Log in

Relevant bibliographies by topics / Aerospace structures / Dissertations / Theses

To see the other types of publications on this topic, follow the link: Aerospace structures.

Dissertations / Theses on the topic 'Aerospace structures'

Author: Grafiati

Published: 4 June 2021

Last updated: 23 February 2023

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the top 50 dissertations / theses for your research on the topic 'Aerospace structures.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Browse dissertations / theses on a wide variety of disciplines and organise your bibliography correctly.

1

Jenett, Benjamin (Benjamin Eric). "Digital material aerospace structures." Thesis, Massachusetts Institute of Technology, 2015. http://hdl.handle.net/1721.1/101837.

Full text

Abstract:

Thesis: S.M., Massachusetts Institute of Technology, Department of Civil and Environmental Engineering, 2015.<br>Cataloged from PDF version of thesis.<br>Includes bibliographical references (pages 71-76).<br>This thesis explores the design, fabrication, and performance of digital materials in aerospace structures in three areas: (1) a morphing wing design that adjusts its form to respond to different behavioral requirements; (2) an automated assembly method for truss column structures; and (3) an analysis of the payload and structural performance requirements of space structure elements made f

APA, Harvard, Vancouver, ISO, and other styles

2

Spendley, Paul R. "Design allowables for composite aerospace structures." Thesis, University of Surrey, 2012. http://epubs.surrey.ac.uk/810072/.

Full text

Abstract:

Recent developments in aircraft design have seen the Airbus A380 and the Boeing Dreamliner employ significant amounts of advanced composite materials. There is some thought however, und the motivation for this current work, that these materials continue to suffer a weight penalty. In this work tests required to generate design allowables which accommodate environmental effects and holes arc performed on Carbon/epoxy quasi-isotropic laminatcs. The test data is treated statistically to provide B-basis allowables for each specimen type and condition. It was seen that the notched specimens (coupon

APA, Harvard, Vancouver, ISO, and other styles

3

Hanuska, Alexander Robert Jr. "Thermal Characterization of Complex Aerospace Structures." Thesis, Virginia Tech, 1998. http://hdl.handle.net/10919/36617.

Full text

Abstract:

Predicting the performance of complex structures exposed to harsh thermal environments is a crucial issue in many of today's aerospace and space designs. To predict the thermal stresses a structure might be exposed to, the thermal properties of the independent materials used in the design of the structure need to be known. Therefore, a noninvasive estimation procedure involving Genetic Algorithms was developed to determine the various thermal properties needed to adequately model the Outer Wing Subcomponent (OWS), a structure located at the trailing edge of the High Speed Civil Transport's (

APA, Harvard, Vancouver, ISO, and other styles

4

White, Caleb, and caleb white@rmit edu au. "Health Monitoring of Bonded Composite Aerospace Structures." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2009. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20090602.142122.

Full text

Abstract:

Airframe assemblers have long recognised that for a new aircraft to be successful it must use less fuel, have lower maintenance requirements, and be more affordable. One common tactic is the use of innovative materials, such as advanced composites. Composite materials are suited to structural connection by adhesive bonding, which minimises the need for inefficient mechanical fastening. The aim of this PhD project was to investigate the application of existing, yet immature Structural Health Monitoring (SHM) techniques to adhesively bonded composite aerospace structures. The PhD study focu

APA, Harvard, Vancouver, ISO, and other styles

5

Zhang, Haochuan. "Nonlinear aeroelastic effects in damaged composite aerospace structures." Thesis, Georgia Institute of Technology, 1996. http://hdl.handle.net/1853/12150.

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

Navarro, Zafra Joaquin. "Computational mechanics of fracture on advanced aerospace structures." Thesis, University of Sheffield, 2016. http://etheses.whiterose.ac.uk/16883/.

Full text

Abstract:

In this thesis, the computational simulation of cracks in advanced composite structures subjected to biaxial loading is studied. A structural integrity analysis using the eXtended Finite Element Method (XFEM) is considered for simulating the crack behaviour of a chopped fibre-glass-reinforced polyester (CGRP) cruciform specimen subjected to a quasi-static tensile biaxial loading [99]. This is the first time this problem is accomplished for computing the stress intensity factors (SIFs) produced in the biaxially loaded area of the cruciform specimen. SIFs are calculated for infinite plates under

APA, Harvard, Vancouver, ISO, and other styles

7

Lam, Daniel F. "STRAIN CONCENTRATION AND TENSION DOMINATED STIFFENED AEROSPACE STRUCTURES." University of Akron / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=akron1145393262.

Full text

APA, Harvard, Vancouver, ISO, and other styles

8

Vishwanathan, Aditya. "Uncertainty Quantification for Topology Optimisation of Aerospace Structures." Thesis, University of Sydney, 2020. https://hdl.handle.net/2123/23922.

Full text

Abstract:

The design and optimisation of aerospace structures is non-trivial. There are several reasons for this including, but not limited to, (1) complex problem instances (multiple objectives, constraints, loads, and boundary conditions), (2) the use of high fidelity meshes which impose significant computational burden, and (3) dealing with uncertainties in the engineering modelling. The last few decades have seen a considerable increase in research output dedicated to solving these problems, and yet the majority of papers neglect the effect of uncertainties and assume deterministic conditions. This

APA, Harvard, Vancouver, ISO, and other styles

9

Pozegic, Thomas R. "Nano-modified carbon-epoxy composite structures for aerospace applications." Thesis, University of Surrey, 2016. http://epubs.surrey.ac.uk/809603/.

Full text

Abstract:

Carbon fibre reinforced plastics (CFRP) have revolutionised industries that demand high specific strength materials. With current advancements in nanotechnology there exists an opportunity to not only improve the mechanical performance of CFRP, but to also impart other functionalities, such as thermal and electrical conductivity, with the aim of reducing the reliance on metals, making CFRP attractive to many other industries. This thesis provides a comprehensive analysis of the nano-phase modification to CFRP by growing carbon nanotubes (CNTs) on carbon fibre (CF) and performing mechanical, el

APA, Harvard, Vancouver, ISO, and other styles

10

Sebastian, Christopher. "Towards the validation of thermoacoustic modelling in aerospace structures." Thesis, University of Liverpool, 2015. http://livrepository.liverpool.ac.uk/2012079/.

Full text

Abstract:

The research presented in this thesis has been performed over the course of three years under funding from the European Office of the United States Air Force (EAORD) as a part of a long-term project to collect high quality data for the validation of computational mechanics models of thermoacoustic loading. The focus is on the adaptation of stereoscopic (3D) Digital Image Correlation for use in a combined thermal and high temperature measurements. To that end, a background is provided which highlights the current state of the art in high temperature, vibration experiments and data acquisition.

APA, Harvard, Vancouver, ISO, and other styles

11

Zhou, Jin. "The energy-absorbing behaviour of novel aerospace composite structures." Thesis, University of Liverpool, 2015. http://livrepository.liverpool.ac.uk/2014139/.

Full text

Abstract:

The aim of this research is to investigate the structural response of PVC foam based sandwich structures, composite reinforced foam cores and fibre metal laminates (FMLs) subjected to quasi-static and dynamic loading conditions. It also includes the investigation of the mechanical properties and energy-absorbing characteristics of the novel hybrid materials and structures for their potential use in aerospace and a wide range of engineering applications. Firstly，a series of experimental tests have been undertaken to obtain the mechanical properties of all constituent materials and structural be

APA, Harvard, Vancouver, ISO, and other styles

12

McCrory, John. "Advanced Acoustic Emission (AE) monitoring techniques for aerospace structures." Thesis, Cardiff University, 2016. http://orca.cf.ac.uk/89212/.

Full text

Abstract:

This thesis contains the development of advanced Acoustic Emission (AE) monitoring techniques for aerospace structures. The techniques developed in this work explore AE’s ability to detect, locate and characterise signals. Experimental studies were conducted on a range of structures made from typical aerospace materials, including carbon fibre composite, GLARE and high grade steel; and the data collected from these studies was processed using the newly developed AE techniques, in order to determine their effectiveness. The work was divided into three main areas of research: 1. AE Source Locati

APA, Harvard, Vancouver, ISO, and other styles

13

Jefferson, Thomas G. "Reconfigurable assembly system design methodology for aerospace wing structures." Thesis, University of Nottingham, 2017. http://eprints.nottingham.ac.uk/42778/.

Full text

Abstract:

The aerospace industry is facing new challenges to meet burgeoning customer demand. An unprecedented number of orders for commercial aircraft has placed great urgency on aerospace manufacturers to make gains in production efficiency. Wing assembly is one such area where cycle times are in the order of hundreds of hours and commissioning cells can take several years which has led to a significant order backlog. In light of these challenges, new techniques are required to bring about greater agility to respond to market changes. Aerospace manufacturers must seize the opportunity to innovate and

APA, Harvard, Vancouver, ISO, and other styles

14

El-Nounu, AbdulRahman. "Redesign methodology for cost effective assembly of aerospace structures." Thesis, University of Nottingham, 2018. http://eprints.nottingham.ac.uk/51634/.

Full text

Abstract:

The research addresses the topic of design for assembly from an aerospace structures perspective. Aerospace assembly has traditionally taken secondary important to aircraft performance. This approach has been validated through healthy sales, most recently demonstrated in the Single Aisle market. However, in recent times, design for assembly has become more important. There are two main drivers behind this shift in focus. The first is a desire from aircraft manufacturers to maximise profits on existing aircraft orders through redesign. The second is the future outlook of aircraft sales, estimat

APA, Harvard, Vancouver, ISO, and other styles

15

Lim, Sang Seok. "Modeling and control of large space structures." Thesis, University of Ottawa (Canada), 1990. http://hdl.handle.net/10393/5822.

Full text

Abstract:

In this thesis a preliminary formulation of large space structures and their stabilization is considered. The system consists of a (rigid) massive body and flexible configurations which consist of several beams, forming the space structure. The rigid body is located at the center of the space structure and may play the role of experimental modules. A complete dynamics of the system has been developed using Hamilton's principle. Euler-Bernoulli, Rayleigh and Timoshenko beam theories are utilized to derive the dynamic equations governing the vibration of the beams. The equations that govern the

APA, Harvard, Vancouver, ISO, and other styles

16

Orifici, Adrian Cirino, and adrian orifici@student rmit edu au. "Degradation Models for the Collapse Analysis of Composite Aerospace Structures." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080619.090039.

Full text

APA, Harvard, Vancouver, ISO, and other styles

17

Qu, Shuang. "Multilevel optimisation of aerospace and lightweight structures incorporating postbuckling effects." Thesis, Cardiff University, 2011. http://orca.cf.ac.uk/55080/.

Full text

Abstract:

The optimisation of aerospace structures is a very complex problem, due to the hundreds of design variables a multidisciplinary optimisation may contain, so that multilevel optimisation is required. This thesis presents the recent developments to the multilevel optimisation software VICONOPT MLO, which is a multilevel optimisation interface between the well established analysis and design software packages VICONOPT and MSC/NASTRAN. The software developed is called VICONOPT MLOP (Multilevel Optimisation with Postbuckling), and allows for postbuckling behaviour, using analysis based on the Wittr

APA, Harvard, Vancouver, ISO, and other styles

18

Halbert, Keith. "Estimation of probability of failure for damage-tolerant aerospace structures." Thesis, Temple University, 2014. http://pqdtopen.proquest.com/#viewpdf?dispub=3623167.

Full text

Abstract:

<p> The majority of aircraft structures are designed to be damage-tolerant such that safe operation can continue in the presence of minor damage. It is necessary to schedule inspections so that minor damage can be found and repaired. It is generally not possible to perform structural inspections prior to every flight. The scheduling is traditionally accomplished through a deterministic set of methods referred to as Damage Tolerance Analysis (DTA). DTA has proven to produce safe aircraft but does not provide estimates of the probability of failure of future flights or the probability of

APA, Harvard, Vancouver, ISO, and other styles

19

Shengnan, Geng, Wang Xinglai, and Feng Hui. "FIBER BRAGG GRATING SENSOR SYSTEM FOR MONITORING COMPOSITE AEROSPACE STRUCTURES." International Foundation for Telemetering, 2016. http://hdl.handle.net/10150/624242.

Full text

Abstract:

To investigate strain-sensitive characteristics of fiber Bragg grating (FBG) sensors, a minimal sensing system consisting of multiplex FBG sensors and signal demodulating and processing instruments was constructed. FBG sensors were designed with different package structures for respectively sensing strain or temperature parameters, and they returned measurand-dependent wavelengths back to the interrogation system for measurement with high resolution. In this paper, tests were performed on structure samples with step-wise increase of deformations. Both FBG sensing system and strain gages

APA, Harvard, Vancouver, ISO, and other styles

20

Footdale, Joseph N. "Multi-axis real-time hybrid testing for precision aerospace structures." Connect to online resource, 2008. http://gateway.proquest.com/openurl?url_ver=Z39.88-2004&rft_val_fmt=info:ofi/fmt:kev:mtx:dissertation&res_dat=xri:pqdiss&rft_dat=xri:pqdiss:3337052.

Full text

APA, Harvard, Vancouver, ISO, and other styles

21

XIE, QIULIN. "PROBABILISTIC DESIGN OPTIMIZATION OF BUILT-UP AIRCRAFT STRUCTURES WITH APPLICATION." MSSTATE, 2003. http://sun.library.msstate.edu/ETD-db/theses/available/etd-07292003-211728/.

Full text

Abstract:

This thesis discusses a methodology for probabilistic design optimization of aircraft structures subject to a multidisciplinary set of requirements originating from the desire to minimize structural weight while fulfilling the demands for quality, safety, producibility, and affordability. With this design methodology as the framework, a software is developed, which is capable of performing design optimization of metallic built-up beam structures where the material properties, external load, as well as the structural dimensions are treated as probabilistic random variables. The structural and f

APA, Harvard, Vancouver, ISO, and other styles

22

Han, Yong. "Aeroelastic oscillations of damaged wing structures with bonded piezoelectric strips." Thesis, McGill University, 2013. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=116892.

Full text

Abstract:

This thesis examines a new method of detecting the presence of structural cracks in wing-like structures at an incipient stage. This method is based on the analysis of the dynamics of damaged structures with bonded piezoelectric strips executing flexural oscillations. Such oscillations can be generated by mechanical loads, piezoelectric actuators, or unsteady aerodynamic loads in certain flight conditions of the aircraft. The proposed method of crack detection uses pairs of piezoelectric strip sensors bonded on the opposite sides of the structure and is based on the fact that the presence of a

APA, Harvard, Vancouver, ISO, and other styles

23

Paget, Christophe. "Active Health Monitoring of Aerospace Composite Structures by Embedded Piezoceramic Transducers." Doctoral thesis, KTH, Aeronautical Engineering, 2001. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3277.

Full text

Abstract:

<p>The objectives of the thesis work were to study theinteraction between embedded piezoceramic transducers andcomposite structures as well as determine techniques tosimplify the Lamb waves analysis. Firstly, this studyconsidered the design of the embedded piezoceramic transducers.Secondly, the effect of the embedded transducer on thecomposite strength as well as the influence of the mechanicallyloaded composite on the characteristics of the embeddedtransducer were investigated. Finally, to simplify the analysisof such complex Lamb wave responses, two techniques weredeveloped. They were based

APA, Harvard, Vancouver, ISO, and other styles

24

Gunel, Murat. "Linear And Nonlinear Progressive Failure Analysis Of Laminated Composite Aerospace Structures." Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12614033/index.pdf.

Full text

Abstract:

This thesis presents a finite element method based comparative study of linear and geometrically non-linear progressive failure analysis of thin walled composite aerospace structures, which are typically subjected to combined in-plane and out-of-plane loadings. Different ply and constituent based failure criteria and material property degradation schemes have been included in a PCL code to be executed in MSC Nastran. As case studies, progressive failure analyses of sample composite laminates with cut-outs under combined loading are executed to study the effect of geometric non-linearity on the

APA, Harvard, Vancouver, ISO, and other styles

25

Elvin, Niell Glen. "Damage detection in civil and aerospace structures with fiber optic sensors." Thesis, Massachusetts Institute of Technology, 1995. http://hdl.handle.net/1721.1/37018.

Full text

Abstract:

Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Civil and Environmental Engineering, 1995, and Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1995.<br>Includes bibliographical references.<br>by Niell Glen Elvin.<br>M.S.

APA, Harvard, Vancouver, ISO, and other styles

26

Neri, Luca. "Negative Stiffness Structures: an additively manufactured design solution for aerospace applications." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2021. http://amslaurea.unibo.it/24997/.

Full text

Abstract:

The aim of this project is to investigate two damping structures based on negative stiffness behavior and realized by Additive Manufacturing in the rubber like material Tango Gray. The first structure is based on the circular geometry by Wang et al. and Corsi et al. This structure is obtained by a circular repetition of an unit cell based on a curved beam plane geometry. When the curved beam is loaded the buckling instability phenomenon appears and the collapse of the structure reduces the force reaction: the fast change of configuration is called snap-through behaviour. If after buckling the

APA, Harvard, Vancouver, ISO, and other styles

27

Martin, Oliver. "Metrology enabled tooling for the assembly of aero-structures." Thesis, University of Bath, 2016. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.690722.

Full text

Abstract:

Metrology and Tooling are considered as discrete disciplines within Manufacturing Engineering, however, assembly tooling often acts as a checking mechanism. Assembly tooling has the primary function of controlling part location during assembly; with a secondary requirement as a quality gate. In-tool checks are manual mechanical checks of the assembly, these gauging checks assume the tooling has the correct, nominal geometry. Tooling conformance is certified periodically; however these intervals can be up to three years. Further examination of the metrology requirements within the aerospace ind

APA, Harvard, Vancouver, ISO, and other styles

28

Fulcher, Jared T. "MECHANICAL CHARACTERIZATIONS OF ENVIRONMENTALLY CONDITIONED SHAPE MEMORY POLYMERS FOR RECONFIGURABLE AEROSPACE STRUCTURES." UKnowledge, 2011. http://uknowledge.uky.edu/gradschool_theses/81.

Full text

Abstract:

Shape memory polymers (SMPs) have been candidate materials for morphing applications. However, the SMPs have not been fully tested to work in relevant environments required for Air Force missions. In this study, an epoxy-based SMP was separately exposed to moisture, lubricating oil and UV radiation, which are simulated service environments designed to be reflective of anticipated performance requirements. The thermomechanical properties and shape memory effects were studied by using novel high-temperature nanoindentation technique. Results show that environmental conditions have affected the g

APA, Harvard, Vancouver, ISO, and other styles

29

Ginzburg, Dmitri. "Damage propagation and detection using nonlinear elastic wave spectroscopy in aerospace structures." Thesis, University of Bath, 2016. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.698994.

Full text

Abstract:

The sustainable future of aerospace industry in large part relies on two factors: (i) development of advanced damage tolerant materials and (ii) the ability to detect and evaluate defects at very early stages of component service life. The use of laminated composite materials, such as carbon fibre reinforced plastics (CFRP), has had a significant contribution to reducing airframe weight while improving passenger safety and comfort. However, it is well known that these materials exhibit poor resistance to impact damage caused by foreign objects. Inspired by the naturally occurring impact resist

APA, Harvard, Vancouver, ISO, and other styles

30

Tomko, Jason Robert. "Fluid-loaded vibration of thin structures due to turbulent excitation." Thesis, University of Notre Dame, 2014. http://pqdtopen.proquest.com/#viewpdf?dispub=3583070.

Full text

Abstract:

<p> Flow-induced structural acoustics involves the study of the vibration of a structure induced by a fluid flow as well as the resulting sound generated and radiated by the motion of the system. The thesis examines several aspects of flow-induced structural vibration for fluid-loaded systems. A new method, termed Magnitude-Phase Identification, is derived to experimentally obtain a modal decomposition of the vibration of a structure using two-point measurements. MPI was used to measure the auto-spectral density of various modes for a non-fluid-loaded, rectangular, clamped plate excited by a s

APA, Harvard, Vancouver, ISO, and other styles

31

Ekren, Mustafa. "Structural Optimization Strategies Via Different Optimization And Solver Codes And Aerospace Applications." Master's thesis, METU, 2008. http://etd.lib.metu.edu.tr/upload/12610250/index.pdf.

Full text

Abstract:

In this thesis, structural optimization study is performed by using three different methods. In the first method, optimization is performed using MSC.NASTRAN Optimization Module, a commercial structural analysis program. In the second method, optimization is performed using the optimization code prepared in MATLAB and MSC.NASTRAN as the solver. As the third method, optimization is performed by using the optimization code prepared in MATLAB and analytical equations as the solver. All three methods provide certain advantages in the solution of optimization problems. Therefore, within the context

APA, Harvard, Vancouver, ISO, and other styles

32

Meshreki, Mouhab. "Dynamics of thin-walled aerospace structures for fixture design in multi-axis milling." Thesis, McGill University, 2009. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=32614.

Full text

Abstract:

Milling of thin-walled aerospace structures is a critical process due to the high flexibility of the workpiece. Available models for the prediction of the effect of the fixture on the dynamic response of the workpiece are computationally demanding and fail to represent practical cases for milling of thin-walled structures. Based on the analysis of typical structural components encountered in the aerospace industry, a generalized unit-element, with the shape of an asymmetric pocket, was identified to repre

APA, Harvard, Vancouver, ISO, and other styles

33

Njuguna, James A. K. "Micro- and macro-mechanical properties of aerospace composite structures and their dynamic behaviour." Thesis, City University London, 2006. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.440734.

Full text

APA, Harvard, Vancouver, ISO, and other styles

34

Christian, William J. R. "The development of a strain-based defect assessment technique for composite aerospace structures." Thesis, University of Liverpool, 2017. http://livrepository.liverpool.ac.uk/3010051/.

Full text

Abstract:

This thesis details the work conducted over three years on the development of strain-based defect assessment techniques for carbon-fibre reinforced composites. This material, whilst exhibiting a high specific strength, is sensitive to defects and thus there is an industrial need for assessment techniques that are capable of characterising defects and obtaining predictions of residual strength or life. The most commonly applied techniques are currently ultrasonic and thermographic non-destructive evaluation. A strain-based defect assessment could lead to more accurate predictions of residual st

APA, Harvard, Vancouver, ISO, and other styles

35

Horton, Brandon Alexander. "Comprehensive Multi-Scale Progressive Failure Analysis for Damage Arresting Advanced Aerospace Hybrid Structures." Diss., Virginia Tech, 2017. http://hdl.handle.net/10919/93961.

Full text

Abstract:

In recent years, the prevalence and application of composite materials has exploded. Due to the demands of commercial transportation, the aviation industry has taken a leading role in the integration of composite structures. Among the leading concepts to develop lighter, more fuel-efficient commercial transport is the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept. The highly integrated structure of PRSEUS allows pressurized, non-circular fuselage designs to be implemented, enabling the feasibility of Hybrid Wing Body (HWB) aircraft. In addition to its unique fabrication

APA, Harvard, Vancouver, ISO, and other styles

36

Kapidzic, Zlatan. "Strength analysis and modeling of hybrid composite-aluminum aircraft structures." Licentiate thesis, Linköpings universitet, Hållfasthetslära, 2013. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-91894.

Full text

Abstract:

The current trend in aircraft design is to increase the proportion of fiber composites in the structures. Since many primary parts also are constructed using metals, the number of hybrid metal-composite structures is increasing. Such structures have traditionally often been avoided as an option because of the lack of methodology to handle the mismatch between the material properties. Composite and metal properties differ with respect to: thermal expansion, failure mechanisms, plasticity, sensitivity to load type, fatigue accumulation and scatter, impact resistance and residual strength, anisot

APA, Harvard, Vancouver, ISO, and other styles

37

Deaton, Joshua D. "Design of Thermal Structures using Topology Optimization." Wright State University / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=wright1401302982.

Full text

APA, Harvard, Vancouver, ISO, and other styles

38

Chatla, Priyanjali. "LS-Dyna for Crashworthiness of Composite Structures." University of Cincinnati / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1352993298.

Full text

APA, Harvard, Vancouver, ISO, and other styles

39

Lenahan, Kristie M. "Thermoelastic control of adaptive composites for aerospace applications using embedded nitinol actuators." Thesis, Virginia Tech, 1996. http://hdl.handle.net/10919/44955.

Full text

Abstract:

<p>Aerospace structures have stringent pointing and shape control requirements during long-term exposure to a hostile environment with no scheduled maintenance. This makes them excellent candidates for a smart structures approach as current passive techniques prove insufficient. This study investigates the feasibility of providing autonomous dimensional control to aerospace structures by embedding shape memory alloy elements inside composite structures. Increasing volume fractions of nitinol wire were embedded in cross-ply graphite/ epoxy composite panels. The potential of this approach was ev

APA, Harvard, Vancouver, ISO, and other styles

40

Kececi, Erkan. "Highly durable hydrophobic thin films for moisture prevention of composite structures for aerospace applications." Diss., Wichita State University, 2012. http://hdl.handle.net/10057/6096.

Full text

APA, Harvard, Vancouver, ISO, and other styles

41

Chronopoulos, Dimitrios. "Prediction of the vibroacoustic response of aerospace composite structures in a broadband frequency range." Phd thesis, Ecole Centrale de Lyon, 2012. http://tel.archives-ouvertes.fr/tel-00787864.

Full text

Abstract:

During its mission, a launch vehicle is subject to broadband, severe, aeroacoustic and structure-borne excitations of various provenances, which can endanger the survivability of the payload and the vehicles electronic equipment, and consequently the success of the mission. Aerospace structures are generally characterized by the use of exotic composite materials of various configurations and thicknesses, as well as by their extensively complex geometries and connections between different subsystems. It is therefore of crucial importance for the modern aerospace industry, the development of ana

APA, Harvard, Vancouver, ISO, and other styles

42

Mullan, Matthew Noel. "Understanding cost drivers within an aerospace manufacturing supply chain for fibre reinforced plastic structures." Thesis, Queen's University Belfast, 2013. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.602691.

Full text

Abstract:

Increasingly stringent emission targets has encouraged prime airframe assemblers to reduce aircraft weight, in doing so reducing CO2 emissions associated with fuel burn. All three major aircraft manufacturers have chosen to achieve this by incorporating greater proportions of advanced composite material within aircraft structural design. This research presents the development of a novel approach to simultaneously model continuous and discontinuous production processes, enabling new understanding of composite material production cost drivers within an aerospace manufacturing supply chain. The s

APA, Harvard, Vancouver, ISO, and other styles

43

Mohammed, Mohammed Abdelaziz Elamin. "IMPACT AND POST IMPACT RESPONSE OF COMPOSITE SANDWICH STRUCTURES IN ARCTIC CONDITION." University of Akron / OhioLINK, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=akron1518520473027006.

Full text

APA, Harvard, Vancouver, ISO, and other styles

44

Wild, Graham. "Distributed optical fibre smart sensors for acoustic sensing in the structural health monitoring of robust aerospace vehicles." Thesis, Edith Cowan University, Research Online, Perth, Western Australia, 2010. https://ro.ecu.edu.au/theses/1873.

Full text

Abstract:

The use of distributed optical fibre smart sensors for the detection of acoustic signals in the Structural Health Monitoring (SHM) of robust aerospace vehicles has been demonstrated. Current distributed optical fibre sensors are multiplexed along a single fibre. Inherent problems exist with a multiplexed architecture. Two significant issues are; the possibility of fibre breakage, and the possibility of failure of the single transmitter, the single receiver, or the single processor. In a ‘smart’ architecture, the intelligence, as well as the sensors, is distributed. Hence, if destructive damage

APA, Harvard, Vancouver, ISO, and other styles

45

McEwan, Matthew Ian. "A combined modal/finite element technique for the non-linear dynamic simulation of aerospace structures." Thesis, University of Manchester, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.504961.

Full text

Abstract:

The surface panels of modern high-speed aircraft are subjected to high-intensity acoustic loading from sources such as jet efflux and turbulent fluid flow. The vibration induced by this loading may result in fatigue crack growth near stress concentrations, and may eventually cause in-service failure of the structure. Central to the acoustic fatigue design problem is knowledge of the dynamic response of the structure in questions, so that some fatigue damage model may be applied in order to determine the fatigue life of the structure. In this thesis, a combined normal mode /finite element techn

APA, Harvard, Vancouver, ISO, and other styles

46

Doyle, Keith Brian. "An optimization method for the design of structures for maximum fundamental frequency." Diss., The University of Arizona, 1993. http://hdl.handle.net/10150/186321.

Full text

Abstract:

An optimization method to maximize the fundamental frequency of a structure is developed. The procedure uses the stresses due to the mechanical loading and the free-vibration mode shapes to determine design coefficients for the elements. Each element of the structure is assigned a design coefficient rated on a scale of zero to ten. The design coefficients are used to modify an initial design following an iterative procedure. This method of optimal structural design, referred to as the Maximum Stiffness Design (MSD), may be classified as an intuitive optimality criteria method. The MSD method i

APA, Harvard, Vancouver, ISO, and other styles

47

Khalili, Ashkan. "Spectrally formulated user-defined element in Abaqus for wave motion analysis and health monitoring of composite structures." Thesis, Mississippi State University, 2017. http://pqdtopen.proquest.com/#viewpdf?dispub=10269016.

Full text

Abstract:

<p> Wave propagation analysis in 1-D and 2-D composite structures is performed efficiently and accurately through the formulation of a User-Defined Element (UEL) based on the wavelet spectral finite element (WSFE) method. The WSFE method is based on the first order shear deformation theory which yields accurate results for wave motion at high frequencies. The wave equations are reduced to ordinary differential equations using Daubechies compactly supported, orthonormal, wavelet scaling functions for approximations in time and one spatial dimension. The 1-D and 2-D WSFE models are highly effici

APA, Harvard, Vancouver, ISO, and other styles

48

Moses, Mychal-Drew. "A Study on the Micro Electro-Discharge Machining of Aerospace Materials." TopSCHOLAR®, 2015. http://digitalcommons.wku.edu/theses/1448.

Full text

Abstract:

Electrical Discharge Machining (EDM) is a non-traditional machining process that uses hundreds of thousands of minute electrical sparks per second to machine any electrically conductive material, no matter the hardness or how delicate it is. EDM allows a much greater range of design possibilities, unconstrained from the traditional machining processes, in which material is removed mechanically by either rotating the cutting tool or the work piece. Shapes that were impossible to machine by any other method, such as deep, precision, square holes and slots with sharp inside corners, are readily p

APA, Harvard, Vancouver, ISO, and other styles

49

Culler, Adam John. "Coupled Fluid-Thermal-Structural Modeling and Analysis of Hypersonic Flight Vehicle Structures." The Ohio State University, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=osu1280930589.

Full text

APA, Harvard, Vancouver, ISO, and other styles

50

Kral, Zachary Tyler. "Development of a decentralized artificial intelligence system for damage detection in composite laminates for aerospace structures." Diss., Wichita State University, 2013. http://hdl.handle.net/10057/10612.

Full text

Abstract:

Because of economic impact that results from downtime, aircraft maintenance is an important issue in the aerospace industry. In-service structures will decay over time. Compared to low-cycle loading structures, aerospace structures experience extreme loading conditions, resulting in rapid crack propagation. The research involved in this dissertation concerns development of the initial stages of structural health monitoring (SHM) system that includes a network of ultrasonic testing sensors with artificial intelligence capable of detecting damage before structure failure. A series of experiments

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!