Academic literature on the topic 'Optimal shapes fuselage'
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Journal articles on the topic "Optimal shapes fuselage"
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Ohapkin, Alexey, and Sergey Serokhvostov. "OPTIMIZATION OF SPAR MASS AND FUSELAGE LOCATION TO DECREASE LOSS OF AIRPLANE LIFT FORCE." Aviation 11, no. 3 (2007): 21–25. http://dx.doi.org/10.3846/16487788.2007.9635965.
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Considered in this paper is the problem of optimizing spar mass to minimize lift force loss for a set of spar cross‐section shapes in cases of constant and elliptical lift force distributions. The main idea is that the deformation of the spar under aerodynamic and gravitational forces causes a decrease in lift force and that there must be some optimal spar strength that gives a minimum for the sum of the loss of lift force and spar weight. The influence of fuselage location on the loss of lift force in the case of multi‐fuselage design is also investigated. The behaviour of lift loss as a function of the location of fuselages is discussed.
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Долгих, Вячеслав Сергеевич. "ОПТИМІЗАЦІЯ НОСОВОЇ ЧАСТИНИ ФЮЗЕЛЯЖУ З ТОЧКИ ЗОРУ АЕРОДИНАМІКИ ЛІТАКА". Open Information and Computer Integrated Technologies, № 86 (14 лютого 2020): 127–38. http://dx.doi.org/10.32620/oikit.2019.86.09.
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The paper represents the analysis intended to optimize the fuselage nose section with regard to aircraft aerodynamics in the process of development of an unmanned transport aircraft (UTA). The article deals with provisions of high aerodynamic efficiency that cannot be achieved without proper selection of the shape and optimal fuselage parameters that determine mutual interference of aircraft components and units. When analyzing the flow improvement around the fuselage nose in flight, three fuselage versions were considered listed further: 1) a prototype for testing automatic flight control systems with participation of pilots; 2) a nose symmetrical relative to the fuselage rocket type cylinder axis; 3) a supposedly optimal variant based on the results of previous calculations. The aerodynamic characteristics of 3D fuselage models for positive integer Reynolds numbers (full-scale model) were calculated using the ANSYS software package. Three computational grids were built for these models in ANSYS ICEM CFD. The given version of the fuselage nose section intended for testing automatic flight control systems with participation of pilots initially has the greatest resistance among the considered variants. That is, first variant of the fuselage nose gives substantial braking zone as well as significant flow acceleration zone exists in place where fuselage is transformed into cylindrical part. The variant with the nose section symmetrical relative to the rocket type cylinder axis has smaller braking zone and less dispersed flow in place where fuselage is transformed into cylindrical part and, therefore, it has lower resistance in comparison with the first version. The fuselage execution developed on the basis of the results of previous calculations, despite the extensive acceleration zone at the junction of the nose to the cylindrical part, has shown the least resistance, respectively, and is the best of the considered variants. This is also confirmed by a comparison of streamlines over the nose surface. The streamlines are given for calculations at angle of attack of 8°; at this angle of attack, the difference in the coefficient Cx is clearly visible.
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Kondor, Máté, and Gergely Dezső. "Unmanned Aerial Vehichle Wing Fuselage Junction Optimalisation with Finite Element Method." Műszaki Tudományos Közlemények 11, no. 1 (2019): 113–16. http://dx.doi.org/10.33894/mtk-2019.11.24.
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Abstract Nowadays one of the main lines of development in aerial craft is the design and construction of unmanned aerial vehicles (UAV’s). Within this wide topic, development of ultralight (UL) aircrafts is especially popular because of their versatility and relative low cost. My task was to design the shape of an airplane wing-fuselage junction, which will be classified as an ultralight and unmanned aerial vehicle. The most optimal wing-fuselage junction is made with the Ansys simulating program, including model calculations. Based on the calculations and results, solutions can be recommended. With CAD geometry models, first stage of testing of the aircraft with 3D printed models, is prepared.
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He, Yanru, Baowei Song, and Yonghui Cao. "Multi-Step Structural Optimization Design of Multi-Bubble Pressure Cabin in the Autonomous Underwater Vehicle with Blended-Wing-Body." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 36, no. 4 (2018): 664–70. http://dx.doi.org/10.1051/jnwpu/20183640664.
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In this paper, multi-bubble pressure cabin is proposed for the flat fuselage of blended-wing-body(BWB) autonomous underwater vehicle(AUV). It has strong compressive capacity and makes full use of the fuselage space. Radial basis function surrogate model and Kriging surrogate model are used to construct mixture surrogate model for higher accuracy. Two infill sampling methods are adopted:the candidate point sampling and the local optimal sampling. Multi-step optimization of multi-bubble pressure cabin is carried out including shape optimization and structure optimization. To optimize shape, the maximum displacement is selected as the objective function and the shape constraint is chosen as the constraint condition. The minimum structural quality is selected as the objective function, the maximum equivalent stress and bulking factor are chosen as the constraint condition to optimize structure. Finite element method(FEM) analysis is carried out to study the strength and stability performance of multi-bubble pressure cabin using the commercial computational structural mechanics code ANSYS.
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Biancolini, Marco Evangelos, Emiliano Costa, Ubaldo Cella, Corrado Groth, Gregor Veble, and Matej Andrejašič. "Glider fuselage-wing junction optimization using CFD and RBF mesh morphing." Aircraft Engineering and Aerospace Technology 88, no. 6 (2016): 740–52. http://dx.doi.org/10.1108/aeat-12-2014-0211.
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Purpose The present paper aims to address the description of a numerical optimization procedure, based on mesh morphing, and its application for the improvement of the aerodynamic performance of an industrial glider which suffers of a large separation occurring in the wing–fuselage junction region at high incidence angles. Design/methodology/approach Shape variations were applied to the baseline configuration through a mesh morphing technique founded on the mathematical framework of radial basis functions (RBF). The aerodynamic solutions were obtained coupling an RANS code with the mesh morphing tool RBF Morph™. Two shape modifiers were set up to generate a parametric numerical model. An optimization procedure, based on a design of experiment sampling, was set up implementing the fully automated workflow within a high performance computing (HPC) environment. The optimal candidates maximizing the aerodynamic efficiency were identified by means of a cubic RBF response surface approach. Findings The separation was significantly reduced, modifying the local geometry of fuselage and fairing and maintaining the wing aerofoil unchanged. A relevant aerodynamic efficiency improvement was finally gained. Practical implications The developed procedure proved to be a very powerful and efficient tool in facing aerodynamic design problems. However, it might be computationally very expensive if a large number of design variables are adopted and, in those cases, the method can be suitably used only within the HPC environment. Originality/value Such an optimization study is part of an explorative set of analyses that focused on better addressing the numerical strategies to be used in the development of the EU FP7 Project RBF4AERO.
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Sasaki, Daisuke, and Kazuhiro Nakahashi. "Aerodynamic Optimization of an Over-the-Wing-Nacelle-Mount Configuration." Modelling and Simulation in Engineering 2011 (2011): 1–13. http://dx.doi.org/10.1155/2011/293078.
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An over-the-wing-nacelle-mount airplane configuration is known to prevent the noise propagation from jet engines toward ground. However, the configuration is assumed to have low aerodynamic efficiency due to the aerodynamic interference effect between a wing and a nacelle. In this paper, aerodynamic design optimization is conducted to improve aerodynamic efficiency to be equivalent to conventional under-the-wing-nacelle-mount configuration. The nacelle and wing geometry are modified to achieve high lift-to-drag ratio, and the optimal geometry is compared with a conventional configuration. Pylon shape is also modified to reduce aerodynamic interference effect. The final wing-fuselage-nacelle model is compared with the DLR F6 model to discuss the potential of Over-the-Wing-Nacelle-Mount geometry for an environmental-friendly future aircraft.
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Kuprikov, Mikhail, Leonid Ponyaev, and Nikita Kuprikov. "DECREASE OF SOUND PRESSURE LEVEL AND NOISE INSIDE HYBRID ELECTRIC WING BODY PLANES AND DIRIDGABLES." Akustika 34 (November 1, 2019): 170–73. http://dx.doi.org/10.36336/akustika201934170.
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The analysis of the find Optimal Structure of the Large Aircraft and Airship for decrease of Sound/Noise Pressure Level inside and outside the Cabin Saloon are very actually today for Worldwide Ecology Program. The Method of Aircraft layout from the virtual mass center is given, which allows us to obtain the Aircraft layout from the conditions of Infrastructural Constraints in the terminal configurations of the Modern Air Transportation Infrastructure and IATA/ICAO Regulation. A Method is proposed for the synthesis of new circuit solutions for an Aircraft passenger compartment and may be use to any Diridgables Projections future. A Geometrical representation of the concept of LHA with large passenger capacity made with a Drop-Shaped Fuselage in the Aerodynamic balancing Flying Wing Body Scheme is given.The new Body Plane LHA and Lighter-then-Air (LTA) Vehicles with cover of Solar Electro Systems will be more innovation projections for Worldwide Security Air Transportation with reduce Noise and CO Pollution Level.
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Du, Juan, Xiaowei Yue, Jeffrey H. Hunt, and Jianjun Shi. "Optimal Placement of Actuators Via Sparse Learning for Composite Fuselage Shape Control." Journal of Manufacturing Science and Engineering 141, no. 10 (2019). http://dx.doi.org/10.1115/1.4044249.
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Shape control is a critical task in the composite fuselage assembly process due to the dimensional variabilities of incoming fuselages. To realize fuselage shape adjustment, actuators are used to pull or push several points on a fuselage. Given a fixed number of actuators, the locations of actuators on a fuselage will impact on the effectiveness of shape control. Thus, it is important to determine the optimal placement of actuators in the fuselage shape control problem. In current practice, the actuators are placed with equal distance along the edge of a fuselage without considering its incoming dimensional shape. Such practice has two limitations: (1) it is non-optimal and (2) larger actuator forces may be applied for some locations than needed. This paper proposes an optimal actuator placement methodology for efficient composite fuselage shape control by developing a sparse learning model and corresponding parameter estimation algorithm. The case study shows that our proposed method achieves the optimal actuator placement for shape adjustments of the composite fuselage.
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Enggar Kristian, Agus Suprianto, Nurhadi Pramana, Sahril Afandi, and Endah Yuniarti. "Analisis Numerik Part Bulkhead Pada Sub System Wing To Fuselage Joinner Assembly Pesawat Aerobatik Menggunakan Metode Elemen Hingga." Jurnal Teknologi Kedirgantaraan 6, no. 1 (2021). http://dx.doi.org/10.35894/jtk.v6i1.34.
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Analisis rancangan bulkhead dilakukan untuk memperoleh geometri terbaik untuk mencari berat yang efisien dengan mengubah geometri bentuk pada bulkhead yang merupakan sub system wing to fuselage untuk pesawat berkategori aerobatik dan berat yang optimal yang memenuhi persyaratan regulasi FAR 23 dan mengetahui respon distribusi tegangan, bending yang dihasilkan dan kriteria kegagalan struktur berdasarkan variasi geometri bentuk bulkhead. Pada penelitian ini untuk analisis statik bulkhead untuk pesawat berkategori aerobatik menggunakan material Aluminium Alloy 7075-T6 dan menggunakan metode pendekatan Schrenk untuk menghitung beban eksternal distrbusi gaya angkat pada sayap. Selain itu dilakukan proses optimisasi berat bulkhead berdasarkan metode pendekatan topologi yaitu perubahan geometri bentuk pada bulkhead untuk mereduksi berat, sudut insiden spar yang berbeda dan menghitung magin of safety. Proses penyelesaian masalah menggunakan perangkat lunak metode elemen hingga (Abaqus CAE). Optimisasi topologi pada part bulkhead sudut insidet 0° dan 4° menghasilkan volume yang berkurang pada benda sehingga mereduksi berat, tetapi nilai dari margin of safety MS = 0. The bulkhead design analysis was carried out to obtain the best geometry to find an efficient weight by changing the shape geometry of the bulkhead which is a sub-system of the wing to the fuselage for an aircraft categorized as aerobatics and an optimal weight that meets the requirements of FAR 23 regulations and sees the stress distribution response, the resulting bending and structural failure criteria based on the geometric variation of bulkhead shapes. In this study, to analyze the bulkhead static for an aerobatic category aircraft using Aluminum Alloy 7075-T6 material and using the Schrenk Approximation method to calculate the external distribution load of lift force on the wing. In addition, the optimization of bulkhead weight based on the topological approach method is to change the shape geometry of the bulkhead to reduce weight, in different spar incidents and calculate margin of safety. The problem solving process uses finite element method software (Abaqus CAE). Topological optimization of the bulkhead part with an incidence angle of 0 ° and 4 ° results in a reduced volume of the object so that it reduces weight, but the value of the margin of safety MS = 0.
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Yue, Xiaowei, Yuchen Wen, Jeffrey H. Hunt, and Jianjun Shi. "Surrogate Model-Based Control Considering Uncertainties for Composite Fuselage Assembly." Journal of Manufacturing Science and Engineering 140, no. 4 (2018). http://dx.doi.org/10.1115/1.4038510.
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Shape control of composite parts is vital for large-scale production and integration of composite materials in the aerospace industry. The current industry practice of shape control uses passive manual metrology. This has three major limitations: (i) low efficiency: it requires multiple trials and a longer time to achieve the desired shape during the assembly process; (ii) nonoptimal: it is challenging to reach optimal deviation reduction; and (iii) experience-dependent: highly skilled engineers are required during the assembly process. This paper describes an automated shape control system that can adjust composite parts to an optimal configuration in a manner that is highly effective and efficient. The objective is accomplished by (i) building a finite element analysis (FEA) platform, validated by experimental data; (ii) developing a surrogate model with consideration of actuator uncertainty, part uncertainty, modeling uncertainty, and unquantified uncertainty to achieve predictive performance and embedding the model into a feed-forward control algorithm; and (iii) conducting multivariable optimization to determine the optimal actions of actuators. We show that the surrogate model considering uncertainties (SMU) achieves satisfactory prediction performance and that the automated optimal shape control system can significantly reduce the assembly time with improved dimensional quality.
Dissertations / Theses on the topic "Optimal shapes fuselage"
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Weis, Martin. "Návrh optimálního tvaru trupu amfibie „Seagle“." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2009. http://www.nusl.cz/ntk/nusl-228598.
Full textConference papers on the topic "Optimal shapes fuselage"
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Valenti, Justin D., Michael P. Kinzel, and Simon W. Miller. "Sequential Design of UAV Fuselage Pods Using Bounding Aerodynamic Models." In ASME 2017 Fluids Engineering Division Summer Meeting. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/fedsm2017-69361.
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In this work, a Sequential Decision Process (SDP) is applied to perform fuselage design using Computational Fluid Dynamics (CFD). The SDP uses models to provide two-sided estimates that attempt to bound the exact solution, ultimately converging to an optimal design space to be analyzed with models of increased fidelity. The present work proposes the use of laminar and turbulent physics in CFD models to form lower and upper bounds on drag calculations, respectively. These bounding models are then used in a formal SDP to cull the design space, focusing the region of interest for increased fidelity modeling and analysis. Increasing mesh resolution is used to increase fidelity, creating a multi-fidelity approach to aerodynamic shape design. In this work the SDP-CFD design approach is applied to two design problems: (1) drag minimization of a fairing with a defined thickness and (2) drag per unit volume minimization of a fairing. The results of this study demonstrate that the SDP-CFD approach can accurately and quickly improve the fuselage design.
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Belloli, Alberto, Oliver Thomaschewski, and Paolo Ermanni. "Optimum Placement of Piezoelectric Ceramic Modules for Vibration Suppression of Highly Constrained Structures." In ASME 2005 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. ASMEDC, 2005. http://dx.doi.org/10.1115/detc2005-84614.
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The vibration suppression efficiency of so-called shunted piezoelectric systems is decisively influenced by the number, shape, dimension, and position of the implemented piezoelectric ceramic elements. This paper presents a procedure based on evolutionary algorithms for optimum placement of piezoelectric ceramic modules on real-world, highly constrained lightweight structures. The optimization loop includes the CAD software CATIA V5, the FE package ANSYS and DynOPS, a proprietary software tool able to connect the Evolving Object library with any simulation software that can be started in batch-mode. A user-defined piezoelectric shell element is integrated into ANSYS 8.1. Modal generalized electromechanical coupling coefficients are used as optimization objective and constraints. Position, dimension and shape of commercial, customized and free-form patches are determined for optimum multi-mode vibration suppression of a pinned, quadratic plate. An aircraft fuselage panel with a window cutout is investigated as test object for complex, curved geometries.