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Browsing Aerospace by Subject "'Aerospace Engineering'"
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Item Open Access A Benchtop Flight Control Demonstrator - Data and Code(Cranfield University, 2019-09-10 09:28) Duran, Joris; Whidborne, James; Pontillo, Alessandro; alejandro Carrizales rodriguez, MartinCodes and data for "A benchtop flight control demonstrator" J R Duran, J F Whidborne, M Carrizales Rodriguez, A Pontillo International Journal of Mechanical Engineering Education Published online July 27, 2019 doi: 10.1177/0306419019852688CodesFlight-Desk-Control-Demonstrator-master.zip - GUI on a computer programmed in JAVA - PID Controller for ArduinoExperimental Results- Test open loop.xls- Test P.xls- Test PID.xlsFluent CFD Fileswindtunnel.casWindtunnel.jouWindtunnel_refine.meshdatJavaFoil filescriptJaveFoilMicrosoft Excel Windtunnel design worksheetWind Tunnel Design V2.xlsmCATIA CAD filesCAD-CATIA.zipMSc DissertationDuran JR. Flight Desk Control Demonstrator. MSc dissertation, Cranfield University, Bedfordshire, U.K., 2018. Available at: http://dspace.lib.cranfield.ac.uk/handle/1826/14154Item Open Access Assessment of Turbulence Models for Transonic / Supersonic Smooth Surface Separation(Cranfield University, 2021-06-21 13:14) Prince, Simon; González caballero, Roberto; Di Pasquale, DavideA systematic comparison of the principle modern turbulence prediction methods for the solution of the Navier-Stokes equations for the calculation of high speed flows about slender forebodies at low to moderate angle of attack is presented. This class of flow involves smooth surface turbulent boundary layer separation resulting in steady symmetric leeside vortices, and also the formation of embedded shock waves from the displacement effect of the large vortices in supersonic flow. As such this flow is both complex and highly sensitive to the state of the boundary layers on the body. This study revealed that the method which most consistently provides accurate predictions of the overall forces and moments on the body, the most accurate distribution of surface pressure and can most accurately resolve the flow features, including leeside vortices and embedded shock wave features, is the Solution Adaptive Simulation method. Detached Eddy Simulation and the Reynold Stress Model, which would be expected to provide superior accuracy over the RANS based linear eddy viscosity models, on the whole, failed to provide better predictions. In fact, the k-omega Realizable and k-omega SST turbulence models provided data which was almost as consistently accurate as the Solution Adaptive Simulation method. The standard k-omega turbulence model appears to be completely unsuitable for the computation of this class of high speed flow problem, and this may be associated with the poor initial / default prescription of the value of omega at the far-field boundary.Item Open Access Civil Transport Aircraft Evolvability Data(Cranfield University, 2018-10-15 13:44) Van Heerden, Stevan; Guenov, Marin; Molina-Cristobal, ArturoThis is an appendix to the paper `Evolvability and Design Reuse in Civil Jet Transport Aircraft', by A.S.J. van Heerden, Marin D. Guenov, and Arturo Molina-Cristobal. It contains data that was used to create the plots and figures in Sections 6, 7, and 8 of the paper.Item Open Access Conceptual and preliminary design methods for use on conventional and blended wing body airliners(Cranfield University, 2019-02-19 11:40) Smith, Howard; Fielding, JohnTranscript of John Fielding and Howard Smith's 1999 lecture to Court, Cranfield University.Item Open Access Data supporting: 'Development of a thermal excitation source used in an active thermographic UAV platform'(Cranfield University, 2022-08-31 16:49) Deane, Shakeb; Tsourdos, Antonios; Avdelidis, Nico; Zolotas, Argyrios; P. V. Maldague, Xavier; Ibarra-Castanedo, Clemente; Genest, Marc; Pant, Shashank; Williamson, Alex; Withers, Stephen; Ahmadi, MohammadaliThis work aims to address the effectivenessand challenges of using active infrared thermography (IRT) on-board an unmannedaerial vehicle (UAV) platform. The work seeks to assess the performance ofsmall low powered forms of excitation which are suitable for activethermography and the ability to locate subsurface defects on composites. Anexcitation source in the form of multiple 250 W lamps are mounted onto a UAVand are solely battery powered with a remote trigger to power cycle them.Multiple experiments address the interference from the UAV whilst performing anactive IRT inspection. The optimal distances and time required for a UAV inspection using IRT is calculated. Multiple signal processing techniques areused to analyse the composites which helps locate the sub-surface defects. It was observedthat a UAV can successfully carry the required sensors and equipment for anActive thermographic NDT inspection which can provide access to difficult areas. Most active thermographic inspection equipment is large, heavy, and expensive. Furthermore, using such equipment for inspection of complexstructures is time-consuming. For example, a cherry picker would be required toinspect the tail of an aircraft. This solution looks to assist engineersinspecting complex composite structures and could potentially significantly reduce the time and cost of a routine inspection.Item Open Access Data supporting: 'Ground Vibration Testing of a Flexible Wing: A Benchmark and Case Study'(Cranfield University, 2023-05-04 16:22) Dessena, GabrieleThis CORD entry contains the experimental data underlying the journal article Ground Vibration Testing of a Flexible Wing: A Benchmark and Case Study published in Aerospace by MDPI. The document XB-2_Dataset.pdf serves as the explanatory note for the data contained in data_xb2.matItem Open Access Data supporting: 'MDAO method and optimum designs of hybrid-electric civil airliners'(Cranfield University, 2022-09-05 10:00) Kang, LeThe data is ready to be shared with readers who read the paper 'MDAO method and optimum designs of hybrid-electric civil airliners', which is published on the 'Journal of Aerospace Engineering'. The data includes validation information as well as case study data in this paper. The paper introduced a design environment appropriate to hybrid-electric civil airliners.Item Open Access Dataset for the publication: "Coupon scale Z-pinned IM7/8552 delamination tests under dynamic loading"(Cranfield University, 2019-08-27 15:00) Cui, Hao; R. Hallett, Stephen; Mahadik, Yusuf; K. Patridge, Ivana; Allegri, Giuliano; Anusuya Ponnusami, Sathiskumar; Petrinic, NikDatasets for a paper published in Composites Part A: Applied Science and Manufacturinghttps://doi.org/10.1016/j.compositesa.2019.105565The quasi-static tests were done at velocity of around 0.01mm/sDynamic tests were conducted at norminal velocity of around 4m/s, some of the WDCB tests were done at 7m/s.Item Open Access DFA/MOST results(Cranfield University, 2017-01-06 15:41) Judt, David; Lawson, Craig;; Lockett, HelenResults for the empirical analysis of the assembly tasks using DFA and basic MOSTItem Open Access New solutions for old problems(Cranfield University, 2018-10-18 10:05) Pontillo, Alessandro3 Minute Thesis presented at the Cranfield Doctoral Network Annual Event, September 2018.Highly flexible structures are now a common scenario in the aeronautic industry due to the adoption of slender and longer wings in order to reduce drag and increase the overall aircraft efficiency. Such configuration brings new challenges as structural dynamics now overlaps flight dynamics. Testing is then more important than ever. The Cranfield BEam Reduction and Dynamic Scaling (BEARDS) programme aims to provide a numerical and experimental tool able to dynamically scale-down a full aircraft and to test it successfully in the wind tunnel. Being able to predict static response along with structure dynamics, allows either universities and industry to mitigate the risk of testing bigger and more expensive models. The presentation will focus on the BEARDS methodology, results obtained from tests already done in the Weybridge wind tunnel and on the future of the programme with the new designed eXperimental Beards (XB-2) model.Item Open Access Power Gearbox and Pitch Control Mechanism for Open Rotors - Investigation of Preliminary Design Methodologies(Cranfield University, 2018-10-18 10:00) guiomar San benito pastor, DianaPoster presented at the Cranfield Doctoral Network Annual Event, September 2018.The expected result of this PhD research is a design methodology that would allow establishing the feasibility of a pusher counter-rotating open rotor (CROR) engine architecture, taking into account both performance and mechanical integrity aspects. The analysis will consider the preliminary design of the main technology enablers, i.e. the advanced power gearbox (PGB) and the pitch change mechanism (PCM), delving into sizing, mechanical integrity aspects and optimal positioning of the components within the propulsion system. The study will then be extended to assess: Design for performance through simulated flight trajectory assessments over selected missions; Lifing aspects of the components and their implication on maintenance costs; Economic benefits through a financial viability analysis. A key requirement is to optimize these objectives by determining the minimum size of the power transmission system of the CROR engine to transmit power from the free turbine to the counter-rotating propellers. This requirement will need to be met without compromising its mechanical integrity nor the overall performance of the engine.Item Open Access Raw post experiment preference data(Cranfield University, 2017-01-06 15:41) Judt, David; Lawson, Craig;; Lockett, HelenRaw data of participant responses to ranking the position preference order.Item Open Access Raw time results(Cranfield University, 2017-01-06 15:41) Judt, David; Lawson, Craig;; Lockett, HelenRaw data for the wing D-nose aircraft system assembly time trialsItem Open Access The Effect of Rotor Tilt on the Stability and Gust Rejection Properties of VTOL Multirotor Aircraft - MATLAB Codes(Cranfield University, 2022-01-04 11:11) Whidborne, JamesVideo visualization and MATLAB files and routines to generate figures, video and some results of paper "The Effect of Rotor Tilt on the Stability and Gust Rejection Properties of VTOL Multirotor Aircraft" by James F. Whidborne, Arthur Mendez and Alastair CookeRun the script MultiRotorGust.m to generate all the figures & the video in the paper.