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Relevant bibliographies by topics / Aeronautical Engineering

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Academic literature on the topic 'Aeronautical Engineering'

Author: Grafiati

Published: 4 June 2021

Last updated: 29 July 2024

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Journal articles on the topic "Aeronautical Engineering"

1

Gudín de la Lama, Enrique. "Emilio Herrera Linares, artífice de la ingeniería aeronáutica española." Llull Revista de la Sociedad Española de Historia de las Ciencias y de las Técnicas 46, no. 92 (November 25, 2023): 39–67. http://dx.doi.org/10.47101/llull.2023.46.92.gudin.

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The beginnings of Spanish aeronautics are linked to the biography of Emilio Herrera, a leading figure among the pioneers of aviation in Spain. Despite the research that has been done on him, his role in the genesis of aeronautical engineering as an area of knowledge with its own identity remained to be explored. Herrera’s work in this field took place at the same time as the birth and growth of this speciality and was oriented —as the subsequent evolution of the decisions he had taken showed— in the right direction. His management work in the Aerodynamic Laboratory, in the commission for the homologation of aeronautical engineering degrees, in the creation of the School of Engineers and in the Association of Aeronautical Engineers were key to the birth and consolidation of Spanish aeronautical engineering. This article highlights the initiatives and decisions taken, and to what extent they contributed to institutionalizing Spanish aeronautical engineering.

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Ackroyd, J. A. D. "The Victoria University of Manchester’s contributions to the development of aeronautics." Aeronautical Journal 111, no. 1122 (August 2007): 473–93. http://dx.doi.org/10.1017/s0001924000004735.

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This issue of the Aeronautical Journal celebrates the 50th anniversary of the foundation of the Honours Degree Course in Aeronautical Engineering at the Victoria University of Manchester. The following article therefore describes the aeronautical research and teaching activities of that university up to its recent amalgamation with the University of Manchester Institute of Science and Technology (UMIST) to form the present-day University of Manchester. This juncture provides a further justification for recording the Victoria University’s achievements.Both the Victoria University and UMIST had their roots in the nineteenth century although, apart from the relatively brief period of the First World War, neither of them was particularly involved in aeronautics until after the Second World War. However, as Sections 6.0-10.0 seek to demonstrate, thereafter the Victoria University’s involvement became considerable. The preceding Sections describe the origins of the Victoria University and UMIST and, in the case of the former institution, the subsequent activities of its staff and graduates in engineering and mathematics which, although not always specifically aeronautical in content, nonetheless had a profound influence on the development of the aeronautical sciences.

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Ackroyd, J. A. D., L. Bernstein, and F. W. Armstrong. "One hundred years of aeronautics in East London." Aeronautical Journal 112, no. 1133 (July 2008): 357–80. http://dx.doi.org/10.1017/s0001924000002335.

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This paper celebrates the centenary of Queen Mary College’s involvement in aeronautics, a celebration with a unique distinction since it was this College’s immediate forebear which was the first British higher education institution to begin teaching and research in this subject. Thus the emphasis is on the early years from 1907 until the 1950s, a period ripe for recording before it recedes beyond living memory, but also the period during which the degree course in aeronautical engineering became firmly established and its parent Department acquired its reputation for research. Section 2.0 gives a brief history of the College’s origins in the East London College. Subsequent sections deal with the foundation of the aeronautical laboratory there, from which the aeronautical department grew, and the activities of the two men who led these developments, A.P. Thurston and N.A.V. Tonnstein who changed his name to Piercy.

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Allen, J. E. "Aeronautics-1903; aerospace-2003; ? ? 2103." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 219, no. 3 (March 1, 2005): 235–60. http://dx.doi.org/10.1243/095441005x30252.

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The centenary of the first manned flight was a unique occasion permitting a rare opportunity to range far into both the past and the future. Most of aeronautics must inevitably be focussed on the near future and immediate actions. However, there are some very long-term underlying issues which are invisible from a day-to-day perspective, but which should not be overlooked as they can be used very often to guide decisions that might otherwise be unsound. In Part 1, the paper reviews the major breakthroughs that have impelled aeronautics along a startling trajectory of success, with some mention of the uncertain beginnings, when even Wilbur Wright considered that all his aerodynamic theories were in a muddle. In that spirit, in Part 2, some attempts are made to anticipate possible breakthroughs that might happen in the 21st century. However, aeronautics does not stand alone. Considerations, such as other transport modes, energy substitution, non-vehicular transport, and the consequences of major global political alignments, will be reviewed in order to seek new aeronautical challenges of the future. Some other long-term, but non-aeronautical engineering, initiatives relevant to the IMechE are introduced and discussed in the appendix

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Lemco, Ian. "Wittgenstein's aeronautical investigation." Notes and Records of the Royal Society 61, no. 1 (December 22, 2006): 39–51. http://dx.doi.org/10.1098/rsnr.2006.0163.

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After a rigorous German education in the physical sciences, young Ludwig Wittgenstein entered Manchester University as an aeronautical engineering research student. There he devised and patented a novel aero-engine employing an airscrew propeller driven by blade tip-jets. Within the context of the growth of English aviation during the first half of the twentieth century (including the contributions of many Fellows of the Royal Society) and taking into account related aspects of his life, this paper examines an unfulfilled engineering aspiration. In enlarging upon what Wittgenstein might have accomplished during his stay at Manchester, it contrasts his invention with later comparable proven designs, albeit applied to hybrid rotorcraft. His engine employed centrifugal flow compression and arguably was a precursor of Sir Frank Whittle's gas turbine. In conclusion, reasons are given for Wittgenstein's departure from Manchester.

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Bearman, Peter. "Special Issue of The Aeronautical Journal, marking the 150th Anniversary of the Founding of the Royal Aeronautical Society." Aeronautical Journal 120, no. 1223 (January 2016): 1–2. http://dx.doi.org/10.1017/aer.2015.1.

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This special issue is one of a number of activities taking place this year to celebrate the founding of the Royal Aeronautical Society in 1866. The decision to form the Society was taken on 12 January 1866 at a meeting of distinguished people held in London and chaired by the Duke of Argyll. One of those present, James Glaisher, addressed the gathering and it is interesting to revisit an extract from his statement: “The first application of the balloon as a means of ascending into the upper regions of the atmosphere has been almost within the recollection of men now living but with the exception of some of the early experimenters it has scarcely occupied the attention of scientific men, nor has the subject of aeronautics been properly recognised as a distinct branch of science. . .”. The meeting resolved “that it is desirable to form a Society for the purpose of increasing by experiments our knowledge of Aeronautics and for other purposes incidental thereto and that a Society be now formed under the title of the ‘Aeronautical Society of Great Britain’ to be supported by annual subscriptions and donations.”

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Goetzendorf-Grabowski, Tomasz. "Multi-disciplinary optimization in aeronautical engineering." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 12 (May 12, 2017): 2305–13. http://dx.doi.org/10.1177/0954410017706994.

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Nowadays, optimization is a very popular tool used to improve existing projects. The optimization covers different disciplines by linking them into multidisciplinary process of design. Existing software tools allow to very effectively solve particular problems giving high quality solutions which were previously very hard to achieve. Aeronautical engineering is a domain/field which links many disciplines: aerodynamics, stability, control, structural analysis, materials, propulsion systems, avionics, etc. Therefore, the multidisciplinary optimization results in very significant progress not only in aircraft design but also in air transport, which links technical aspects with economical questions. The paper presents selected aspects of using the multidisciplinary optimization in aeronautical engineering with special focus on multidisciplinary aircraft design.

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Klemin, Alexander. "TRAINING AND RESEARCH IN AERONAUTICAL ENGINEERING." Journal of the American Society for Naval Engineers 46, no. 4 (March 18, 2009): 527–30. http://dx.doi.org/10.1111/j.1559-3584.1934.tb02575.x.

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Arti, Endang Sugih, Elfi Amir, Dini Wagini, Togi Adnan Maruli, Ferry Budi Cahyono, Agustono Agustono, and Rini Sadiatmi. "Sosialisasi Program Studi Penerangan Aeronautika Di SMA Negeri 3 Kabupaten Tangerang." Jurnal Pengabdian Kepada Masyarakat (JPKM) Langit Biru 5, no. 01 (March 1, 2024): 1–5. http://dx.doi.org/10.54147/jpkm.v5i01.866.

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Kegiatan Pengabdian Kepada Masyarakat (PKM) ini didasarkan pada UU No. 20 Tahun 2003 tentang Sistem Pendidikan Nasional dan PERPRES No. 68 tahun 2022 tentang Revitalisasi Pendidikan Vokasi. PPI Curug merupakan salah satu perguruan tinggi vokasi dibawah Kementerian Perhubungan yang dekat /mudah aksesnya, biaya relatif terjangkau, jangka waktu pendidikan relative cepat dengan menghasilkan lulusan siap kerja dengan pemberian bekal kompetensi / keterampilan lapangan. PKM ini dilaksanakan dalam bentuk sosialiasi dan bertujuan untuk lebih mengenalkan program studi D.III Penerangan Aeronautika di PPI Curug yang lulusannya akan bekerja di dunia penerbangan dan bertugas menyampaikan informasi penerbangan dalam bentuk self-briefing, Notam (Notice To Airmen), AIP (Aeronautical Information Publication, Aeronautical chart/peta) kepada siswa SMAN 3 Tangerang. Diharapkan dengan penjelasan ini peserta PKM akan termotivasi dan tumbuh minatnya untuk memilih melanjutkan pendidikannya di PPI Curug, terutama pada Prodi D.III Penerangan Aeronautika. Kegiatan berjalan lancar dan animo siswa SMAN 3 Kabupaten Tangerang sangat tertarik dengan PPI Curug terbukti dengan banyaknya pertanyaan yang diajukan.

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Pertiwi, Dewanti Ratna. "Needs Analysis of English for Aeronautical Engineering Purposes at STT Adisutjipto Yogyakarta." LLT Journal: A Journal on Language and Language Teaching 19, no. 2 (January 9, 2017): 105–14. http://dx.doi.org/10.24071/llt.v19i2.304.

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In the context of ESP, needs analysis is the first step to develop a program. Needs analysis is conducted to investigate the present students mastery and the need of the future work field. This study aims to investigate the needs analysis of English for aeronautical engineering. The study employed a survey technique in the form of distributing questionnaires and interview for the lecturers, and centre of quality insurance. Indonesian qualification framework to standardize the graduate of aeronautical engineering with the national criteria is used as the source of developing the research instruments. The result of the study is expected to be able to build the foundation of developing better English course for aeronautical engineering students.DOI: https://doi.org/10.24071/llt.2016.190205

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Dissertations / Theses on the topic "Aeronautical Engineering"

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Ivliev. "SPACE X’S ROCKET CONCEPTS – STEP FORWARD IN AERONAUTICAL ENGINEERING." Thesis, Київ 2018, 2018. http://er.nau.edu.ua/handle/NAU/33718.

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Guiho, Audren. "Design, development and use of a mechanism simulator for aeronautical engineering." Thesis, KTH, Flygdynamik, 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-244830.

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This paper deals with the strategy for developing a very specific mechanism simulator. This mechanism is currently designed by Safran Group. A previous version of the same mechanism does exist but the scale is not on a like-for-like basis. Therefore, physical phenomena involved in this mechanism and their magnitude are not comparable to the previous version of the mechanism and this is why a new simulator has been developed (specified, coded and validated) from scratch. The paper addresses the strategy adopted for modelling a mechanism laying on a wide set of parameters as well as its use.
Artikeln handlar om en strategi som mål bestå av att utveckla en särskild simulator mekanism, för närvarande utformad av Safran Group. Det finns en tidigare version av samma mekanismen men systemskalor är inte i en like-for-like grund. Alltså, fysiska fenomenen som innebärs i mekanismen och deras magnitud kan inte jämföras med tidigare versionen av systemet. Det är varför en ny simulator har skrivits i kod. Artikeln analyserar strategin som adopterades för att utforma ett system som lägger på en bred uppsättning parametrar.

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Frogget, Jacob William. "Automatic Modulation Recognition for Aeronautical Telemetry." BYU ScholarsArchive, 2013. https://scholarsarchive.byu.edu/etd/3826.

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This these explores automatic modulation recognition as applied to PCM/FM, SOQPSK- TG and ARTM CPM. It found that the likelihood based approach is intractable. The statistical features of the amplitude, phase and frequency are ineffective at distinguishing these modulation types. A method based on the phase changes between symbols is developed and shows that as long as symbol timing is established, this method can effectively distinguish PCM/FM, SOQPSK-TG and ARTM CPM for signal-to-noise ratios above 30 dB. Another method, the Bianchi-Loubaton- Sirven technique, was able to distinguish PCM/FM and SOQPSK-TG but was unable to distinguish ARTM CPM. A happy byproduct of this classification algorithm is a reasonably accurate estimate of the bit rate. Simulation results show that this classifier works essentially error-free for signal- to-noise ratios above 20 dB and for sufficiently high resolution in the search algorithms required by the maximizations.

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Haque, Jamal. "An OFDM Based Aeronautical Communication System." Scholar Commons, 2011. http://scholarcommons.usf.edu/etd/3143.

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Wireless connectivity is becoming an integral part of our society. A new paradigm for aeronautical data services is beginning to take shape. The advances in signal processing, rapid prototyping, an insatiable consumer demand for Internet services, increase in aircraft traffic, aircraft safety, etc., are driving the demand for high speed data services. Programs led by the National Aeronautics and Space Administration (NASA), the Federal Aviation Administration (FAA), EUROCONTROL and Networking the Sky for Civil Aeronautical Communications (NEWSKY) are all looking into aeronautical platforms as part of their Aeronautical Data Network (ADN). The desire is to provide low delay, cost effective and high speed data connectivity for aeronautical platforms. The platforms can also be used as a relay for ground and airborne nodes. Such a capability could potentially provide data connectivity to remote areas. Most of the current high altitude platforms, i.e., aircraft, provide data connectivity through a satellite. However, satellite resources are limited and expensive, and they offer limited data throughput as compared to a terrestrial network. A potential solution is connectivity to ground stations that can provide high speed physical layers. Since the frequency spectrum is a valuable estate and needs to be used efficiently, the use of spectrum efficient techniques are evaluated. This dissertation discusses issues and challenges for developing a high speed ground based physical layer for aircraft and proposes a novel solution. A detailed analytical analysis is presented to show the issues related to aeronautical channel and its impacts to aeronautical communication system. Specifically, the impact of Doppler shifts that limit the use of efficient modulation schemes, such as Orthogonal Frequency Division Multiplexing (OFDM), is presented. OFDM is sensitive to Doppler shifts. In addition, Doppler spread and shifts in aeronautical channels depict different characteristics compared to terrestrial networks, i.e., multiple Doppler shifts xi and delays. Parametric techniques are investigated to accurately estimate the Doppler shifts. The results of parametric methods for estimating the Doppler shifts are presented. The simulation results of MUltiple Signal Classification (MUSIC), Eigenvector (EV) and Minimum norm methods are considered for an aeronautical channel and their performances is presented.

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Gagakuma, Edem Coffie. "Multipath Channel Considerations in Aeronautical Telemetry." BYU ScholarsArchive, 2017. https://scholarsarchive.byu.edu/etd/6529.

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This thesis describes the use of scattering functions to characterize time-varying multipath radio channels. Channel Impulse responses were measured at Edwards Air Force Base (EAFB) and scattering functions generated from the impulse response data. From the scattering functions we compute the corresponding Doppler power spectrum and multipath intensity profile. These functions completely characterize the signal delay and the time varying nature of the channel in question and are used by systems engineers to design reliable communications links. We observe from our results that flight paths with ample reflectors exhibit significant multipath events. We also examine the bit error rate (BER) performance of a reduced-complexity equalizer for a truncated version of the pulse amplitude modulation (PAM) representation of SOQPSK-TG in a multipath channel. Since this reduced-complexity equalizer is based on the maximum likelihood (ML) principle, we expect it to perform optimally than any of the filter-based equalizers used in estimating received SOQPSK-TG symbols. As such we present a comparison between this ML detector and a minimum mean square error (MMSE) equalizer for the same example channel. The example channel used was motivated by the statistical channel characterizations described in thisthesis. Our analysis shows that the ML equalizer outperforms the MMSE equalizer in estimating received SOQPSK-TG symbols.

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Alroqi, Abdurrhman Atig. "Investigation of the heat and wear of aircraft landing gear tyres." Thesis, University of Sussex, 2017. http://sro.sussex.ac.uk/id/eprint/68761/.

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In aircraft, the main landing gear wheels skid on the runway at the moment of touchdown because of high slip. A slipping tyre generates enough heat to melt its rubber. Melted rubber is easily eroded by the friction force between the tyre and runway; and part of eroded rubber stays on the runway, and other is burnt off as smoke. Since the early days of airplane use, a number of ideas have been patented to improve tyre safety and decrease the substantial wear and smoke during every landing by spinning the gear wheels before touchdown. In this thesis, there are three parts of research work. First part is to find the effectiveness of the technique of pre-spinning the wheel to reduce the tyre tread heat and wear, and then choosing the initial wheel rotation speed that prevent the tread rubber from melting temperature. For achieving this, a coupled structural – thermal transient analysis in ANSYS has been used to model a single wheel main landing gear as a mass-spring system. This model has been chosen to analyze the wheel's dynamic behaviour and tyre tread temperature and wear during the short period from static to a matching free-rolling velocity in which the wheel is forced to accelerate by the friction between the tyre and ground. The tyre contact surface temperature and wear have been calculated for both the initially static and pre-spun wheels in order to compare the temperature and wear levels for different initial rotation speeds. In the second part, the required torque to spin the aircraft wheel to the required angular speed at approach speed has been calculated using ANSYS CFX, which is used to determine the wheel aerodynamic forces developed by simulation of fluid flows in a virtual environment. In the last part, several types of wind turbines have been simulated.

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Alkandri, Ahmad. "Design and performance assessment of correlation filters for the detection of objects in high clutter thermal imagery." Thesis, University of Sussex, 2014. http://sro.sussex.ac.uk/id/eprint/49954/.

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The research reported in this thesis has examined means of enhancing the performance of the Optimal Trade-off Maximum Average Correlation Height (OT-MACH) filter for target detection in Forward Looking Infra-Red (FLIR) imagery acquired from a helicopter and border security FLIR camera in northern Kuwait. The data acquired with these FLIR sensors allows real-world evaluation of the comparative performance of the various filters that have been developed in the thesis. The results obtained have been quantified using well known performance measures such as Peak to Side-lobe Ratio (PSR) and Total Detection Error (TDE). The initial focus was to study the effect of modifying the OT-MACH parameters on the correlation metrics. A new optimisation technique has been presented, which computes statistically the filter alpha parameter associated with controlling the response of the filter to clutter noise. A further modification of the OT-MACH filter performance using the Difference of Gaussian bandpass filter (named the D-MACH filter) as a pre-processing stage has been described. The D-MACH has been applied to several test images containing single and multiple targets in the scene. Enhanced performance of the modified filter is demonstrated with improved metrics being obtained with less false side peaks in the correlation plane, especially when multiple targets are present in the test images. A further pre-processing technique was investigated using the Rayleigh distribution as a pre-processing filter (named the R-MACH filter). The R-MACH filter has been applied to multiple target types with tests conducted across various image data sets. The filter demonstrated an improvement over the Difference of Gaussian filter in terms of 6 reducing the number of parameters needing to be tuned whilst producing further enhanced correlation plane metrics. Finally, recommendations for future work has been made to improve the use of the OT-MACH filter in target detection and identification. A novel training image representation is proposed for further investigation, which will minimise the computational intensity of using the MACH filter for unconstrained object recognition.

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Bramer, Elinor C. "Development of a particle in cell code for the simulation of dual stage ion thrusters." Thesis, University of Sussex, 2014. http://sro.sussex.ac.uk/id/eprint/48913/.

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This thesis focuses on the design, development and testing of a two dimensional particle in cell (PIC) code (PICSIE) written in Matlab. The code is applied to the specific problem of modelling the performance of dual stage ion thrusters. The code simulates one full aperture within dual stage ion thruster systems, focusing on the flow of ions through the aperture. Only the ions have been included in the simulation in order to minimize running time. The results produced by the simulation code are compared with results obtained from the vacuum chamber testing of the DS4G prototype, along with results from other simulation codes and research papers in order to verify the performance of the simulation code. The Dual-Stage 4-Grid (DS4G) and Dual-Stage 3-Grid (DS3G) thrusters are both sim- ulated in order to compare the performance of the two thrusters and assess the benefits and disadvantages of including the fourth grid in a dual stage thruster system. Different grid configurations are simulated in order to find the most efficient configuration of the ion optics and accelerating voltages for each thruster, with the aim being to find the con- figurations that produce the maximum particle momentum, thrust and specific impulse while minimizing the rate of erosion of the ion optics and maximising the efficiency of the thruster. These simulations are applied to the problem of deciding if the advantages provided in using a 4th grid outweigh the disadvantages compared to the 3 grid design. The results show that if erosion due to backstreaming ions is disregarded, including the fourth grid in the thruster design results in no apparent advantages in terms of the perfor- mance parameters studied in this work. The only noticeable difference between the three and four grid cases is a significant increase in the change in ion momentum observed when the fourth grid is not included in the design. The conclusion of the work is that the fourth grid should not be included in the dual stage design unless a very long lifetime is required and it is thought that erosion due to backstreaming will prevent the three grid thruster from fulfilling this criteria. The concept of propagating waves through the plasma within the ion thruster discharge chamber is investigated, with the aim of discovering any benefits and improvements in performance that may arise and forming a conclusion on whether further study on the topic of waves within the discharge chamber may be beneficial. No improvements in per- formance parameters were observed in this work, although further study in the area may show benefits to introducing waves into the plasma.

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Langari, Mostafa. "Large eddy simulation of separated boundary layer transition under free-stream turbulence." Thesis, University of Sussex, 2014. http://sro.sussex.ac.uk/id/eprint/48940/.

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Physics of laminar-to-turbulent transition in a separated-reattached flow subjected to two free-stream turbulence levels have been explored using Large-Eddy Simulation (LES). Separation of the laminar boundary layer occurs at a curvature change over a flat plate with a semi-circular leading edge. A numerical trip has been used to generate the targeted free-stream turbulence levels. A dynamic Sub-grid-scale (SGS) model has been employed and excellent agreement has been achieved between the LES results and the experimental data. Detailed investigation of the LES data has been carried out to explore the primary instability mechanism at low (< 0.2%) and high free-stream turbulence (5.6%). The flow visualisations and spectral analysis of the separated shear layer reveal that the two-dimensional Kelvin-Helmholtz instability mode, well known to occur at low free-stream turbulence levels, is bypassed at a higher level leading to earlier breakdown to turbulence. The whole transition process leading to breakdown to turbulence has been revealed clearly by the flow visualisations and the differences between the low and high free-stream turbulence cases are clearly evident. Coherent structures are also visualised using iso-surfaces of the Q-criterion and for the high free-stream turbulence case the spanwise oriented two-dimensional rolls, which are clearly apparent in the low free-stream turbulence case, are not visible anymore. Detailed quantitative comparisons between the present LES results against experimental data and the previous LES results at low free-stream turbulence using a staggered grid have been done and a good agreement has been obtained, indicating that the current LES using a co-located grid with pressure smoothing can predict transitional flows accurately. Comprehensive spectral analysis of the separated shear layer at two free-stream turbulence levels has been performed. Under very low free-stream turbulence condition, a distinct regular vortex shedding and trace of the low-frequency flapping phenomena were detected. Under the higher free-stream turbulence however, a mild high-frequency activity was observed. No low frequency oscillations could be detected.

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Shaw, Christopher G. "Modulation and Synchronization for Aeronautical Telemetry." BYU ScholarsArchive, 2014. https://scholarsarchive.byu.edu/etd/3971.

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Aeronautical telemetry systems have historically been implemented with constant envelope modulations like CPM. Shifts in system constraints including reduced available bandwidth and increased throughput demands have caused many in the field to reevaluate traditional methods and design practices. This work examines the costs and benefits of using APSK for aeronautical telemetry instead of CPM. Variable rate turbo codes are used to improve the power efficiency of 16- and 32-APSK. Spectral regrowth in nonlinear power amplifiers when driven by non-constant envelope modulation is also considered. Simulation results show the improved spectral efficiency of this modulation scheme over those currently defined in telemetry standards. Additionally, the impact of transitioning from continuous transmission to burst-mode is considered. Synchronization loops are ineffective in burst-mode communication. Data-aided feed forward algorithms can be used to estimate offsets in carrier phase, frequency, and symbol timing between the transmitter and the receiver. If a data-aided algorithm is used, a portion of the transmitted signal is devoted to a known sequence of pilot symbols. Optimum pilot sequences for the three synchronization parameters are obtained analytically and numerically for different system constraints. The alternating sequence is shown to be optimal given a peak power constraint. Alternatively, synchronization can be accomplished using blind algorithms that do not rely on a priori knowledge of a pilot sequence. If blind algorithms are used, the observation interval can be longer than for data-aided algorithms. There are combinations of pilot sequence length and packet length where data-aided algorithms perform better than blind algorithms and vice versa. The conclusion is that a sequential arrangement of blind algorithms operating over an entire burst performs better than a CRB-achieving data-aided algorithm operating over a short pilot sequence.

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Books on the topic "Aeronautical Engineering"

1

Laudański, Ludomir M. Computational probability for aeronautical engineering. Warsaw: Institute of Aviation Scientific Library, 2002.

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T, Leondes Cornelius, ed. Advances in aeronautical systems. San Diego: Academic Press, 1990.

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Eastburg, Steven R. An engineering study of altitude determination deficiencies of the Service Aircraft Instrumentation Package (SAIP). Monterey, California: Naval Postgraduate School, 1991.

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Burke, Mary V. Profiles--aeronautical/astronautical engineering: Human resources and funding. Washington, D.C: National Science Foundation, 1989.

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Burke, Mary V. Profiles--aeronautical/astronautical engineering: Human resources and funding. Washington, D.C: National Science Foundation, 1989.

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United States. Naval Air Systems Command, ed. AED aeronautical engineering duty officer: Career planning guide. Washington, DC: Naval Air Systems Command, 1989.

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Burke, Mary V. Profiles--aeronautical/astronautical engineering: Human resources and funding. Washington, D.C: National Science Foundation, 1989.

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Burke, Mary V. Profiles--aeronautical/astronautical engineering: Human resources and funding. Washington, D.C: National Science Foundation, 1989.

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Burke, Mary V. Profiles--aeronautical/astronautical engineering: Human resources and funding. Washington, D.C: National Science Foundation, 1989.

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Burke, Mary V. Profiles--aeronautical/astronautical engineering: Human resources and funding. Washington, D.C: National Science Foundation, 1989.

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Book chapters on the topic "Aeronautical Engineering"

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Williatte, Philippe, Alexandre Durupt, Sebastien Remy, and Matthieu Bricogne. "Reverse Engineering for Aeronautical Products:." In Lecture Notes in Mechanical Engineering, 377–87. Cham: Springer International Publishing, 2023. http://dx.doi.org/10.1007/978-3-031-23615-0_39.

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Jafer, Shafagh, Umut Durak, Hakan Aydemir, Richard Ruff, and Thorsten Pawletta. "Advances in Software Engineering and Aeronautics." In Advances in Aeronautical Informatics, 87–102. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-75058-3_7.

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Atkins, Ella M. "Aerospace Engineering Curricular Expansion in Information Systems." In Advances in Aeronautical Informatics, 135–51. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-75058-3_10.

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Sulaiman Al Amri, Nasser. "Effective Utilization of Aeronautical Engineering Training Aids." In Proceedings of the First International Conference on Aeronautical Sciences, Engineering and Technology, 380–85. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-7775-8_41.

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Beligni, Alessio, Kamil Kowalczyk, Claudio Sbarufatti, and Marco Giglio. "An Impact Monitoring System for Aeronautical Structures." In Lecture Notes in Civil Engineering, 636–46. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-64594-6_62.

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Jiang, Hui, Huayuan Zhu, Jie Yu, and Kai Zhang. "Development of Nondestructive Testing for Aeronautical Composite Structures." In Lecture Notes in Electrical Engineering, 469–80. Berlin, Heidelberg: Springer Berlin Heidelberg, 2014. http://dx.doi.org/10.1007/978-3-642-54233-6_52.

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Llanos, Iñigo, Arkaitz Beristain, Jose Luis Lanzagorta, and Hendric Matzat. "Case Study 2.3: Distortions in Aeronautical Structural Parts." In Lecture Notes in Production Engineering, 99–115. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-45291-3_6.

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Mozzillo, Rocco, Ferdinando Vitolo, Paola Iaccarino, and Pasquale Franciosa. "Tolerance Prediction for Determinate Assembly Approach in Aeronautical Field." In Lecture Notes in Mechanical Engineering, 229–40. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-31154-4_20.

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Mathlouthi, Safa. "Improvement of the Quality of Aeronautical Products Stelia Tunisia." In Lecture Notes in Mechanical Engineering, 743–51. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-27146-6_81.

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Groth, Corrado, Marco Evangelos Biancolini, Emiliano Costa, and Ubaldo Cella. "Validation of High Fidelity Computational Methods for Aeronautical FSI Analyses." In Flexible Engineering Toward Green Aircraft, 29–48. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-36514-1_3.

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Conference papers on the topic "Aeronautical Engineering"

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Terent'ev, V. B. "Experimental determination of probabilistic indicators aeronautical engineering." In Наука России: Цели и задачи. LJournal, 2019. http://dx.doi.org/10.18411/sr-10-04-2019-80.

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Nielsen, Milton C., and Steven A. Brandt. "Software Simulations for Problem-Based Aeronautical Engineering Education." In World Aviation Congress & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1997. http://dx.doi.org/10.4271/975637.

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Albero, Vicente, and Carmen Ibáñez. "Content review using Kahoot! with aeronautical engineering students." In Fourth International Conference on Higher Education Advances. Valencia: Universitat Politècnica València, 2018. http://dx.doi.org/10.4995/head18.2018.8158.

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In the framework of the subject “Analysis of aeronautical structural components” included in the Master of Science of Aeronautical Engineering at the Universitat Politècnica de València, the application Kahoot! is employed in order to review the technical content and obtain feedback of the level of knowledge acquired by the students. Kahoot! allows developing multiple choice interactive quizzes that are solved in the classroom. Using this type of tools enhances the attention of the students and helps to create interesting discussions making the students be part of the teaching-learning process. Besides, the platform allows analyzing the results of the technical content reviewed which, in turn, permits the lecturer to adapt the didactic material to a real scenario. Furthermore, the results obtained from the assessment survey show the high level of satisfaction of the students with an activity which allows them to learn in a fun way. In conclusion, the application of Kahoot! for content review helps to perfect the teaching-learning process and improves academic performance in an attractive and engaging environment.

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Byerley, A., T. Scully, and J. Bertin. "An undergraduate-centered research program in aeronautical engineering." In 40th AIAA Aerospace Sciences Meeting & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-1047.

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Nielsen, Milton, Steven Brandt, Milton Nielsen, and Steven Brandt. "Software simulations for problem-based aeronautical engineering education." In 1997 World Aviation Congress. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-5637.

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Aleksejenko, Ivars, and Maris Kalinka. "Geodetic database for aeronautical purpose." In The 9th International Conference "Environmental Engineering 2014". Vilnius, Lithuania: Vilnius Gediminas Technical University Press “Technika” 2014, 2014. http://dx.doi.org/10.3846/enviro.2014.185.

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Catapane, G. "Acoustic metamaterial design for aeronautical purposes." In Aerospace Science and Engineering. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902677-14.

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Abstract. Labyrinth-shape quarter wavelength tubes are numerically studied under plane wave excitation, with analytical comparison. These labyrinth resonators (LRs) are tuned at 60, 90 and 120 Hz, and their sound absorption response exhibits maximum peak at those frequencies with high fidelity and performance. These objects can absorb tonal sources at very low frequencies, with an incredibly competitive thickness, resulting in the possibility of considering them for the design of acoustic liners for an aerospace engine, but also for the automotive and naval industries. They are put together to form an acoustic metamaterial which exhibits multiple tonal peaks, demonstrating that the performance of each resonator is not affected by their coupling.

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Kecskemety, Krista M., and Rachel Kajfez. "Aeronautical and Astronautical Engineering and Mechanical Engineering Major Movement to Graduation." In 2018 AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0809.

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Kecskemety, Krista M., and Rachel L. Kajfez. "Aeronautical and Astronautical Engineering Major Selection in First-Year Engineering Students." In 54th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1805.

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Tomita, Jesuino Takachi, João Roberto Barbosa, and Cleverson Bringhenti. "The Flow Machines Course at the Technological Institute of Aeronautics for Mechanical-Aeronautical Engineering Undergraduate Course." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-95228.

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Undergraduate courses at Technological Institute of Aeronautics (ITA) are 5-years course, divided into Fundamental (2 years) and Professional (3 years). The Flow Machines, in the Mechanical-Aeronautical Engineering Course, is offered by the Turbomachines Department and is taught in the first semester of the fourth year (2nd professional year). In the course, the basic theory, unified for all machines, is presented in details for the students, emphasizing the physics of all processes involved in the fluid-machine energy transfer. Incompressible and compressible fluids are treated accordingly. The flow machines types are individually studied, focusing attention to their performance characteristics and range of applications. The preliminary design and off-design operation issues are discussed in details with the students, with emphasis on relevant aspects of each machine, like cavitation, stall and surge. The students are taught on how to choose the flow properties at the blade edges for the sake of preliminary design and off-design performance estimations. Loss models are introduced during the theory classes and popular models are presented. At this point, in-house computer codes and commercial software are presented to the students, who are asked to solve simple problems. The installation, operation and basic performance calculations are also presented for the students during the lab classes for several hydraulic machines installed at ITA laboratories. All course material is transferred for the students in pdf format before classes. In this work, the experience with the teaching process in flow machines at ITA, theory and laboratory, is described.

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Reports on the topic "Aeronautical Engineering"

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Haas, David J., Eric J. Silberg, and Judah H. Milgram. Birth of U.S. Naval Aeronautical Engineering and Phenomenal Rise to Excellence. Fort Belvoir, VA: Defense Technical Information Center, December 2011. http://dx.doi.org/10.21236/ada558168.

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Silberg, Eric J., and David J. Haas. Developing the Navy's NC Flying Boats: Transforming Aeronautical Engineering for the First Transatlantic Flight. Fort Belvoir, VA: Defense Technical Information Center, December 2011. http://dx.doi.org/10.21236/ada558169.

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Bidier, S., U. Khristenko, R. Tosi, R. Rossi, and C. Soriano. D7.3 Report on UQ results and overall user experience. Scipedia, 2021. http://dx.doi.org/10.23967/exaqute.2021.9.002.

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This deliverable report focuses on the main Uncertainty Quanti cation (UQ) results obtained within the EXAscale Quanti cation of Uncertainties for Technology and Science Simulation (ExaQUte) project. Details on the turbulent wind inlet generator, that enables the supply of random, yet steady, wind velocity boundary conditions during run-time, are given in section 2. This enables the developed UQ workflow, whose results are presented on the basis of the Commonwealth Advisory Aeronautical Council (CAARC) as described in Deliverable 7.1. Finally, the completed UQ workflow and the results are evaluated from an application-driven wind engineering point of view. Thereby, the significance of the developed methods and the obtained results are discussed and their applicability in practical wind-engineering applications is tested through a complete test-run of the UQ workflow.

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Platzer, Max F., and Raymond P. Shreeve. Summary of Research 2001, Department of Aeronautics and Astronautics, Graduate School of Engineering and Applied Sciences. Fort Belvoir, VA: Defense Technical Information Center, September 2002. http://dx.doi.org/10.21236/ada415406.

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Pisani, William, Dane Wedgeworth, Michael Roth, John Newman, and Manoj Shukla. Exploration of two polymer nanocomposite structure-property relationships facilitated by molecular dynamics simulation and multiscale modeling. Engineer Research and Development Center (U.S.), March 2023. http://dx.doi.org/10.21079/11681/46713.

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Polyamide 6 (PA6) is a semi-crystalline thermoplastic used in many engineering applications due to good strength, stiffness, mechanical damping, wear/abrasion resistance, and excellent performance-to-cost ratio. In this report, two structure-property relationships were explored. First, carbon nanotubes (CNT) and graphene (G) were used as reinforcement molecules in simulated and experimentally prepared PA6 matrices to improve the overall mechanical properties. Molecular dynamics (MD) simulations with INTERFACE and reactive INTERFACE force fields (IFF and IFF-R) were used to predict bulk and Young's moduli of amorphous PA6-CNT/G nanocomposites as a function of CNT/G loading. The predicted values of Young's modulus agree moderately well with the experimental values. Second, the effect of crystallinity and crystal form (α/γ) on mechanical properties of semi-crystalline PA6 was investigated via a multiscale simulation approach. The National Aeronautics and Space Administration, Glenn Research Center's micromechanics software was used to facilitate the multiscale modeling. The inputs to the multiscale model were the elastic moduli of amorphous PA6 as predicted via MD and calculated stiffness matrices from the literature of the PA6 α and γ crystal forms. The predicted Young's and shear moduli compared well with experiment.

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