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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.
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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Cerutti, Xavier, and Katia Mocellin. "Prediction of Post-Machining Distortion Due to Residual Stresses Using FEM and a Massive Removal Approach." Key Engineering Materials 611-612 (May 2014): 1159–65. http://dx.doi.org/10.4028/www.scientific.net/kem.611-612.1159.
In aeronautics weight reduction of aircrafts has become one of the main objectives. This has led to the fact that a majority of the aeronautical parts made from aluminium are large monolithic parts (to avoid the use of assembling systems like rivets and screws). The manufacturing of these aeronautic parts, especially the structural parts, is usually performed by machining. On large aluminium aeronautical parts, the main factor which can lead to non-compliance of a part is the re-equilibrium of the initial residual stresses inside the workpiece during the machining process. In this paper, an example of multi-sided machining of a part made of AIRWARE® 2050 alloy is realised. Simulations of the machining of this part have been performed using a specific finite element tool which has been specially developed to predict the distortion due to the redistribution of these initial residual stresses during machining. Results numerically obtained are then compared with experimental results, showing a good agreement.
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Popov, Aleksey Vladimirovich, and Olga Dmitrievna Fedotova. "Training of lower officers in the Russian system of military aviators' training of the late 19th – early 20th century." KANT 38, no. 1 (March 2021): 321–25. http://dx.doi.org/10.24923/2222-243x.2021-38.67.
The article analyzes the issues of training military aeronauts in the late 19th – early 20th century in Russia. It is shown that the emergence of new technical means providing ascent into the airspace has opened up new possibilities for conducting military operations, as evidenced by the experience of using aeronautics abroad. The Russian command did not immediately realize the possibilities of conducting reconnaissance and conducting artillery fire on the enemy, which led to a lag in the development of aeronautics and aeronautics, as well as in training personnel for flight support. The article shows that for the training of officers and lower ranks in the Russian army, special units were created in which the lower ranks were taught special subjects that guarantee the production of safe flights due to their technical support.
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Yuniarti, Endah, Mufti Arifin, Amat Chaeroni, and Syaiful Rifki. "Peningkatan Motivasi Belajar Siswa SMK Tentang Aeronautics Science Melalui Metode Demonstrasi Mini Wind Tunnel di SMK Angkasa 01 Halim Perdanakusuma." JURNAL Comunità Servizio : Jurnal Terkait Kegiatan Pengabdian kepada Masyarakat, terkhusus bidang Teknologi, Kewirausahaan dan Sosial Kemasyarakatan 5, no. 2 (September 14, 2023): 1305–16. http://dx.doi.org/10.33541/cs.v5i2.4700.
Pada kurikulum Sekolah Menengah Kejuruan (SMK) Penerbangan, khususnya pada Mata Pelajaran Fisika terdapat dasar ilmu Aeronautika yaitu Dinamika Fluida. Salah satu kendala dalam mempelajari Dinamika Fluida adalah penggambaran yang sulit dan alat peraga yang jarang. Salah satu alat peraga yang sesuai dan digunakan di dunia penerbangan adalah wind tunnel. Kegiatan pengabdian kepada masyarakat berupa demonstrasi dan pendampingan pembuatan mini wind tunnel yang telah dilakukan dapat menjadi solusi permasalahan miskonsepsi materi Dinamika Fluida pada siswa SMK Angkasa 01 Halim Perdanakusuma. Kegiatan dilakukan dengan metode survey mengenai profil miskonsepsi materi Dinamika Fluida, demonstrasi prinsip Bernoulli, dan pendampingan pembuatan mini wind tunnel. Kegiatan diikuti oleh siswa kelas X dan XI yang dilaksanakan tanggal 14 sampai 20 Juni 2022 yang terbagi dalam 2 (dua) sesi yaitu demonstrasi wind tunnel dan pendampingan pembuatan mini wind tunnel. Pengukuran tingkat pemahaman Aeronautics Science dilakukan 3 (tiga) kali yaitu sebelum dan sesudah demonstrasi dan sesudah pendampingan pembuatan mini wind tunnel. Hasil kuesioner pertama yaitu sebagian besar siswa belum mempelajari Dinamika Fluida. Hasil kuesioner kedua cukup signifikan, dimana pengetahuan Aeronautics Science bertambah setelah mengikuti kegiatan PKM. Hasil kuesioner ketiga memperoleh kesimpulan bahwa telah terjadi perubahan tingkat pengetahuan Aeronautics Science siswa yang mengikuti pembuatan mini wind tunnel.
Pada kurikulum Sekolah Menengah Kejuruan (SMK) Penerbangan, khususnya pada Mata Pelajaran Fisika terdapat dasar ilmu Aeronautika yaitu Dinamika Fluida. Salah satu kendala dalam mempelajari Dinamika Fluida adalah penggambaran yang sulit dan alat peraga yang jarang. Salah satu alat peraga yang sesuai dan digunakan di dunia penerbangan adalah wind tunnel. Kegiatan pengabdian kepada masyarakat berupa demonstrasi dan pendampingan pembuatan mini wind tunnel yang telah dilakukan dapat menjadi solusi permasalahan miskonsepsi materi Dinamika Fluida pada siswa SMK Angkasa 01 Halim Perdanakusuma. Kegiatan dilakukan dengan metode survey mengenai profil miskonsepsi materi Dinamika Fluida, demonstrasi prinsip Bernoulli, dan pendampingan pembuatan mini wind tunnel. Kegiatan diikuti oleh siswa kelas X dan XI yang dilaksanakan tanggal 14 sampai 20 Juni 2022 yang terbagi dalam 2 (dua) sesi yaitu demonstrasi wind tunnel dan pendampingan pembuatan mini wind tunnel. Pengukuran tingkat pemahaman Aeronautics Science dilakukan 3 (tiga) kali yaitu sebelum dan sesudah demonstrasi dan sesudah pendampingan pembuatan mini wind tunnel. Hasil kuesioner pertama yaitu sebagian besar siswa belum mempelajari Dinamika Fluida. Hasil kuesioner kedua cukup signifikan, dimana pengetahuan Aeronautics Science bertambah setelah mengikuti kegiatan PKM. Hasil kuesioner ketiga memperoleh kesimpulan bahwa telah terjadi perubahan tingkat pengetahuan Aeronautics Science siswa yang mengikuti pembuatan mini wind tunnel.
Kata Kunci: Aeronautics science; Dinamika Fluida; mini wind tunnel;
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Berriman, Algernon E. "AERONAUTICS*." Journal of the American Society for Naval Engineers 26, no. 3 (March 18, 2009): 1007–16. http://dx.doi.org/10.1111/j.1559-3584.1914.tb00335.x.
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.
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.
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.
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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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.
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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Hurley, D. G. "Mathematical research at the Aeronautical Research Laboratories 1939–1960." Journal of the Australian Mathematical Society. Series B. Applied Mathematics 30, no. 4 (April 1989): 389–413. http://dx.doi.org/10.1017/s0334270000006342.
AbstractThe Aeronautical Research Laboratories were established in Australia in 1939 as the CSIR Division of Aeronautics. Mathematicians were amongst the first staff employed, and their number reached a peak in the mid 1950s. They were an able group: in their subsequent careers 12 became Professors, 5 obtained higher doctorates, 6 became Fellows of the Australian Academy of Science and 6 Fellows of the Royal Society. They published over 100 papers, and these are discussed here under 11 separate headings.The length of discussion given here to the various areas of research is not uniform. I have emphasised those with which I am familiar and those that interest me personally. Nevertheless, I believe the present paper provides an accurate picture of the mathematical research that was carried out at ARL during the period under review, and makes it clear that mathematicians at ARL made substantial contributions to many areas of theoretical aeronautics.
Bergström, Linda, and Johanna Säreborn. "Value stream mapping at SAAB Aeronautics." Thesis, Linköpings universitet, Kommunikations- och transportsystem, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-139024.
Detta examensarbete handlar om att skapa en flödeskartläggning samt utvärdera materialförsörjningen mellan Saab Aeronautics och deras tredjepartslogistiker Servistik. Servistik försörjer Saabs produktion med material och dylikt med hjälp av det s.k. linjeflödet på vilket transporterna sker. Nu står Saab inför en taktökning, närmare bestämt för flygplanet Gripen E. Målet med detta arbete har varit att ta fram ett underlag för hur denna taktökning kan påverka materialförsörjningen, samt ge förslag på lösningar kring hur linjeflödet ska kunna hantera detta. Redan idag finns det tillfällen då allt material riskerar att inte får plats på linjeflödets fordon, och det är tydligt att linjeflödet måste ses över och modifieras vid en framtida taktökning. Genom observationer och intervjuer har en flödeskartläggning gjorts för att tydliggöra hur linjeflödet är uppbyggt samt fungerar i dagsläget. Syftet med flödeskartläggningen var att identifiera vilka flaskhalsar och problem som uppstått alt. kan uppstå på och kring linjeflödet. Utifrån observationer har beräkningar genomförts för att erhålla ett genomsnittligt medelvärde för de pallar och lådor som är vanligast förekommande som emballage på linjeflödet. Dessa värden har använts för att beräkna procentuella ökningar i materialmängd. Därefter har ett antal lösningsförslag tagits fram för hur olika flaskhalsar och scenarier kan hanteras. De två främsta förslagen som presenteras i detta examensarbete är att dels införa s.k. slot-tider för externa transportörer i godsmottagningen på området, samt att dela upp linjeflödets nuvarande rutt i två mindre rutter. Detta för att både kunna eliminera flaskhalsen som uppstår i godsmottagningen som innebär förseningar i linjeflödets transporter, men även för att senare kunna hantera den ökade mängd material som ska transporteras till respektive hus för produktion.
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Mezannar, Nay <1984>. "Innovative Man Machine Interfaces In Aeronautics." Doctoral thesis, Alma Mater Studiorum - Università di Bologna, 2015. http://amsdottorato.unibo.it/6901/1/Mezannar_Nay_tesi.pdf.
The research activity focused on the study, design and evaluation of innovative human-machine interfaces based on virtual three-dimensional environments.
It is based on the brain electrical activities recorded in real time through the electrical impulses emitted by the brain waves of the user. The achieved target is to identify and sort in real time the different brain states and adapt the interface and/or stimuli to the corresponding emotional state of the user.
The setup of an experimental facility based on an innovative experimental methodology for “man in the loop" simulation was established. It allowed involving during pilot training in virtually simulated flights, both pilot and flight examiner, in order to compare the subjective evaluations of this latter to the objective measurements of the brain activity of the pilot. This was done recording all the relevant information versus a time-line.
Different combinations of emotional intensities obtained, led to an evaluation of the current situational awareness of the user. These results have a great implication in the current training methodology of the pilots, and its use could be extended as a tool that can improve the evaluation of a pilot/crew performance in interacting with the aircraft when performing tasks and procedures, especially in critical situations.
This research also resulted in the design of an interface that adapts the control of the machine to the situation awareness of the user. The new concept worked on, aimed at improving the efficiency between a user and the interface, and gaining capacity by reducing the user’s workload and hence improving the system overall safety.
This innovative research combining emotions measured through electroencephalography resulted in a human-machine interface that would have three aeronautical related applications:
• An evaluation tool during the pilot training;
• An input for cockpit environment;
• An adaptation tool of the cockpit automation.
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Mezannar, Nay <1984>. "Innovative Man Machine Interfaces In Aeronautics." Doctoral thesis, Alma Mater Studiorum - Università di Bologna, 2015. http://amsdottorato.unibo.it/6901/.
The research activity focused on the study, design and evaluation of innovative human-machine interfaces based on virtual three-dimensional environments.
It is based on the brain electrical activities recorded in real time through the electrical impulses emitted by the brain waves of the user. The achieved target is to identify and sort in real time the different brain states and adapt the interface and/or stimuli to the corresponding emotional state of the user.
The setup of an experimental facility based on an innovative experimental methodology for “man in the loop" simulation was established. It allowed involving during pilot training in virtually simulated flights, both pilot and flight examiner, in order to compare the subjective evaluations of this latter to the objective measurements of the brain activity of the pilot. This was done recording all the relevant information versus a time-line.
Different combinations of emotional intensities obtained, led to an evaluation of the current situational awareness of the user. These results have a great implication in the current training methodology of the pilots, and its use could be extended as a tool that can improve the evaluation of a pilot/crew performance in interacting with the aircraft when performing tasks and procedures, especially in critical situations.
This research also resulted in the design of an interface that adapts the control of the machine to the situation awareness of the user. The new concept worked on, aimed at improving the efficiency between a user and the interface, and gaining capacity by reducing the user’s workload and hence improving the system overall safety.
This innovative research combining emotions measured through electroencephalography resulted in a human-machine interface that would have three aeronautical related applications:
• An evaluation tool during the pilot training;
• An input for cockpit environment;
• An adaptation tool of the cockpit automation.
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pozzobon, oscar. "Satellite Navigation Authentication and applications in Aeronautics." Doctoral thesis, Università degli studi di Padova, 2017. http://hdl.handle.net/11577/3426197.
GNSS is becoming a fundamental mean of navigation for aviation, unmanned aircraft including drones and rockets. Although integrity of the system has been planned and designed since the 70s, little few work have been performed in the domain of security related to satellite navigation systems and aviation. The emerging threats refers to mainly intentional interferences such as jamming and spoofing.
Today in an aircraft cockpit there is a number of technologies that rely on Global Satellite Navigation Systems (GNSS), from flight management to Timing, Navigation and anti-collision to Auto pilot functions. The increasing use of GNSS in the flight management and auto pilot systems and its benefits both for navigation and surveillances are the baseline to design protection and alerting systems for GNSS. This thesis begins with an introduction and review of use of GNSS in aeronautics with a particular focus in aviation. A number of critical avionics components are identified and potential risk and security issues are identified and discussed. A generalized theoretical threat model is defined which can be used as a starting point for risk assessment and analysis of vulnerabilities of GNSS. Attacks are categorized in different sophistication that can be used by risk planners to model the security requirements and probability of risk. The work continues with a theoretical background of GNSS authentication, to introduce the philosophical aspects of GNSS authentication design. Three postulates are announced and explained, which have the objectives to provide an instrument for verification of correct authentication protocol design and verification. The work analyzes two main possibilities for protecting the radio navigation in aeronautics: Aircraft protections, which include protections in the GNSS receiver or integration with other equipment in order to verify and mitigate any attacks, and GNSS System protections, which discusses authentication services that can be implemented in the ground or space component of GNSS. Details and results of all different techniques are presented and discussed for every group of technique presented. A final concluding chapter analyzes the pros and cons of the different techniques and attempts to perform an example of how risk assessment can be performed by government or service providers using as input the safety requirements and comparing them with the different attacks and protection techniques. The work concludes with directions and guidelines for future work. I sistemi di navigazione satellitare stanno diventando un mezzo fondamentale di navigazione per l’aviazione ed aeronautica e la navigazione senza pilota, incluso droni e razzi. Sebbene l’integrità sia stata studiata ed implementata dagli anni 70, poco è stato fatto per discutere la sicurezza degli stessi nel settore dell’aviazione. I pericoli ed attachi che stanno emergendo sono in particolare interferenze di jamming e spoofing.
Ad oggi nelle cabine pilota dei moderni aerei vi sono installate un gran numero di tecnologie che si basano sui sistemi di navigazione satellitare (GNSS), dalla gestione del volo al tempo, alla navigazione ed anti-collisione, alle funzioni di auto pilota.
L’uso sempre più commune del GNSS nei sistemi di gestione del volo e gli autopilota ed I benefici per sia la navigazione che la sorveglianza sono le basi per il design dei sistemi di protezione ed alert del GNSS.
La tesi inizia con una review ed introudzione al GNSS ed aeronautica con particolare focus all’aviazione civile. Gli elementi critici dell’avionica ed i potenziali rischi e limiti di sicurezza sono identificati e discussi. Un modello teorico generale è presentato e discusso ed usato come base per le discussioni sulla valutazione del rischio e dell’analisi vulnerabilità del GNSS.
Gli attacchi sono categorizzati con diversi livelli di sofisticazione e possono essere usati per pianificare e modellare il rischio
Il lavoro continua con introduzione al background della autenticazione GNSS ed introduce aspetti teorici dell’autenticazione. Tre postulati sono enunciati e spiegati, con l’obiettivo di dare uno strumento per la corretta definizione e progettazione degli schemi di autenticazione.
Il lavoro analizza due maggiori possibilità per introdurre sicurezza nel settore dell’aviazione: protezione a livello dell’aereo e quindi dei sistemi avionici e protezione a livello sistema GNSS.
Un numero di tecniche per la protezione a livello aereo e a livello GNSS sono presentate e per le quali sono state effettuate diverse sperimentaizoni e simulazioni. I risultati vengono presentati e discussi nelle varie sottosezioni e per ogni gruppo di tecniche presentate.
Un capitolo in conclusione confronta le varie tecniche e cerca di fornire uno strumento su cui fare del risk assessment e come baseline per la definizione dei requisiti. Il lavoro conclude con conclusioni generali e proposte per lavoro futuro.
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Mellqvist, Hanna, and Elise Lord. "Optimeringsverktyg för att effektivisera huvudprogrammet på Saab Aeronautics." Thesis, Linköpings universitet, Institutionen för teknik och naturvetenskap, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-170827.
Saab är ett ledande företag på marknaden inom försvar- och säkerhetslösningar. De levererar produkter, tjänster och lösningar inom både militärt försvar och civil säkerhet. Saab Aeronautics tillverkar och utvecklar stridsflygplanet JAS 39 Gripen. Saab har en pågående affär med det brasilianska flygvapnet som inkluderar produktion och utveckling av totalt 36 stycken stridsflygplan av modellerna Gripen E och Gripen F. Planering kan ske på strategisk, taktisk eller operativ nivå. Om leveranstiden till kunden är lång är det vanligt att den strategiska och taktiska nivån slås samman, vilket också är fallet på Saab där nivåerna slagits samman och benämns som huvudplanering. Huvudplaneringen har som uppgift att ta fram ett huvudprogram för produktion av Gripen med en planeringshorisont på tio år. För att produktionen ska vara effektiv är det viktigt att huvudprogrammet är så bra utformat som möjligt, samt att det inkluderar alla avtalade teknikutbyten. I dagsläget har huvudplaneringen inget optimeringsverktyg som på ett systematiskt vis inkluderar de faktorer som bör tas hänsyn till vid framtagandet av ett huvudprogram. Syftet med examensarbetet är att utreda vad som krävs för att huvudplaneringen ska kunna ta hänsyn till fler faktorer vid framtagande av huvudprogram. En matematisk modell för Saab togs fram och därefter var planen att implementera den i Excel, eftersom huvudplaneringen använder denna programvara i dagsläget. Under arbetets gång upptäcktes det att Excel har begränsningar som gjorde att det inte var möjligt att implementera den matematiska modellen enligt den matematiska notationen. En avvägning om att endera fokusera på implementerbarhet eller teknisk noggrannhet gjordes och implementerbarhet valdes. Ett verktyg som inkluderar de krav som anges i den matematiska modellen skapades i Excel. För att verifiera den matematiska modellen implementerades den i optimeringsverktyget AMPL. Därefter gjordes en jämförelse mellan de olika verktygen för att visa på eventuella skillnader i resultatet som de genererade. Arbetet resulterade i en matematisk modell för Saab och ett verktyg i Excel. Modellen tar hänsyn till olika typer av teknikutbyte, att ledtiden är inom tillåtet tidsspann för varje aktivitet och att glapptider minimeras. Verktyg i Excel tar hänsyn till faktorerna som inkluderades i den matematiska modellen. För att målet ska uppnås krävs djupare utredning kring befintliga programvaror eller att investera i en ny programvara. Saab is a global company within defense and security, and they deliver products, services and solutions within military defense and civil security. The business area Aeronautics develop and produce the aircraft system JAS 39 Gripen. Saab has a contract with the Brazilian air force which includes development and production of 36 aircraft systems. There are three different levels of planning, strategical, tactical and operational. It is common to merge the strategical and tactical level if the delivery time is long. The strategical and tactical level at Saab is one unit and they are called Master Planning. The main task for Master Planning is to create a master production schedule with a planning horizon of ten years. It is important that the master production schedule includes all technological transfers and that the schedule is as efficient as possible. They do not use any technological tool that systematically includes all factors that needs to be taken into account when creating a schedule. The aim with this master thesis is to investigate how more factors can be integrated when developing the master production schedule. A mathematical model for Saab was created. Then the plan was to implement the mathematical model in Excel, since the Master Planning use this tool currently. During the implementation it was discovered that Excel has limitations that makes it impossible to implement the mathematical model according to the mathematical notation. A tradeoff was made, to either focus on implementability or technological accuracy, and implementability was chosen. Then a tool was created in Excel, which includes the requirements from the mathematical model. To verify the mathematical model, it was implemented in the optimization tool AMPL. Then a comparison between Excel and AMPL was made, to be able to show possible differences. The result of the master thesis is a mathematical model for Saab and a tool in Excel. The mathematical model includes different types of technological transfer, lead time requirements and minimization of gap time. The tool in Excel includes the requirements which is specified in the mathematical model. To be able to achieve the goal, an investigation must be done to find out if Saab can use any existing software at the company or if they need to invest in a new type of software.
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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/.
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/.
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/.
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/.
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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Melin, Tomas. "Multidisciplinary Design in Aeronautics, Enhanced by Simulation-Experiment Synergy." Doctoral thesis, Stockholm : Kungliga Tekniska högskolan, 2006. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3996.
United States. National Aeronautics and Space Administration, ed. Aeronautics. [Washington, D.C.?: National Aeronautics and Space Administration, 1988.
Division, United States National Aeronautics and Space Administration Scientific and Technical Information. NASA thesaurus aeronautics vocabulary. Washington, D.C: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.
Hallion, Richard. NASA's contributions to aeronautics. Edited by United States. National Aeronautics and Space Administration. Washington, DC: National Aeronautics and Space Administration, 2010.
Insaurralde, Carlos C., and Erik Blasch. "Ontologies in Aeronautics." In Advances in Aeronautical Informatics, 67–85. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-75058-3_6.
RASSON, JEAN L. "GEOMAGNETIC MEASUREMENTS FOR AERONAUTICS." In Geomagnetics for Aeronautical Safety, 213–30. Dordrecht: Springer Netherlands, 2006. http://dx.doi.org/10.1007/978-1-4020-5025-1_16.
De Keyser, V., and D. Javaux. "Human Factors in Aeronautics." In Eurographics, 28–45. Vienna: Springer Vienna, 1996. http://dx.doi.org/10.1007/978-3-7091-7491-3_2.
Bloom, Daniel T. "Morrison Aeronautics Brain Trust." In Reality, Perception, and Your Company’s Workplace Culture, 53–58. New York, NY : Routledge, 2019.: Productivity Press, 2019. http://dx.doi.org/10.4324/9780429429118-9.
Gollin, Alfred. "The Advisory Committee for Aeronautics." In The Impact of Air Power on the British People and their Government, 1909–14, 24–48. London: Palgrave Macmillan UK, 1989. http://dx.doi.org/10.1007/978-1-349-10887-9_2.
Gollin, Alfred. "The Forward March of Aeronautics." In The Impact of Air Power on the British People and their Government, 1909–14, 89–108. London: Palgrave Macmillan UK, 1989. http://dx.doi.org/10.1007/978-1-349-10887-9_5.
Latham, David W. "National Aeronautics and Space Administration." In Encyclopedia of Astrobiology, 1107. Berlin, Heidelberg: Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-11274-4_1788.
Cugini, Umberto. "Feature-Based Assembly for Aeronautics." In CAD Tools and Algorithms for Product Design, 31–46. Berlin, Heidelberg: Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-04123-9_3.
Malaval, Philippe, Christophe Bénaroya, and Jonathan Aflalo. "Marketing in the Aeronautics Industry." In Management for Professionals, 1–27. Cham: Springer International Publishing, 2013. http://dx.doi.org/10.1007/978-3-319-01354-1_1.
Bloom, Daniel T. "The Visit to Morrison Aeronautics." In Reality, Perception, and Your Company’s Workplace Culture, 41–52. New York, NY : Routledge, 2019.: Productivity Press, 2019. http://dx.doi.org/10.4324/9780429429118-8.
Bisagni, C. "Can we use buckling to design adaptive composite wings?" In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-77.
Abstract. In aeronautics, buckling has long been considered as a structural phenomenon to be avoided, because characterized by large out-of-plane displacements and therefore by losing the ability to sustain the designed loads. Several recent studies show the possibility to allow composite stiffened panels of primary aeronautical components to work in the post-buckling field so to potentially reduce the structural weight. The present study aims to control buckling behavior of composite structural components for future adaptive wings using novel tailorable and effective mechanisms. Instead of the traditional design against buckling, the idea is to use the nonlinear post-buckling response to control stiffness changes which redistribute the load in the wing structure. Numerical studies are at first conducted on a composite plate and then implemented in a simplified thin-walled composite wing box, where stiffness changes is controlled using buckling.
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Kroo, Ilan. "Innovations in Aeronautics." In 42nd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-1.
Anese, G. "Electro-thermal dynamic simulations and results of a deorbiting tethered system." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-117.
Abstract. Deorbiting techniques with small or better no propellant consumption are an important and critical field of space studies for the mitigation of orbital debris. Electrodynamic tethers (EDTs) are of particular interest because they make possible to deorbit space debris by exploiting the Lorentz force that is provided by the current flowing in the tether thanks to the interaction of the system with the Earth’s magnetosphere and the ionosphere. This paper focuses on the differences between two software packages built at the University of Padova (FLEX and FLEXSIM) and their results in simulating various deorbiting scenarios. Both FLEXSIM and FLEX simulate the electro-thermal behaviour and the dynamics of an EDT. However, while the first one has the simplifying assumption that the tether is always aligned with the local vertical, the second one considers also the overall system attitude with respect to the radial direction and the tether flexibility. The computational times of these S/W are very different and it is important to understand the scenarios that are more appropriate for their use. Results aim to show the impact of different solar activity (simulations are done at different epochs) and lengths of conductive and non conductive segments of tether, in the range of a few hundreds of meters, on the total re-entry time. As expected, deorbiting is faster for high solar activity and conductive tether length but the performance must be balanced against the dynamics stability. The issue of stability over the deorbiting time is evaluated numerically for specific cases by using FLEX.
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Trevisi, F. "Multidisciplinary design, analysis and optimization of fixed-wing airborne wind energy systems." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-30.
Abstract. Airborne wind energy (AWE) is the second generation of wind energy systems, an innovative technology which accesses the large untapped wind resource potential at high altitudes. It enables to harvest wind power at lower carbon intensity and, eventually, at lower costs compared to conventional wind technologies. The design of such systems is still uncertain and companies and research institutions are focusing on multiple concepts. To explore the design space, a new multidisciplinary design, analysis and optimization framework for fixed-wing airborne wind energy systems (T-GliDe) is being developed. In this work, the framework of T-GliDe and its problem formulation are introduced.
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Catapane, G. "Labyrinth quarter-wavelength tubes array for the reduction of machinery noise." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-158.
Abstract. Anthropogenic noise from navigation is a major contributor to the disturbance of the acoustic soundscape in underwater environments. The noise generated by ship’s machinery exhibits energetic tonal harmonic peaks at multiples of the rotating and firing frequency, that occur in the 20-200 Hz frequency range and difficult to control with classical soundproofing materials. Quarter wavelength tubes (QWT) can be a concrete solution since their absorption peaks are harmonic odd integers of the first resonance frequency. The main issue of QWT is their tuning length, which equals 1.43 m for a 60 Hz resonator. The problem is solved by coiling the tube into a labyrinth. Three labyrinth quarter wavelength tubes are tuned respectively at 60, 90 and 120 Hz. Samples are printed with filament 3D additive manufacturing techniques using PLA and tested with a square impedance tube designed for low-frequency measurements. Measurement results are in good agreement with analytical and numerical predictions. An array including four 60 Hz, four 90 Hz and four 120 Hz labyrinths QWTs is finally tested.
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Lopresti, S. "Overview of spacecraft fragmentation testing." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-112.
Abstract. Spacecraft fragmentation due to collisions with space debris is a major concern for space agencies and commercial entities, since the production of collisional fragments is one of the major sources of space debris. It is in fact believed that, in certain circumstances, the increase of fragmentation events could trigger collisional cascade that makes the future debris environmental not sustainable. Experimental studies have shown that the fragmentation process is highly complex and influenced by various factors, such as the material properties, the velocity and angle of the debris impact and the point of collision (e.g. central, glancing, on spacecraft appendages). In recent years, numerous impact tests have been performed, varying one or more of these parameters to better understand the physics behind these phenomena. In this context some tests have been also performed at the hypervelocity impact facility of the university of Padova. This paper provides an overview of the main experiments performed, the most critical issues observed and proposes some future directions for further research. Moreover, it summarizes the current state of research in spacecraft fragmentation, including the methods and techniques used to simulate debris impacts, the characterization of fragment properties and the analysis of the resulting debris cloud.
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Filippi, M. "Refined structural theories for dynamic and fatigue analyses of structure subjected to random excitations." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-100.
Abstract. This paper presents the application of low- and high-fidelity finite beam elements to analyze the dynamic response of aerospace structures subjected to random excitations. The refined structural models are developed with the Carrera Unified Formulation (CUF), enabling arbitrary finite element solutions to be easily generated. The solution scheme uses power spectral densities and the modal reduction strategy to reduce the computational burden. The response of an aluminum box beam is studied and compared with a solution obtained by a commercial code. Considering the root-mean-square value of the axial stress, an estimation of the fatigue life of the structure is obtained.
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Adamo, F. P. "Aeroacoustic assessment of blended wing body configuration with low noise technologies." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-1.
Abstract. An aeroacoustic assessment of promising novel aircraft concepts (BOLT and REBEL, two Blended wing bodies respectively with conventional and hybrid engines) devoted to fly in 2035-2050 scenario coupled with Low Noise Technologies (LNT) developed inside the framework of ARTEM project (H2020)[1] has shown. The noise assessment of each noise source of the AAC (Advanced Air Concepts) has been provided including the attenuation due to the masking effects due to the fuselage. The results are then used for the noise impact on the ground, through a ray-tracing method and taking into account the installative effects, with a comparison with standard/similar aircraft. Finally, the noise assessment of a AAC&Standard fleet on a reference airport has been provided.
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Conte, C. "Improvements in on-board systems design for advanced sustainable air mobility." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-98.
Abstract. This paper describes the activity proposed in the context of National Center for Sustainable Mobility (CN MOST) for designing an advanced core Guidance, Navigation, and Control system together with an effective on-board systems configuration for sustainable air mobility. A Model Based Systems Engineering strategy is adopted to support the design and development phases. The introduction of new sustainability objectives and the U-Space services to support the integration of unmanned air vehicles in the traditional Air Traffic Management drives the need of a full redesign of on-board systems that must be interfaced with different air platform categories. High performance processing units are considered for embedded systems, including but not limited to machine learning based, image processing and data fusion algorithms for advanced navigation. Three use-cases are presented as reference platform and mission types for validating the proposed systems configuration, specifically unmanned electric Vertical Take Off and Landing aircraft, fully electric general aviation aircraft, and hybrid-electric regional aircraft.
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Fiorio, M. "Hardware-in-the-loop validation of a sense and avoid system leveraging data fusion between radar and optical sensors for a mini UAV." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-16.
Abstract. The present work illustrates the results obtained at the conclusion of the three-year project TERSA (Tecnologie Elettriche e Radar per Sapr Autonomi), involving the aerospace section of the Dept. of Civil and Industrial Engineering (DICI) of the University of Pisa and its industrial partners. The project aimed at the design and development of a fully autonomous Sense and Avoid (SAA) prototype system, based on data fusion between optical and radar sensors data, for a tactical lightweight surveillance UAV (MTOW<25Kg). The problem of non-cooperative collision avoidance is well known in literature and is currently a central theme of investigation within the aeronautical industry, considering the growing UAV traffic and the consequent need to employ autonomous self-separation technologies in the market. Several past works have investigated the most varied solutions for the Sense problem utilizing optical, acoustic, electro-magnetic signals or a combination of the previous. Likewise, the Avoidance problem has been successfully tackled in literature by means of a wide variety of different approaches ranging from rule-based methods, strategies based on game theory, force field methods, optimization frameworks leveraging genetic algorithms and nonlinear programming techniques and geometric methods. Yet, to the knowledge of the authors, no previous work found in literature has successfully demonstrated and validated the real-time simultaneous interaction of both sense and avoid functionalities within a highly integrated simulation environment. The present work describes the implementation of a complex, nonlinear, simulation environment conceived in order to perform real-time, Hardware-in-the-Loop (HIL), testing of the effective cooperation between sense and the avoid algorithms constituting the core of the SAA system developed within the context of the project. The system effectiveness has been validated by means of complex dynamic simulations, comprising an accurate, fully nonlinear, flight mechanic model of the aircraft, a graphic rendering engine of the scene, proper video capture and transmission pipelines, computer vision algorithms and collision avoidance logics running on the target hardware (Nvidia Jetson Nano) and tailored noise resilient data fusion algorithms. Results show the effectiveness of the system in detecting impending collisions and performing last-resort resolution manoeuvres with high computational efficiency and update frequencies compatible with real world applications in Unmanned Aircraft Systems (UAS).
Звіти організацій з теми "Aeronautics":
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Burge, Legand L. Dr. Alexander H. Flax: Technologist of Aeronautics. Fort Belvoir, VA: Defense Technical Information Center, March 1992. http://dx.doi.org/10.21236/ada258441.
Platzer, Max F., and Raymond P. Shreeve. Summary of Research 2000, Department of Aeronautics and Astronautics. Fort Belvoir, VA: Defense Technical Information Center, December 2001. http://dx.doi.org/10.21236/ada408912.
Lindsey, Gerald H., and Oscar Biblarz. Summary of Research 1997, Department of Aeronautics and Astronautics. Fort Belvoir, VA: Defense Technical Information Center, January 1999. http://dx.doi.org/10.21236/ada360675.
Smith, Frances M., Oscar Biblarz, and Daniel J. Collins. Summary of Research 1995, Department of Aeronautics and Astronautics. Fort Belvoir, VA: Defense Technical Information Center, August 1996. http://dx.doi.org/10.21236/ada316201.
Roback, Edward. National Aeronautics and Space Administration's (NASA) automated information security handbook. Gaithersburg, MD: National Institute of Standards and Technology, 1991. http://dx.doi.org/10.6028/nist.ir.4518.
Haas, David J., and Eric J. Silberg. Birth of U.S. Naval Aeronautics and the Navy's Aerodynamics Laboratory. Fort Belvoir, VA: Defense Technical Information Center, December 2011. http://dx.doi.org/10.21236/ada558167.
Beymer, Mark. Self-Concept Competency of National Aeronautics and Space Administration Research and Development Managers. Portland State University Library, January 2000. http://dx.doi.org/10.15760/etd.1379.
Macedo Junior, Ronaldo Porto, Clarissa Piterman Gross, Fabrizio Cafaggi, Tiago Andreotti e. Silva, Luana F. Joppert Swensson, Thiago Alves Ribeiro, and Lucila Gabriel de Almeida. Accessing the Global Value Chain in a Changing Institutional Environment: Comparing Aeronautics and Coffee. Inter-American Development Bank, November 2012. http://dx.doi.org/10.18235/0011454.
The aim of the paper, based on empirical research in Brazil, is to investigate how supply chains have evolved over time, what factors have driven this evolution and also how a specific set of contractual practices along these chains is linked to access to international markets. The two selected case studies in the field of agriculture and aeronautics permit comparison between different modes of accessing international markets and GVCs; they illustrate the roles of transnational corporations and those of public institutions both at domestic and international levels in promoting access and determining its modes and potential spillover effects onto local production systems. More specifically, the research identifies the alternative channels of access to GVCs and international markets, and the institutional, legal and economic obstacles which prevent access or make it very costly. It looks at the role of intermediaries who control access to international markets, examining when they operate as gateways and when as bottlenecks. It examines both private and public actors, trying to disentangle when they facilitate and when they hinder access. It focuses on the most relevant factors that may attract foreign direct investments in human and physical capital to Brazil.
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Eddy, W., W. Ivancic, and T. Davis. Network Mobility Route Optimization Requirements for Operational Use in Aeronautics and Space Exploration Mobile Networks. RFC Editor, October 2009. http://dx.doi.org/10.17487/rfc5522.
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.
