Relevant bibliographies by topics / Wing spar

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Academic literature on the topic 'Wing spar'

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

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Journal articles on the topic "Wing spar"

1

ENNOS, A. ROLAND. "The Importance of Torsion in the Design of Insect Wings." Journal of Experimental Biology 140, no. 1 (November 1, 1988): 137–60. http://dx.doi.org/10.1242/jeb.140.1.137.

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A model insect wing is described in which spars of corrugated membrane which incorporate stiffening veins branch serially from a V-section leading edge spar. The mechanical behaviour of this model is analysed. The open, corrugated spars possess great resistance to bending, but are compliant in torsion. Torsion of the leading edge spar will result in torsion and relative movement of the rear spars. As a result camber will automatically be set up in the wing as it twists. Aerodynamic forces produced during the wing strokes will result in torsion and camber of the wing which should improve its aerodynamic efficiency. The effects of varying parameters of the wing model are examined. For given wing torsion, higher camber is given by spars branching from the leading edge at a lower angle, by spars which curve posteriorly, and by spars which diverge from each other. Wings of three species of flies were each subjected to two series of mechanical tests. Application of a force behind the torsional axis caused the wings to twist and to develop camber. Immobilizing basal regions of the leading edge greatly reduced compliance to torsion and camber, as predicted by the theoretical model. Aerodynamic forces produced during a half-stroke are sufficient to produce observed values of torsion and camber, and to maintain changes in pitch caused by inertial effects at stroke reversal.
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Kong, Chang Duk, Hyun Bum Park, Jae Huy Yoon, and Kuk Jin Kang. "Conceptual Design on Carbon-Epoxy Composite Wing of a Small Scale WIG Vehicle." Key Engineering Materials 334-335 (March 2007): 353–56. http://dx.doi.org/10.4028/www.scientific.net/kem.334-335.353.

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Conceptual structural design of the main wing for the 20 seats WIG(Wing in Ground Effect)flight vehicle, which will be a high speed maritime transportation system for the next generation in Rep. of Korea, was performed[1,2]. The high stiffness and strength Carbon-Epoxy material was used for the major structure and the skin-spar with a foam sandwich structural type was adopted for improvement of lightness and structural stability. As a design procedure for this study, firstly the design load was estimated through the critical flight load case study, and then flanges of the front and the rear spar from major bending loads and the skin structure and the webs of the spars from shear loads were preliminarily sized using the netting rule and the rule of mixture[4,5]. In order to investigate the structural safety and stability, stress analysis was performed by commercial Finite Element code such as NASTRAN/PATRAN. From the stress analysis results, it was confirmed that the upper skin structure between the front spar and rear spar was weak for the buckling. Therefore in order to solve this problem, a middle spar and the foam sandwich structure at the upper skin and the web were added. After design modification, even thought the designed wing weight was a little bit heavier than the target wing weight, the structural safety and stability of the final design feature was confirmed. In addition to this, the insert bolt type structure with six high strength bolts to fix the wing structure at the fuselage was adopted for easy assembly and removal. As well as consideration of the fatigue limit load for more than 20 years fatigue life.
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Zhou, Hong Xia, and Bin Liu. "Characteristics Analysis and Optimization of Flying-Wing Vehicle Structure." Advanced Materials Research 1077 (December 2014): 177–84. http://dx.doi.org/10.4028/www.scientific.net/amr.1077.177.

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To study structural characteristics of flying-wing vehicle, static and dynamic model of half wing span, static and dynamic model of all wing span, optimization model were established. Based on associated static test and ground resonance test data, these models were modified to implement static, dynamic and optimization analysis. Results demonstrated that structural bending and torsional deformations are mainly at outer wing surface. Torsion at inner wing is positive, while torsion at outer wing is negative. Total spar axial force along the wing span increases gradually from inner wing to outer wing and then decreases gradually after reaching the inner-outer wing interface. After axial force is transmitted to the inner wing, it is going to concentrate at the rear spar obviously. Structural bending rigidity and torsional rigidity satisfy requirements of both static force and flutter, without flutter problem of main structural mode. Viewed from the optimization size, ±45° and 0° skin at inner-outer wing turn thickens significantly. This can increase structural bending and torsional rigidity, which is good for satisfying multiple constraints comprehensively.
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Stamatelos, Dimitriοs, and George Labeas. "Towards the Design of a Multispar Composite Wing." Computation 8, no. 2 (April 9, 2020): 24. http://dx.doi.org/10.3390/computation8020024.

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In the pursuit of a lighter composite wing design, fast and effective methodologies for sizing and validating the wing members (e.g., spar, ribs, skins, etc.) are required. In the present paper, the preliminary design methodology of an airliner main composite wing, which has an innovative multispar configuration instead of the conventional two-spar design, is investigated. The investigated aircraft wing is a large-scale composite component, requiring an efficient analysis methodology; for this purpose, the initial wing sizing is mostly based on simplified Finite Element (FE) stress analysis combined to analytically formulated design criteria. The proposed methodology comprises three basic modules, namely, computational stress analysis of the wing structure, comparison of the stress–strain results to specific design allowable and a suitable resizing procedure, until all design requirements are satisfied. The design constraints include strain allowable for the entire wing structure, stability constraints for the upper skin and spar webs, as well as bearing bypass analysis of the riveted/bolted joints of the spar flanges/skins connection. A comparison between a conventional (2-spar) and an innovative 4-spar wing configuration is presented. It arises from the comparison between the conventional and the 4-spar wing arrangement, that under certain conditions the multispar configuration has significant advantages over the conventional design.
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Petrasinovic, Nikola, Danilo Petrasinovic, Bosko Rasuo, and Dragan Milkovic. "Aircraft duraluminum wing spar fatigue testing." FME Transaction 45, no. 4 (2017): 531–36. http://dx.doi.org/10.5937/fmet1704531p.

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Ajaj, R. M., M. I. Friswell, W. G. Dettmer, G. Allegri, and A. T. Isikveren. "Performance and control optimisations using the adaptive torsion wing." Aeronautical Journal 116, no. 1184 (October 2012): 1061–77. http://dx.doi.org/10.1017/s000192400000748x.

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Abstract This paper presents the Adaptive Torsion Wing (ATW) concept and performs two multidisciplinary design optimisation (MDO) studies by employing this novel concept across the wing of a representative UAV. The ATW concept varies the torsional stiffness of a two-spar wingbox by changing the enclosed area through the relative chordwise positions of the front and rear spar webs. The first study investigates the use of the ATW concept to improve the aerodynamic efficiency (lift-to-drag ratio) of the UAV. In contrast, the second study investigates the use of the concept to replace conventional ailerons and provide roll control. In both studies, the semi-span of the wing is split into five equal partitions and the concept is employed in each of them. The partitions are connected through thick ribs that allow the spar webs of each partition to translate independently of the webs of adjacent partitions and maintain a continuous load path across the wing span. An MDO suite consisting of a Genetic Algorithm (GA) optimiser coupled with a high-end low-fidelity aero-structural model was developed and employed in this paper.
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Dvorak, Milan, Miroslav Kabrt, and Milan Růžička. "The Use of Fiber Bragg Grating Sensors during the Static Load Test of a Composite Wing Structure." Applied Mechanics and Materials 486 (December 2013): 102–5. http://dx.doi.org/10.4028/www.scientific.net/amm.486.102.

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The article describes process of implementation of optical Fiber Bragg Grating (FBG) sensors into the composite wing structure and their behavior during the strength test. The wing is of all-composite construction. The upper and lower skins are made of glass/epoxy composite. The spar caps are made of carbon/epoxy unidirectional composite. Optical fibers were integrated directly into the spar caps and into the adhesive joints. They were oriented in parallel with the main spar axis. The first optical fiber with chain of multiple FBG sensors was integrated into the structure of upper spar cap. Another FBG chain of FBG sensors was located in the adhesive joint of lower spar cap and shear web. The wing was instrumented with strain gages as well. Strain gages were glued to the sides of the spar caps. Static load was produced by a hydraulic actuator. Experimental results from strain gages and FBG sensors were compared with the results of the analytical analysis of the wing.
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Wang, Yuhui, Peng Shao, Qingxian Wu, and Mou Chen. "Reliability analysis for a hypersonic aircraft’s wing spar." Aircraft Engineering and Aerospace Technology 91, no. 4 (April 1, 2019): 549–57. http://dx.doi.org/10.1108/aeat-11-2017-0242.

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Purpose This paper aims to present a novel structural reliability analysis scheme with considering the structural strength degradation for the wing spar of a generic hypersonic aircraft to guarantee flight safety and structural reliability. Design/methodology/approach A logarithmic model with strength degradation for the wing spar is constructed, and a reliability model of the wing spar is established based on stress-strength interference theory and total probability theorem. Findings It is demonstrated that the proposed reliability analysis scheme can obtain more accurate structural reliability and failure results for the wing spar, and the strength degradation cannot be neglected. Furthermore, the obtained results will provide an important reference for the structural safety of hypersonic aircraft. Research limitations/implications The proposed reliability analysis scheme has not implemented in actual flight, as all the simulations are conducted according to the actual experiment data. Practical implications The proposed reliability analysis scheme can solve the structural life problem of the wing spar for hypersonic aircraft and meet engineering practice requirements, and it also provides an important reference to guarantee the flight safety and structural reliability for hypersonic aircraft. Originality/value To describe the damage evolution more accurately, with consideration of strength degradation, flight dynamics and material characteristics of the hypersonic aircraft, the stress-strength interference method is first applied to analyze the structural reliability of the wing spar for the hypersonic aircraft. The proposed analysis scheme is implemented on the dynamic model of the hypersonic aircraft, and the simulation demonstrates that a more reasonable reliability result can be achieved.
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Pavan, G., and N. Kishore. "Static and Fatigue Analysis on a Wing Spar Joint for a Light Jet Aircraft Structure Using 2024 T351 Material." Applied Mechanics and Materials 895 (November 2019): 244–52. http://dx.doi.org/10.4028/www.scientific.net/amm.895.244.

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The main objective of this paper is to present prototype of wing spar joint using CATIA V5 software to study the behavior of wing spar joint as per actual working condition and to perform structural analysis of the wing spar joint based on condition of cyclic loading (fatigue loading). Determining the loading modes in the spar joint is subjected to static load and fatigue loads which should be taken into account in the evaluation of the strength and fatigue life. Initially, the components were modeled with CATIA V5 and imported to MSC PATRAN; MSC NASTRAN is used as a solver. From the obtained maximum tensile stresses, fatigue analysis was carried out to find fatigue life of the spar joint with different fatigue load spectra.
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Edwards, Tim, and Jeremy Thompson. "Spar Corner Radius Integrity for the A400M Wing." Applied Mechanics and Materials 3-4 (August 2006): 197–204. http://dx.doi.org/10.4028/www.scientific.net/amm.3-4.197.

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The paper focuses on the structural integrity of the corner radius of the carbon fibre composite, ‘C’-section spar for the Airbus A400M wing. The corner radius is subject to opening moments generated by internal wing box fuel pressures. The low inter-lamina strength of composites makes de-lamination of the corner of prime concern. The paper describes initial development of analytical techniques to calculate the through-thickness tensile stresses and inter-lamina shear stresses developed in a corner radius under applied bending moments and transverse shear forces. A test programme is also described, aimed at the determination of the failure moment of curved laminates under pure bending moments. Using the analytical expressions developed, a through-thickness failure stress is calculated from the failure moments. A variation of the failure stress with specimen thickness is indicated, showing that thicker specimens fail at higher inter-lamina stresses – a characteristic that must be exploited in the design of the spar. Using finite element analysis of the test configuration, in conjunction with virtual crack extension techniques, it is demonstrated that, at the failure load, a constant rate of strain energy release accompanies inter-lamina crack growth in the different test specimens. A critical energy release rate for uncontrolled crack growth is thus established, which is used, in conjunction with further finite element analysis, to predict the failure stress of specimens with different values of thickness and corner radius. It is concluded that this fracture mechanics approach to integrity can be applied to the A400M spar corner and to similar aircraft structures. Recommendations for further testing and correlation with analysis are proposed to strengthen the theoretical basis for such integrity assessments.
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Dissertations / Theses on the topic "Wing spar"

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Lazarin, Juan Reuben. "Optimum Design of Composite Wing Spar Subjected to Fatigue Loadings." DigitalCommons@CalPoly, 2017. https://digitalcommons.calpoly.edu/theses/1816.

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Composites are now being incorporated into aircraft designs because of their high strength to weight ratio compared to traditional metal materials. Due to the complexity of the material, composite parts are presently being over designed to satisfy static and fatigue requirements. A greater understanding of composite fatigue behavior will allow for even greater weight savings leading to increased fuel economy. A critical part of an aircraft that is subjected to fatigue bending loads are its wings. The forces acting on the wings include its lift distribution, powerplant, and fuel which can be carried in the wing body. When in flight these forces repeatedly cause cyclic displacements which could ultimately lead to failure. It is important to design the wing spars which carry the bending loads, to be fatigue resistant so that damage or expensive inspections could be avoided. Wing models were be made from composite materials with a NACA 0016 airfoil shape, chord length of 9.25”, and a span of 15.25”. The C – channel spars were located at 22% and 72% of the chord. Strain gages on the wing model were used to measure strain at different locations. Static test were conducted on the specimens in order to validate a finite element analysis(FEA) model to be used for simulations. Overall, the strain measurements on the leading edge from two of the wings matched the model within 9% of the simulation results. Additional spar designs were then analyzed to determine the optimal one for static and fatigue bending loads. The wings were fatigue tested under displacement control at a test frequency. A model 8801 servo-hydraulic Instron machine and Wave Matrix software was used to fatigue the wings. After 100,000 cycles the test would be deemed a success and concluded.
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Kite, Adam Howard. "Nondestructive evaluation of a carbon fiber wing spar using air-coupled ultrasound." [Ames, Iowa : Iowa State University], 2007.

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Hála, Aleš. "Návrh změny kostrukčního řešení hlavních závěsů křídla letounu Z 242." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2020. http://www.nusl.cz/ntk/nusl-417468.

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This diploma thesis deals with modernization of the Z 242 L aircraft wing. The main emphasis is given to the connection of the wing and fuselage. The new concept of both main and rear wing spar is designed together with integral fuel tank. The strength of the structure is evaluated analytically and numerically by use of Finite element analysis. Wide range of milling operations is implemented into manufacturing process as well. This thesis shows how to innovate current aircraft with respect to feasibility of the design in case of future project realization.
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Thompson, Eric J. "Design of a multi-piece removable mandrel mold tool to fabricate and control inner mold surface contour of a composite wing spar." Morgantown, W. Va. : [West Virginia University Libraries], 2010. http://hdl.handle.net/10450/11141.

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Thesis (M.S.)--West Virginia University, 2010.
Title from document title page. Document formatted into pages; contains viii, 69 p. : col. ill. Includes abstract. Includes bibliographical references (p. 69).
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Cejpek, Jakub. "Analysis of Aeronautical Composite Structures under Static Loading." Doctoral thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2018. http://www.nusl.cz/ntk/nusl-385288.

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Poměrně velké množství soukromých firem v České republice vyrábí lehká sportovní letadla. Značná část těchto letadel využívá kompozitní pružiny ve svých přistávacích zařízení. Tyto pružiny jsou buďto menší díly, absorbující energii (na příďové noze či ostruze), anebo jde celé pružnice hlavního podvozku. Všechny tyto pružiny sdílí základní charakteristiky: jsou vyrobeny převážně z jednosměrného kompozitu s významnou tloušťkou, hlavním druhem zatížení je ohybový moment a jsou očekávány velké deformace. Podobnou charakteristiku můžeme použít i při popisu hlavního nosníku křídla. Jak vypadá návrh a analýza takovýchto dílů? V zásadě jsou dvě možnosti. První z nich je poměrně jednoduchá analytická analýza, případně naprogramovaná v tabulkovém výpočetním prostředí. Nevýhody tohoto řešení jsou limitované možnosti výpočtu a jeho nízká flexibilita. Druhou možností je využít komerční konečno-prvkový systém pro analýzu, případně i pro optimalizaci. Pochopitelnou nevýhodou této možnosti je cena programu a obsluhy. Cílem této disertační práce je vytvořit program, jež nabídne třetí možnost, která umožní provádět zevrubnou analýzu řešených produktů bez nutnosti pořizovat nákladný software. Tento program zjednoduší a urychlí návrh a pevnostní kontrolu. Umožní uživateli rychle analyzovat více návrhových variant. Program dále bude zohledňovat specifika analyzovaných produktů (například velké deformace a lokální koncentrace napětí kolmo na vlákno). Z pohledu uživatele by program měl být jednoduchý na ovládání. Minimum množství vstupních dat a přehledné grafické rozhraní zajistí komfortní používání. Samostatně spustitelný program (bez instalace a bez podpůrného softwaru) zlepšuje rozšiřitelnost programu.
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Mestrinho, João Rafael da Conceição. "Design of a variable-span morphing wing." Master's thesis, Universidade da Beira Interior, 2009. http://hdl.handle.net/10400.6/2048.

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The present work focuses on the study, design and validation of a variable-span morphing wing to be tted to the UAV \Olharapo". Using an optimization code, which uses a viscous two-dimensional panel method formulation coupled with a non-linear liftingline algorithm and a sequential quadratic programming optimization routine, na aerodynamic analysis is performed to estimate the optimal values of wing span which ensure minimum drag across the ight speed envelope. The UAV ies in a relatively short speed range - from about 12 m/s to 30 m/s. Near its maximum speed it is possible to obtain a 20% drag reduction with the variable-span wing in comparison with the original xed wing. A stability analysis is also performed to estimate the roll rate available with asymmetric span control. The variable-span wing matches the aileron in terms of roll power and maximum roll rate. It is concluded that roll control is possible with asymmetric span control. A new electro-mechanical actuation mechanism is developed using a simple and cheap rack and pinion system. The wing model is designed with graphical CAD/CAM tools and then a full scale model is built for bench testing the wing/actuator system. The concepts used on the morphing wing for both xed and movable part are considered simple and e ective. The actuation concept is also feasible but needs improvements in the attenuator. A powerful servo is also needed to more easily deploy the wing. Some future modi cations at structural level and ideas for an in-flight automatic span controller are also presented.
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Proskovics, Roberts. "Dynamic response of spar-type offshore floating wind turbines." Thesis, University of Strathclyde, 2015. http://oleg.lib.strath.ac.uk:80/R/?func=dbin-jump-full&object_id=26017.

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In recent years there has been a significant increase in the interest in floating offshore wind turbines from the wind energy industry, governments and academia. Partially driven by the recent nuclear disaster in Japan, but also by the lack or complete absence of shallow waters in various countries around the globe (making fixed offshore wind turbines infeasible), multiple different topology floating offshore wind turbines have been proposed and, in some cases, prototypes built and installed offshore. The most well-known of these is Hywind by Statoil, which has been operational off the coast of Norway since the end of 2009. While small scale prototypes had been installed even before Hywind, for example Blue-H in 2007, no guidelines have yet emerged that would give recommendations and guiding principles in designing new floating offshore wind turbines. The aim of this thesis is to provide some knowledge base for future design of floating offshore wind turbines by looking at what simplifications could be made and what effect these would have on the preliminary designs of new floating offshore wind turbines. This thesis starts by comparing different topology floating offshore wind turbines and choosing one, deemed the most promising, as the base case scenario for use in the subsequent analysis and calculations. This thesis also looks at the importance of unsteady representations of the aerodynamics compared with quasi-steady when designing a new floating offshore wind turbine, by comparing quasi-steady aerodynamic loads first with fully-attached unsteady loads and later with fully-unsteady (fully-attached, separated and dynamic stall). A chapter is allocated to identifying which degree-of-freedom of loading is the most damaging to the system, as floating offshore wind turbines operate in very harsh and unstable environments. Once identified, this knowledge can be used to further improve floating offshore wind turbines, hence making them even more feasible. Finally, the wind turbine previously chosen as a base case has its floating support shortened and four different draft designs proposed that would allow it to be deployed in medium-to-deep waters, in which fixed supports for wind turbines are not economical.
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Solberg, Thomas. "Dynamic Response Analysis of a Spar Type Floating Wind Turbine." Thesis, Norges teknisk-naturvitenskapelige universitet, Institutt for marin teknikk, 2011. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-16215.

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Wind power is a large natural source for renewable energy, and many countries have shown interest in establishing floating offshore wind parks. There are many advantages with floating offshore wind turbines, but also many challenges connected to them. This report focuses on establishing a model for wave-wind induced loading on a Spar type floating wind turbine named OC3-Hywind. The OC3-Hywind is a modified version of an original design developed by Statoil. Two fellow MSc students have developed models for a tension leg platform (TLP) and a semi-submersible, and a comparison between the three concepts have been done. The model has been constructed by the use of the well known software tools HydroD and DeepC. In addition, a DLL extension, TDHMILL3d, was used to obtain thrust force. HydroD was used in calculations of the hydrodynamic coefficients of the floater. DeepC was used to run coupled floater and mooring analysis in time domain. Important parameters like hydrodynamic coefficients and natural frequencies compare well to data from the literature. Simulations showed that the Spar is mostly influenced by wind loads in the operational conditions. At rated wind speed of 11.4 m/s the pitch motions of the Spar was showed to be large. To reduce these motions a simple filter was used to extend the turbine control system. In situations where wind and waves have different directions, the Spar experiences large yaw motions. Several factors that may contribute to these motions have studied. To achieve good accuracy in statistical parameters, 10 or more simulations with different seeds were needed.The original depth of 320 m was changed to 160 m. Only minor changes to the mooring system were needed to obtain similar performance as the base case. In the comparison part typical trends of the different floaters was studied. Based on these trends, positive and negative response characteristics were discovered. The semi-submersible had the largest pitch and surge motions, while the TLP had the largest accelerations below rated. This may result in difficulties in maintenance operations. Only the Spar showed sign of excessive yaw motions. The semi-submersible had the lowest nacelle accelerations and STD for all load cases. In addition, the semi-submersible is the most versatile when it comes to water depth.
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Lee, Sungho Ph D. Massachusetts Institute of Technology. "Dynamic response analysis of spar buoy floating wind turbine systems." Thesis, Massachusetts Institute of Technology, 2008. http://hdl.handle.net/1721.1/46545.

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Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Mechanical Engineering, 2008.
Includes bibliographical references (leaves 83-84).
The importance of alternative energy development has been dramatically increased by the dwindling supplies of oil and gas, and our growing efforts to protect our environment. A variety of meaningful steps have been taken in order to come up with cleaner, healthier and more affordable energy alternatives. Wind energy is one of the most reliable energy alternatives for countries that have sufficiently large wind sources. Due to the presence of steady and strong winds, and the distance from coastline residential, the offshore wind farm has become highly attractive as an ideal energy crisis solution. Floating wind turbine systems are being considered as a key solution to make the offshore wind farm feasible from an economic viewpoint, and viable as an energy resource. This paper presents the design of a synthetic mooring system for spar buoy floating wind turbines functioning in shallow water depths. Nacelle acceleration, static and dynamic tensions on catenaries, the maximum tension acting on the anchors are considered as design performances, and a stochastic analysis method has been used to evaluate those quantities based on sea state spectral density functions. The performance at a 100-year hurricane condition is being defined as a limiting case, and a linear wave theory has been the most fundamental theory applied for the present analysis.
by Sungho Lee.
S.M.
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Sanches, Tiago Nunes. "Longitudinal flight control with a variable span morphing wing." Master's thesis, Universidade da Beira Interior, 2012. http://hdl.handle.net/10400.6/2006.

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The present study focuses on the design of a longitudinal flight controller for an unmanned aircraft equipped with dissymmetric variable-span system (VSMW or Variable-Span Morphing Wing). Its primary role consists in the longitudinal flight stabilization of the aeroplane while in levelled cruise flight, although, it was designed to offer longitudinal flight stabilization for other flight phases as well, such as e.g. take-off and landing. The stabilization algorithm relies on the most up-to-date developments in the state-of-the-art LQR and Batz-Kleinman controller techniques to stabilize the aircraft on its intended longitudinal attitude upon any small atmospheric disturbances inflicted. It was designed for the experimental UAV prototype Olharapo equipped with the VSMW, so it can automatically adjust the VSMW overall wingspan in accordance with the flight speed and stabilize the aircraft in the desired attitude, although, its modular concept allows it to be used for different configurations of the aircraft or even for a different aircraft. The development, simulation and testing of the algorithm were done using the MATLAB® software and the aircraft’s stability and control derivatives previously obtained using the XFLR5® software. Minor adaptations of the flight dynamics equations were performed to allow the compatibilization with the VSMW. The required implementation of imposed flight qualities was also performed to ensure proper scaling the controller weight matrix for optimal values. Finally, the algorithm was tested using three different methods: Classic Disturbances Simulation, Sinusoidal Pitch Variation Test Response and Random Pitch Variation Test Response.
O presente trabalho consiste na projeção, programação e teste de um controlador de voo longitudinal destinado a uma aeronave não-tripulada equipada com um sistema de variação dissimétrica da envergadura das asas (conhecido como VSMW, asa dissimétrica ou asa telescópica). Este trabalho tem como principal objetivo desenvolver um controlador capaz de assegurar a estabilidade longitudinal da aeronave em voo nivelado a velocidade de cruzeiro, contudo, este foi também projetado para providenciar essa mesma estabilidade noutras fases de voo tais como a aterragem ou a descolagem. O algoritmo de estabilização baseia-se nas mais sofisticadas técnicas de controlo de voo atualmente disponíveis, mais concretamente LQR e Batz-Kleinman, para estabilizar a aeronave na atitude pretendida aquando da ocorrência de quaisquer pequenas perturbações atmosféricas que afetem a aeronave durante o voo. A aeronave a que se destina trata-se de um protótipo designado de Olharapo equipado com uma asa telescópica que permite ajustar a envergadura total das asas de acordo com a velocidade de voo. No entanto, o conceito modular da estrutura do programa permite que o controlador possa ser utilizado para diferentes configurações da mesma aeronave, ou até mesmo com uma aeronave totalmente diferente. Tanto o desenvolvimento como as simulações e testes do algoritmo foram efetuados com recurso ao software MATLAB® , tendo as necessárias derivadas de estabilidade e controlo iniciais sido providenciadas pelo software XFLR5® . As equações de voo foram devidamente adaptadas para permitirem uma compatibilização com o sistema da asa telescópica e a sua integração nos métodos de controlo LQR e Batz-Kleinman. As qualidades de voo da aeronave foram devidamente definidas e impostas ao controlador para garantir a afinação da matriz de ponderação para valores ótimos. Por fim, o algoritmo foi sujeito a três tipos de testes e simulações: Simulação Clássica por meio de Imposição de Perturbações Atmosféricas, Teste de Resposta a uma Variação Sinusoidal do Ângulo de Arfagem, e Teste de Reposta a uma Variação Aleatória do Ângulo de Arfagem.
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Books on the topic "Wing spar"

1

Fish, Cheryl J. Wing span: Poems. Lewiston [N.Y.]: Mellen Poetry Press, 1992.

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Matthew, Accarrino, and Leahy Kate, eds. SPQR: Modern Italian food + wine. Berkeley: Ten Speed Press, 2012.

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Mehler, Felix Eckhart. The structural testing and modification of a full-scale ornithopter's wing spars. [Toronto]: Dept. of Aerospace Science and engineering, University of Toronto, 1997.

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Mehler, Felix Eckhart. The structural testing and modification of a full-scale ornithopter's wing spars. Ottawa: National Library of Canada = Bibliothèque nationale du Canada, 1999.

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Milholen, William E. Computational analysis of semi-span model test techniques. Hampton, Virginia: National Aeronautics and Space Administration, Langley Research Center, 1996.

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Archibald, Russell. Span of wings: Memoirs of a working life in aircraft design encompassing a span from biplanes to Concorde-Bristol fashion. Shrewsbury: Airlife, 1992.

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Rinoie, Kenichi. Experimental studies of vortex flaps and vortex plates. Part 1. 0.53m span 60 deg delta wing. Tokyo: National Aerospace Laboratory, 1992.

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Borri, Claudio, and Claudio Mannini, eds. Aeroelastic Phenomena and Pedestrian-Structure Dynamic Interaction on Non-Conventional Bridges and Footbridges. Florence: Firenze University Press, 2010. http://dx.doi.org/10.36253/978-88-6453-202-8.

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Fluid-structure and pedestrian-structure interaction phenomena are extremely important for non-conventional bridges. The results presented in this volume concern: simplified formulas for flutter assessment; innovative structural solutions to increase the aeroelastic stability of long-span bridges; numerical simulations of the flow around a benchmark rectangular cylinder; examples of designs of large structures assisted by wind-tunnel tests; analytical, computational and experimental investigation of the synchronisation mechanisms between pedestrians and footbridge structures. The present book is addressed to a wide audience including professionals, doctoral students and researchers, aiming to increase their know-how in the field of wind engineering, bluff-body aerodynamics and bridge dynamics.
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Millott, T. A. Vibration reduction in helicopter rotors using an actively controlled partial span trailing edge flap located on the blade. Moffett Field, Calif: Ames Research Center, 1994.

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Goodger, E. M. Transport fuels technology: From well to wheels, wings, and water. Norwich: Landfall Press, 2000.

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Book chapters on the topic "Wing spar"

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Wanhill, Russell, Simon Barter, and Loris Molent. "Aermacchi MB-326H Wing Spar (1990): Exponential FCG Analysis." In SpringerBriefs in Applied Sciences and Technology, 43–48. Dordrecht: Springer Netherlands, 2019. http://dx.doi.org/10.1007/978-94-024-1675-6_4.

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Main, Ben, Keith Muller, Michael Konak, Michael Jones, Sudeep Sudhakar, and Simon Barter. "Evaluation of a PC-9/A Wing Main Spar with Misdrills Using Enhanced Teardown at Resonance." In ICAF 2019 – Structural Integrity in the Age of Additive Manufacturing, 874–88. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-21503-3_70.

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Irez, A. B., E. Bayraktar, and I. Miskioglu. "Devulcanized Rubber Based Composite Design Reinforced with Nano Silica, Graphene Nano Platelets (GnPs) and Epoxy for “Aircraft Wing Spar” to Withstand Bending Moment." In Mechanics of Composite, Hybrid and Multifunctional Materials, Volume 5, 9–22. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-95510-0_2.

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Ge, Yaojun, and Hiroshi Tanaka. "Long-Span Bridge Aerodynamics." In Advanced Structural Wind Engineering, 85–120. Tokyo: Springer Japan, 2013. http://dx.doi.org/10.1007/978-4-431-54337-4_4.

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Gao, Binbin, Rongjie Kang, and Yan Chen. "Deployable Mechanism Design for Span Morphing Wing Aircraft." In Lecture Notes in Electrical Engineering, 801–13. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-2875-5_66.

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Barbanti, G., E. Marino, and C. Borri. "Mooring System Optimization for a Spar-Buoy Wind Turbine in Rough Wind and Sea Conditions." In Lecture Notes in Civil Engineering, 87–98. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-12815-9_7.

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Guerrero, Joel E. "Wake Signature of Finite-Span Flapping Rigid Wings." In High Performance Computing in Science and Engineering '10, 407–27. Berlin, Heidelberg: Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-15748-6_31.

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Zhang, Zhi-chun, Hong-wei Liu, and Guo-wen Huang. "Wind Turbine Spare Parts Management Based on Kanban System." In Proceedings of 20th International Conference on Industrial Engineering and Engineering Management, 1121–29. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-40063-6_110.

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Patil, Ajay H., and D. Karmakar. "Hydrodynamic Performance of Spar-Type Wind Turbine Platform Combined with Wave Energy Converter." In Lecture Notes in Civil Engineering, 115–23. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-8293-6_9.

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Rani, Neelam, Ajay Pratap, and Ashok K. Ahuja. "Wind Pressure Distribution on Multi-span Semi-circular Canopy Roofs." In Lecture Notes in Civil Engineering, 831–40. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-80312-4_71.

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Conference papers on the topic "Wing spar"

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Ajaj, Rafic M., Erick Saavedra Flores, and M. Friswell. "Variable Wing Span Using the Compliant Spar Concept." In 54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-1451.

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Lease, Kevin, Daniel Swenson, and Claire Stroede. "Fatigue Analysis of an Aircraft Wing Spar." In General, Corporate & Regional Aviation Meeting & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1999. http://dx.doi.org/10.4271/1999-01-1561.

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Wissa, Aimy, Joseph Calogero, James E. Hubbard, and Mary Frecker. "Stability Analysis of the Wing Leading Edge Spar of a Passively Morphing Ornithopter." In ASME 2014 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/smasis2014-7528.

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This paper presents a stability model for the wing leading edge spar of a test ornithopter. The long-term goal of this research effort is to passively improve the performance of ornithopters during steady level flight by implementing a set of wing kinematics found in natural flyers. The desired kinematics is achieved by inserting a compliant mechanism called a compliant spine into the wing leading edge spar to mimic the function of an avian wrist. The stiffness of the compliant spine is time varying and given the nature of flapping flight, it is periodic. Introducing a variable stiffness compliant mechanism into the leading edge spar of the ornithopter affects its structural stability. Therefore, a stability analysis is required. In order to start the stability analysis, an analytical model of the ornithopter wing leading edge spar with a compliant spine inserted in is necessary. In the model, the compliant spine is modeled as a torsional spring with a sinusoidal stiffness function. Moreover, the equations of motion of the wing leading edge spar-spine system can be written in the form of non-homogeneous Mathieu’s equations, which has well-known stability criteria. The analytical system response is then validated using experimental data taken at NASA Langley Research Center. Results show that the analytical spine angular deflection agrees with the experimental angular deflection data within 11%. Stability was then demonstrated using both analytical and graphical proving that the response of leading edge spar with a compliant spine design inserted at 37% of the wing half span is bounded.
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Silva, Carlos, Bruno Rocha, and Afzal Suleman. "A Metamodelling Optimization Approach to a Wing Spar Design." In 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
16th AIAA/ASME/AHS Adaptive Structures Conference
10t. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-1887.

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Anton, Steven, and Daniel Inman. "Electromechanical Modeling of a Multifunctional Energy Harvesting Wing Spar." In 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-2004.

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Calogero, Joseph, Mary Frecker, Zohaib Hasnain, and James E. Hubbard. "A Dynamic Spar Numerical Model for Passive Shape Change." In ASME 2015 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/smasis2015-8837.

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A three-dimensional constraint-driven numerical dynamic model of a flapping wing structure called the Dynamic Spar Numerical Model (DSNM) is introduced and implemented. The model currently includes a leading edge spar and a diagonal spar, attached to a body by revolute and spherical joints, respectively. The spars consist of a user-specified number of rigid links connected by compliant joints (CJs): spherical joints with distributed masses and three axis nonlinear torsional spring-dampers. The goal of this model is to quickly simulate mechanisms in a test platform to see how their CJ design properties and spatial distribution affect passive shape change and physical performance metrics. The results of this model can be used as a starting point for further refinement in compliant joint design for passive shape change. Previous research leading to and assumptions made for modeling CJ are presented. The constraints are established, followed by the formulation of a state model used in conjunction with a forward time integrator, and finally several example runs. Modeling the CJs as linear springs produces a nearly symmetric rotation angles through the flapping cycle, while bi-linear springs show the wing is able to flex more during upstroke than downstroke. Increasing damping ratio reduces high frequency oscillations during the flapping cycle and the number of cycles required to reach steady state. Coupling the spring stiffnesses allows an angle about one axis to induce an angle about another axis, where the magnitude is proportional to the coupling term. Modeling both the leading edge and diagonal spars show that the diagonal spar changes the kinematics of the leading edge spar verses only considering the leading edge spar, causing much larger axial rotations in the leading edge spar. The kinematics are very sensitive to CJ location, where moving the CJ toward the wing root causes a stronger response, and adding multiple CJs on the leading edge spar with a CJ on the diagonal spar allow the wing to deform with larger magnitude in all directions. Future work includes implementing a performance metric, experimental verification, applying loads to represent ambient and flight conditions, and using the model as an optimization tool for parameter and spatial optimization.
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Stacey, Benjamin J., and Peter Thomas. "Initial Analysis of a Novel Biomimetic Span-Wise Morphing Wing Concept." In ASME 2019 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/smasis2019-5567.

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Abstract Morphing wings and the adaptive systems they form have been developed significantly over recent decades. Increased efficiency and control performance can be achieved with their implementation, while advances in material technology, system integration and control, have allowed concepts to present a realistic alternative to fixed-wing and aft-tail aircraft. Set out in this paper is the preliminary design and development for a novel span-wise morphing concept which employs and heavily implements biomimetic design. Specifically, the skeletal structure of the bird wing by mimicking the humerus, ulna/radius, and carpometacarpus of birds of prey as they exhibit the most versatile wing shape enabling multiple manoeuvre and flight types. The concept comprises three sections corresponding to the skeletal structure, each consisting of a leading edge D-spar and an internal structural member onto which trailing edge plates are mounted. Pneumatic artificial muscle (PAM) actuators are presented as a drive for a biologically derived ‘drawing-parallels’ mechanism, through which a 75% semi-span length change and variable sweep angle, can be obtained. Analysis of initial CFD results is discussed in comparison with similar concepts in the field and a proposal for small scale wind tunnel verification put forward. While a rapid prototype is printed to confirm the viability of the concept.
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Araujo, Pablo M. N., Thiago R. Costa, and Eduardo C. Silva. "DESIGN AND MANUFACTURING PROCESS OF A UAV COMPOSITE WING SPAR." In Brazilian Conference on Composite Materials. Pontifícia Universidade Católica do Rio de Janeiro, 2018. http://dx.doi.org/10.21452/bccm4.2018.09.06.

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Blondeau, Julie, and Darryll Pines. "Wind Tunnel Testing of a Morphing Aspect Ratio Wing Using an Pneumatic Telescoping Spar." In 2nd AIAA "Unmanned Unlimited" Conf. and Workshop & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-6659.

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Moore, James, and Stephen Cutright. "Structural Analysis and Performance-Based Validation of a Composite Wing Spar." In AIAA Scitech 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-0548.

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Reports on the topic "Wing spar"

1

Moshier, Monty A. Ram Load Simulation of Wing Skin-Spar Joints: New Rate-dependent Cohesive Model. Fort Belvoir, VA: Defense Technical Information Center, January 2006. http://dx.doi.org/10.21236/ada448143.

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Sharp, Nathan, Rebecca Cutting, and Drew Sommer. Thermal Instability in the Manufacturing of Wind Turbine Blade Spar Caps. Office of Scientific and Technical Information (OSTI), June 2020. http://dx.doi.org/10.2172/1633432.

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Rarback, Harvey. Old Wine in New Bottles-The SPEAR Control System Upgrade. Office of Scientific and Technical Information (OSTI), October 1999. http://dx.doi.org/10.2172/15086.

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ER-20037 LLNL eternal pathfinder wing spar design study report. Office of Scientific and Technical Information (OSTI), March 1994. http://dx.doi.org/10.2172/10142966.

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Department of Energy Awards $43 Million to Spur Offshore Wind Energy, Wind Program Newsletter, September 2011 Edition (Brochure). Office of Scientific and Technical Information (OSTI), September 2011. http://dx.doi.org/10.2172/1027675.

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