛОГІЧНІ ОСОБЛИВОСТІ ХВОСТО-ВИХ БАЛОК СІТЧАСТОГО ТИПУ З ПОЛІМЕРНИХ КОМПО-ЗИЦІЙНИХ МАТЕРІАЛІВ ВЕРТОЛЬОТІВ ТРАНСПОРТНОЇ КАТЕГОРІЇ". Open Information and Computer Integrated Technologies, № 88 (6 листопада 2020): 15–30. http://dx.doi.org/10.32620/oikit.2020.88.02.

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The analysis of the design and technological features of the tail boom (ТB) of a helicopter made of polymer composite materials (PCM) is carried out.Three structural and technological concepts are distinguished - semi-monocoque (reinforced metal structure), monocoque (three-layer structure) and mesh-type structure. The high weight and economic efficiency of mesh structures is shown, which allows them to be used in aerospace engineering. The physicomechanical characteristics of the network structures are estimated and their uniqueness is shown. The use of mesh structures can reduce the weight o

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15

Hafid, M., Abian Nurrohmad, and Redha Akbar Ramadhan. "NUMERICAL INVESTIGATION ON THE FUSELAGE AIRFRAME OF LSU 05 NG AIRCRAFT." Jurnal Teknologi Dirgantara 18, no. 2 (2020): 93. http://dx.doi.org/10.30536/j.jtd.2020.v18.a3327.

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In this paper, numerical investigation on the fuselage structure of LSU 05 NG was carried out. This fuselage is designed to carry the payload up to 30 kg. Statical numerical analysis using finite element method was done using Simulia Abaqus. The fuselage structure that has been design consists of frame, longeron, and skin that can also be semi-monocoque structure. This airframe use combination of balsa and GFRP type of composite as the material. There are three load case: take-off condition, cruise condition, and landing condition. Tsai-hill failure criteria is used to investigate the strength

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16

Kopecki, Tomasz, Przemysław Mazurek, Tomasz Lis, and Dorota Chodorowska. "Post-buckling deformation states of semi-monocoque cylindrical structures with large cut-outs under operating load conditions. Numerical analysis and experimental tests." Ekspolatacja i Niezawodnosc - Maintenance and Reliability 18, no. 1 (2016): 16–24. http://dx.doi.org/10.17531/ein.2016.1.3.

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17

Muhammad Fadhil, Aditya Prayoga, Andi Eriawan, Erwin Sulaeman, and Ari Legowo. "Aerodynamic Pressure Mapping Technique from CFD to FEM Model of N219 Winglet." CFD Letters 13, no. 12 (2021): 90–99. http://dx.doi.org/10.37934/cfdl.13.12.9099.

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Due to relatively complex geometry of N219 winglets, CFD simulations have to be conducted to predict the aerodynamic load by the structure in some critical flight conditions. Since the aerodynamic CFD model is not the same as the finite element model of the structure, there is a need to accurately transform the load data between the two models. This paper discusses a simple alternative technique to map pressure distribution from the mesh or face zone of a CFD simulation to an FEM model using a Matlab based in-house code program. The technique focuses on how an FEM shell element has same pressu

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18

Kavrar, Deniz, M. Lutfy Öveçoğlu, and Halit S. Türkmen. "Production of a Helicopter Tail Boom and Associated Mechanical Tests." Advanced Materials Research 445 (January 2012): 566–70. http://dx.doi.org/10.4028/www.scientific.net/amr.445.566.

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The lightweight materials such as composites are often used for the aerospace structures. One of the uses of these materials is for the tail boom of helicopters. Tail booms are the structures connecting the tail rotor to the fuselage. It is mainly subjected to the pitching moment and torsion. Because it is long to obtain the enough distance between the tail rotor and the main rotor, the materials used for manufacturing the tail boom needs to be a lightweight material. The structural optimization of the tail boom is also necessary. In this study, two different tail booms are manufactured by usi

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19

Barca, Iga, Jan Godzimirski, and Marek Rośkowicz. "Strength tests of repair joints loaded with tension and loss of stability." Technologia i Automatyzacja Montażu 126, no. 4 (2024): 3–13. https://doi.org/10.7862/tiam.2024.4.1.

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During aircraft service, the skin is the component that first comes into contact with factors that can cause mechanical damage - that is why it is most often damaged during use. Semi-monocoque aircraft structures are made of a skin (usually aluminum alloy) and a frame. The skin is an element that significantly affects the safety of the structure, since it transfers loads between the elements of the frame. For this reason, the skin is subject to special supervision during technical maintenance, and any damage detected must be repaired. The research was carried out on specimens made of AW 2024-T

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20

Liu, Dianzi, Chuanwei Zhang, Z. Wan, and Z. Du. "Topology optimization of a novel fuselage structure in the conceptual design phase." Aircraft Engineering and Aerospace Technology 90, no. 9 (2018): 1385–93. http://dx.doi.org/10.1108/aeat-04-2017-0100.

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Purpose In recent years, innovative aircraft designs have been investigated by researchers to address the environmental and economic issues for the purpose of green aviation. To keep air transport competitive and safe, it is necessary to maximize design efficiencies of the aircrafts in terms of weight and cost. The purpose of this paper is to focus on the research which has led to the development of a novel lattice fuselage design of a forward-swept wing aircraft in the conceptual phase by topology optimization technique. Design/methodology/approach In this paper, the fuselage structure is mod

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21

Rośkowicz, Marek, and Iga Barca. "ANALYSIS OF THE AIRFRAME REPAIR NODE." Technologia i Automatyzacja Montażu, 2022, 42–48. http://dx.doi.org/10.7862/tiam.2022.3.6.

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Polymer composite materials can be used both for the production of semi-monocoque structures and for the repair of aircraft airframes. Of all the elements of the semi-monocoque structure, the airframe skin is most often damaged during operation. The fragments of the skin between the frame elements of the semi-monocoque structure are considered as a thin-walled plate. The paper presents an analysis of the repair node of a metal plate subjected to uniform shear. The model of the repaired plate made in the Ansys Workbench environment was used for the analysis. The boundary conditions were defined

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22

Nilesh Singh, R., S. Rudraksh, and M. Sachidhanandam. "Design, Development and Analysis of a Three-Wheeler Vehicle Chassis." International Journal of Vehicle Structures and Systems 14, no. 1 (2022). http://dx.doi.org/10.4273/ijvss.14.1.13.

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The advancement in a lightweight three-wheeled vehicle chassis is limited and requires development, SHELL eco-marathon is an event that motivates students to build energy-efficient systems to give better mileage efficiency from a vehicle. Chassis is an important element in the development of such lightweight vehicles. This study aims to develop designs of three-wheeler prototype vehicle chassis in tadpole configuration in the spaceframe, semi-monocoque and monocoque construction. Finite element analysis of these designs was carried out using Ansys software. The torsional and bending stiffness

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23

Fink, Axel, and Rolf Schatz. "Structurally integrated constrained layer damping for noise reduction on sandwich and semi-monocoque helicopter structures." Composite Structures, July 2023, 117354. http://dx.doi.org/10.1016/j.compstruct.2023.117354.

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24

Sasongko, Agung Dwi, Handoko, and Raihan Rafif. "2. Analisis Numerik Badan Pesawat Sejenis UAV Aerostar pada Fase Terbang." TNI Angkatan Udara 1, no. 1 (2023). http://dx.doi.org/10.62828/jpb.v1i1.44.

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Pesawat Terbang Tanpa Awak atau UAV merupakan pesawat udarayang mampu terbang dengan interval waktu tertentu tanpa dikendarai oleh pilot,pengendalian pesawat dilakukan secara otomatis melalui perangkat elektronik yangdiprogram serta mampu melakukan misinya berulang kali. Kebutuhan terhadapUAV merupakan salah satu tuntutan perkembangan teknologi penerbangan.Dalam jurnal ini, penelitian berupa simulasi numerik dilakukan pada struktur badanUAV sejenis Aerostar dengan pembebanan pada fase terbang cruise. Badan UAVdirancang dapat menahan beban sebesar 132 kg pada fase terbang cruise denganload fact

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