Thematische Bibliographien / Aircraf

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Auswahl der wissenschaftlichen Literatur zum Thema „Aircraf“

Autor: Grafiati

Veröffentlicht am 28. Juni 2021

Zuletzt aktualisiert am 1. Februar 2022

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Zeitschriftenartikel zum Thema "Aircraf"

Suharyadi, Suharyadi, und Yudhistira Tri Nurteisa. „Teknologi Pesawat Tanpa Awak untuk Pemetaan Skala Detail Rencana Jaringan Pipa Sanitasi Komunal bagi Masyarakat Dusun Kepek 1, Kepek, Wonosari, Gunungkidul“. Jurnal Pengabdian kepada Masyarakat (Indonesian Journal of Community Engagement) 2, Nr. 1 (16.02.2017): 1–13. http://dx.doi.org/10.22146/jpkm.22081.

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Human settlements can not be separated from the emergence of waste generated by human activity. Waste will give a negative efect on health and the environment if not handled and managed properly. Hamlet Kepek 1, Kepek, Wonosari have realized the impact that arises when household waste is not managed properly. For that, some residents have initiated a communal waste management and manufacture of communal sanitation pipelines. Conventionally, communal sanitary pipe network planning and data requires a huge cost, for it takes breakthrough of utilization of appropriate technology to facilitate the planning process and reduce the cost incurred.Utilization of small format aerial photographs resulting from the unmanned aircraf vehicle (UAV) used as an alternative technology in the planning communal sanitation pipelines. Analytical methods to create a map of the communal sanitation pipelines through least cost path analysis. Utilization of UAV technology is expected to make the planning of communal sanitary pipelines with good results and at afordable costs. Te result of small format aerial photography from unmanned aircraf vehicle (UAV) can be used to produce the spatial data with high resolution. Small format aerial photographs produced is then processed to obtain the orthophoto image and the image of Digital Surface Model (DSM). Both kinds of remote sensing image are then used as the main data to create maps of the communal sanitation pipelines. Te result of processing in the form of a map of communal sanitation pipelines in t Kepek 1 at low cost and appropriate technology.

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Al Wardi, Yousuf, Sasirajan Jeevarathinam und Saleh Al Sabei. „A Cross-Cultural Anthropometric Analysis in Military Aviation“. Aerospace Medicine and Human Performance 91, Nr. 4 (01.04.2020): 358–62. http://dx.doi.org/10.3357/amhp.5530.2020.

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BACKGROUND: Aircrew-aircraft compatibility is important in military aviation for flight safety. Anthropometric aircrew selection standards in RAFO were embedded from the selection standards of western defense forces as the aircrafts were imported from there. Henceforth efforts were made to fit local native aviators into aircrafts not initially designed for them. In view of this, this study was carried out to obtain the anthropometric data of Oman aircrew recruits and compare these with published western and eastern data with a hope to understand and highlight the aircrew-aircraft mismatch issues, if any.METHODS: The anthropometric data of 2296 Omani recruits from 2003 to 2012 were collected and their statistical distribution of data was collated. Published data from the UK and Singapore were used to carry out the comparative distribution of five anthropometric dimensions.RESULTS: Minimal differences were noted between Oman and Singaporean recruits whereas differences were most pronounced between Oman and Western populations (UK). Aircrew cadets from Oman, Singapore, and UK differed significantly in standing height. The UK cadets (M = 177.4 cm) showed the highest standing height followed by Oman cadets (M = 171.9cm), and then Singapore cadets (M = 168.5 cm).DISCUSSION: This study has provided opportunities to recognize the discrepancies involved in selection of Middle Eastern aircrew for western cockpits. This adds impetus to the scope for application of military recruitment standards suitable to the native population in aiding the ideal man-machine interface. This approach shall consider national policy, the significant anthropometric trends of the general population, and the procured aircraft profile of the country.Al Wardi Y, Jeevarathinam S, Al Sabei S. A cross-cultural anthropometric analysis in military aviation. Aerosp Med Hum Perform. 2020; 91(4):358–362.

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Biswal, P., und YS Dahiya. „Principal component analysis: The path ahead for aircrew-aircraft compatibility at the Institute of Aerospace Medicine“. Indian Journal of Aerospace Medicine 63 (07.11.2019): 8–15. http://dx.doi.org/10.25259/ijasm_2019_3.

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Introduction: The Institute of Aerospace Medicine provides design consultancy on aircraft-aircrew compatibility on a number of fixed-wing as well as rotary-wing aircrafts during various stages of development. Till date, the cockpit compatibility of aircrew has been determined based on the percentile concept. Percentiles, though useful when dealing with a single parameter, pose major design and fitment problems when considering multiple parameters simultaneously as in aircraft cockpit design. The concept of multivariate analysis has been the solution which the aviation industry the world over has accepted in overcoming this problem. This paper presents the Institute of Aerospace Medicine initial foray into the field of multivariate analysis, specifically principal component analysis (PCA) to achieve desired aircrew fitment in the aircraft cockpit right from the design stage. Materials and Methods: The fighter aircraft of the near future is being designed using the anthropometric parameters available in the IAF aircrew anthropometry survey 2013. Of the 57 parameters available, six parameters critical to the design of the cockpit were subject to PCA to derive three principal components. About 96% confidence ellipse was drawn on the plot of the principal components. From this, along the different axes, 21 boundary individuals were identified defining the extreme individuals in various combinations of the six parameters. Discussion: The use of more than 2 parameters is not amenable to sequential use of percentiles. As the number of parameters considered increases, it leads to reduced fitment percentage. The use of PCA allows consideration of critical parameters together at one go. The design aim is changed from the 3rd to 97th percentile to an overall aim of fitting 96% of the target population in the cockpit. The boundary individual’s entire anthropometry data are used to create boundary manikins for use in computer-aided design models. The fitment of these boundary individuals ensures that if these individuals fit, all others would fit in the cockpit. This concept brings about a paradigm shift in the aircrew-aircraft compatibility in the aviation industry in India.

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Lewitowicz, Jerzy, und Stefan Rutkowski. „Research of the Reliability of an Air Combat Manoeuvere – Nosedive of a Jet Powered Aircraft / Badanie Niezawodności Lotniczego Manewru Bojowego – Lotu Nurkowego Samolotu Odrzutowego“. Journal of KONBiN 31, Nr. 1 (01.12.2014): 13–22. http://dx.doi.org/10.2478/jok-2014-0019.

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Abstract This paper considered a problem of: the reliability of performance of a nosedive of a jet powered aircraft in the context of the ability of pilots trained on a simulator to reliably accomplish a combat mission. For research purposes, the manoeuvre of attack of a target with the nosedive, which is most commonly used by the pilots performing flights on different types of modern aircrafts, and the basic manoeuvre during aircrew training, both basic and advanced were assumed. The research was conducted on a flight simulator.

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Fujita, Etsushi, Taichi Higashioka, Manabu Sugiura und Osamu Kohashi. „Evaluation method of military aircraft noise using AI analysis of aircraft images“. INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, Nr. 6 (01.08.2021): 854–62. http://dx.doi.org/10.3397/in-2021-1668.

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In recent aircraft noise survey in Japan, noise data is associated with each aircraft by flight log or by radio information including transponder signals. Especially, above Tokyo metropolitan area, flight tracks are tangled extremely each other, therefore assessments from various perspectives such as departure / arrival airport, used runway, aircraft model, and operator have been demanded for determining noise policies. However, for military aircrafts, it is not easy to identify their information with the same way as commercial aircrafts, because their flight logs are not disclosed and many of them do not emit transponder signals like commercial aircrafts. Therefore, manned 24 hours survey around air bases have been necessary to obtain flight information of military aircrafts. In this paper, we propose an AI-based analysis using captured aircraft images for obtaining actual flight data of military aircrafts. In the past trials, we could determine the takeoff/landing time and the aircraft model by the above method. Associating these information and noise data measured at monitoring stations, details of noise characteristics around the air base can be clearly grasped. Advanced analysis of the causes of noise impact will lead effective and concrete countermeasures.

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Zhang, Yuhang, Hao Sun, Jiawei Zuo, Hongqi Wang, Guangluan Xu und Xian Sun. „Aircraft Type Recognition in Remote Sensing Images Based on Feature Learning with Conditional Generative Adversarial Networks“. Remote Sensing 10, Nr. 7 (16.07.2018): 1123. http://dx.doi.org/10.3390/rs10071123.

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Aircraft type recognition plays an important role in remote sensing image interpretation. Traditional methods suffer from bad generalization performance, while deep learning methods require large amounts of data with type labels, which are quite expensive and time-consuming to obtain. To overcome the aforementioned problems, in this paper, we propose an aircraft type recognition framework based on conditional generative adversarial networks (GANs). First, we design a new method to precisely detect aircrafts’ keypoints, which are used to generate aircraft masks and locate the positions of the aircrafts. Second, a conditional GAN with a region of interest (ROI)-weighted loss function is trained on unlabeled aircraft images and their corresponding masks. Third, an ROI feature extraction method is carefully designed to extract multi-scale features from the GAN in the regions of aircrafts. After that, a linear support vector machine (SVM) classifier is adopted to classify each sample using their features. Benefiting from the GAN, we can learn features which are strong enough to represent aircrafts based on a large unlabeled dataset. Additionally, the ROI-weighted loss function and the ROI feature extraction method make the features more related to the aircrafts rather than the background, which improves the quality of features and increases the recognition accuracy significantly. Thorough experiments were conducted on a challenging dataset, and the results prove the effectiveness of the proposed aircraft type recognition framework.

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Zuo, Yu Yu. „Analysis of Gas Turbine Engines Auxiliary Power Units“. Applied Mechanics and Materials 533 (Februar 2014): 13–16. http://dx.doi.org/10.4028/www.scientific.net/amm.533.13.

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As aircraft became more complex a need was created for a power source to operate the aircraft systems on the ground without the necessity for operating the aircrafts main engines. This became the task of the Auxiliary Power Unit (APU). The use of an APU on an aircraft also meant that the aircraft was not dependant on ground support equipment at an airfield. It can provide the necessary power for operation of the aircrafts Electrical, Hydraulic and Pneumatic systems. It should come as no surprise that the power unit selected to do this task is a Gas Turbine Engine.

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Wang, Hong Yong, Rui Ying Wen und Yi Fei Zhao. „Empirical Research on Topological Characteristics of Air Traffic Situation Network“. Applied Mechanics and Materials 744-746 (März 2015): 1975–79. http://dx.doi.org/10.4028/www.scientific.net/amm.744-746.1975.

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A method for description of structural characteristics of air traffic situation based on the theory of complex network was proposed. This method characterizes the air traffic situation from three dimensions, including single aircraft, local sector, and overall sector. We selected the routinely-recorded flight data in an air traffic control sector within China's airspace in 2013. With the aircrafts in the sector regarded as nodes, and with the between-aircraft proximity relations as edges, we constructed an undirected and unweighted aircraft network. The results show that network node degree can distinguish the key aircraft in the sector; the network connection rate reflects the proximity of aircrafts; the clustering coefficient identifies the presence of high-density aircraft group.

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Yao, Man. „Water Impact Analysis for Aircraft over Sea“. Applied Mechanics and Materials 341-342 (Juli 2013): 563–66. http://dx.doi.org/10.4028/www.scientific.net/amm.341-342.563.

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The modern aircrafts flying height is strictly limited by the conditions on the sea. Terrible conditions may lead overturning or dropping into the water to the aircraft. Whats more, the structure of the aircraft may be broken by water-impact force. The affection of the water impact must be considered to promise the safety of the aircraft. This paper focuses on the water impact to a typical symmetrical aircraft flying above sea. The water impact force related to the trajectory angle and equivalent pitch angle is researched based on the water impact force model of a two-dimensional wedge. In addition, concerning with the limitation of the aircrafts overload, the water-contact condition is proposed to avert attitude overturning and structure broken of the aircraft.

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Zhao, Chang Jun, Yue Bai, Xun Gong, Dong Fu Xu und Zhi Jun Xu. „Control System Design of a Hex-Rotor Aircraft Based on the Neural Network Sliding Mode Method“. Advanced Materials Research 971-973 (Juni 2014): 418–21. http://dx.doi.org/10.4028/www.scientific.net/amr.971-973.418.

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For the existing Multi-rotor aircrafts, the under-actuation and strong coupling characteristics have a remarkable influence on their flight performance. In order to overcome this effect, a novel Hex-Rotor aircraft is proposed in this paper. Based on the unique configuration of its six driving rotors, the Hex-Rotor aircraft has the ability to achieve the real independent control on the space 6-DOF channels. An autonomous flight control system with neural network sliding mode is designed. The simulation proved that the novel Hex-Rotor aircraft has desired maneuvering capability,and thehe control system is able to guarantee the aircrafts tracking flight of the aircraft.

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Dissertationen zum Thema "Aircraf"

Torres, Calderon Rosa Maria. „Multi-objective environmentally-friendly departure procedures for civil aircraf : modeling, optimization and robustness assessment“. Toulouse 3, 2011. http://www.theses.fr/2011TOU30320.

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Cette thèse présente le concept MCDP (Multi-Criteria Departure Procedure), qui a comme objectif l’optimisation des procédures de départ afin de minimiser l’impact environnemental des avions. Ces impacts portent essentiellement sur les nuisances acoustiques, la qualité de l’air et l’émission des gaz d’effet de serre. Il n’existe pas une seule procédure capable de minimiser les trois critères simultanément. Le concept MCDP est donc modélisé par un problème d’optimisation multi-objectif sous contraintes. La technique de recherche directe MADS est utilisée pour obtenir les trajectoires Pareto optimales associées au problème d’optimisation. Des indicateurs de robustesse sont ensuite construits pour analyser l’impact des incertitudes sur le front de Pareto. L’application des méthodologies développées aux avions Airbus montre le potentiel intérêt d’optimiser la phase de départ en termes environnementaux
This Ph. D. Work introduces the MCDP (Multi-Criteria Departure Procedure) concept, the aim of which is to optimize civil aircraft departure procedures in order to minimize their environmental impact, mainly represented by noise, local air quality and greenhouse gas emissions. It is not possible to determine a single departure procedure minimizing the three objectives simultaneously. Therefore, the concept is modeled as a multi-objective, constrained optimization problem. The MADS direct search optimization technique is used to obtain the Pareto optimal departure procedures associated with this problem. Robustness indicators have then been built to determine the impact of uncertainty on the Pareto front. Application to Airbus aircraft of the methodologies developed shows the potential interest of optimizing the departure phase in terms of environmental benefits

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Urbano, Simone. „Detection and diagnostic of freeplay induced limit cycle oscillation in the flight control system of a civil aircraf“. Thesis, Toulouse, INPT, 2019. http://www.theses.fr/2019INPT0023/document.

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Cette étude est le résultat d’une thèse CIFRE de trois ans entre le bureau d’étude d’Airbus (domaine du contrôle de l’avion) et le laboratoire TéSA à Toulouse. L’objectif principal est de proposer, développer et valider une solution logicielle pour la détection et le diagnostic d’un type spécifique de vibrations des gouvernes de profondeur et direction, appelée oscillation en cycle limite (limit cycle oscillation ou LCO en anglais), basée sur les signaux existants dans les avions civils. LCO est un terme mathématique générique définissant un mode périodique indépendant de conditions initiales et se produisant dans des systèmes non linéaires non conservatifs. Dans cette étude, nous nous intéressons au phénomène de LCO induit par les jeux mécaniques dans les gouvernes d’un avion civil. Les conséquences du LCO sont l’augmentation locale de la charge structurelle, la dégradation des qualités de vol, la réduction de la durée de vie de l’actionneur, la dégradation du confort du poste de pilotage et de la cabine, ainsi que l’augmentation des coûts de maintenance. L’état de l’art en matière de détection et de diagnostic du LCO induit par le jeu mécanique est basé sur la sensibilité du pilote aux vibrations et sur le contrôle périodique du jeu sur les gouvernes. Cette étude propose une solution basée sur les données (issues de la boucle d’asservissement des actionneurs qui agissent sur les gouvernes) pour aider au diagnostic du LCO et à l’isolement du jeu mécanique. L’objectif est d’améliorer encore plus la disponibilité des avions et de réduire les coûts de maintenance en fournissant aux compagnies aériennes un signal de contrôle pour le LCO et les jeux mécaniques. Pour cette raison, deux solutions algorithmiques pour le diagnostic des vibrations et des jeux ont été proposées. Un détecteur en temps réel pour la détection du LCO est tout d’abord proposé basé sur la théorie du rapport de vraisemblance généralisé (generalized likelihood ratio test ou GLRT en anglais). Certaines variantes et simplifications sont également proposées pour satisfaire les contraintes industrielles. Un détecteur de jeu mécanique est introduit basé sur l’identification d’un modèle de Wiener. Des approches paramétrique (estimateur de maximum de vraisemblance) et non paramétrique (régression par noyau) sont explorées, ainsi que certaines variantes des méthodes non paramétriques. En particulier, le problème de l’estimation d’un cycle d’hystérésis (choisi comme la non-linéarité de sortie d’un modèle de Wiener) est abordé. Ainsi, les problèmes avec et sans contraintes sont étudiés. Une analyse théorique, numérique (sur simulateur) et expérimentale (données de vol et laboratoire) est réalisée pour étudier les performances des détecteurs proposés et pour identifier les limitations et la faisabilité industrielle. Les résultats numériques et expérimentaux obtenus confirment que le GLRT proposé (et ses variantes / simplifications) est une méthode très efficace pour le diagnostic du LCO en termes de performance, robustesse et coût calculatoire. D’autre part, l’algorithme de diagnostic des jeux mécaniques est capable de détecter des niveaux de jeu relativement importants, mais il ne fournit pas de résultats cohérents pour des niveaux de jeu relativement faibles. En outre, des types d’entrée spécifiques sont nécessaires pour garantir des résultats répétitifs et cohérents. Des études complémentaires pourraient être menées afin de comparer les résultats de GLRT avec une approche Bayésienne et pour approfondir les possibilités et les limites de la méthode paramétrique proposée pour l’identification du modèle de Wiener
This research study is the result of a 3 years CIFRE PhD thesis between the Airbus design office(Aircraft Control domain) and TéSA laboratory in Toulouse. The main goal is to propose, developand validate a software solution for the detection and diagnosis of a specific type of elevator andrudder vibration, called limit cycle oscillation (LCO), based on existing signals available in flightcontrol computers on board in-series aircraft. LCO is a generic mathematical term defining aninitial condition-independent periodic mode occurring in nonconservative nonlinear systems. Thisstudy focuses on the LCO phenomenon induced by mechanical freeplays in the control surface ofa civil aircraft. The LCO consequences are local structural load augmentation, flight handlingqualities deterioration, actuator operational life reduction, cockpit and cabin comfort deteriorationand maintenance cost augmentation. The state-of-the-art for freeplay induced LCO detection anddiagnosis is based on the pilot sensitivity to vibration and to periodic freeplay check on the controlsurfaces. This study is thought to propose a data-driven solution to help LCO and freeplaydiagnosis. The goal is to improve even more aircraft availability and reduce the maintenance costsby providing to the airlines a condition monitoring signal for LCO and freeplays. For this reason,two algorithmic solutions for vibration and freeplay diagnosis are investigated in this PhD thesis. Areal time detector for LCO diagnosis is first proposed based on the theory of the generalized likeli hood ratio test (GLRT). Some variants and simplifications are also proposed to be compliantwith the industrial constraints. In a second part of this work, a mechanical freeplay detector isintroduced based on the theory of Wiener model identification. Parametric (maximum likelihoodestimator) and non parametric (kernel regression) approaches are investigated, as well as somevariants to well-known nonparametric methods. In particular, the problem of hysteresis cycleestimation (as the output nonlinearity of a Wiener model) is tackled. Moreover, the constrainedand unconstrained problems are studied. A theoretical, numerical (simulator) and experimental(flight data and laboratory) analysis is carried out to investigate the performance of the proposeddetectors and to identify limitations and industrial feasibility. The obtained numerical andexperimental results confirm that the proposed GLR test (and its variants/simplifications) is a very appealing method for LCO diagnostic in terms of performance, robustness and computationalcost. On the other hand, the proposed freeplay diagnostic algorithm is able to detect relativelylarge freeplay levels, but it does not provide consistent results for relatively small freeplay levels. Moreover, specific input types are needed to guarantee repetitive and consistent results. Further studies should be carried out in order to compare the GLRT results with a Bayesian approach and to investigate more deeply the possibilities and limitations of the proposed parametric method for Wiener model identification

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Dvořáček, Zdeněk. „Návrh hlavního podvozku pro letouny řady Zlín 40“. Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2021. http://www.nusl.cz/ntk/nusl-442850.

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This master thesis deals with the modernization of the main landing gear of the Z 143 LSi aircraft. The main emphasis is placed on optimizing of the landing gear shape and its deformation characteristics. Along with this change, variants made of different materials are examined. The landing load is calculated analytically and the load-bearing capacity of the structure is verified using the numerical FEM method. This work brings a possible replacement of the current chassis, which is production-intensive not only in time and money, but also in terms of cooperation with external companies. The objective is to design a new landing gear and verify the feasibility for the case of future implementation.

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Bauer, David O. „A historical perspective of aircrew systems effects on aircraft design“. Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1996. http://handle.dtic.mil/100.2/ADA320281.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, September 1996.
Thesis advisor(s): Conrad F. Newberry. "September 1996." Includes bibliographical references (p. 99-100). Also available online.

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Megas, Vasileios. „Aircraft to Aircraft Connectivity Analysis“. Thesis, KTH, Skolan för elektroteknik och datavetenskap (EECS), 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-254887.

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It is very common to feel the need to be connected, especially in cases where we are idle, such as in airplanes. Aircraft connectivity has already been implemented by using direct air-to-ground communication and satellite communication. However, since the current solutions are not satisfying, more ways to provide connectivity to aircraft are being researched. One solution is to use aircraft as relay nodes and forward signals to aircraft which are out of range of the ground base stations, creating an ad-hoc network.This thesis aims in evaluating the performance of such networks over the North Atlantic ocean in terms of connectivity and achievable data rate by means of simulations. First, an aircraft mobility model is created by analyzing past flight data. Then, the topology of the network is created with the purpose of maximizing the number of connected aircraft and minimizing interference. Finally, the available bandwidth is allocated to all connected aircraft in a maxmin way. The simulations were repeated to evaluate the impact of: threshold in data rates to assume connectivity, maximum number of connections per aircraft, maximum antenna steering angle, beamwidth and bandwidth.Our results show that aircraft to aircraft connectivity is feasible if all airlines cooperate, and more than 80% of the aircraft can find a path to a base station, when the aircraft density is higher than 1 aircraft per approximately 150000 km2, which is 88% of a 24 hours period. The median data rate of the connected aircraft, achieved in the middle of the ocean is limited to 25 Mbps with a 20MHz bandwidth, which is not high enough to provide access to demanding applications, such as video streaming. Increasing the bandwidth to 200 MHz can increase the data rate to more than 184 Mbps, for 50% of the connected aircraft, which surpasses the performance of current satellite communication systems.
Det är ganska vanligt att känna behovet av att sammankopplas, särskilt i fall där vi är inaktiva, exempelvis i flygplan. Flygplansanslutning har redan implementerats genom att utnyttja direkt luft till markkommunikation och satellitkommunikation. Men eftersom de befintliga lösningarna inte är tillfredsställande, undersöks fler sätt att tillhandahålla anslutning till flygplan. En lösning är att använda flygplan som relä knutpunkter och framåtsignaler till flygplan som ligger utanför markbasen, skapar ett adhocnätverk.Den här avhandlingen syftar till att utvärdera prestanda för sådana nätverk över Nordatlanten när det gäller anslutning och uppnåelig datahastighet genom simuleringar. För det första frambringas en flygplansmobilitet genom att analysera tidigare flygdata. Därefter åstadkommas nätets topologi med syftet att maximera antalet anslutna flygplan och minimera störningar. Slutligen tilldelas den tillgängliga bandbredden till alla anslutna flygplan på maximal väg. Simuleringarna upprepas för att utvärdera effekten av: tröskeln i datahastigheter för att mottaga anslutning, maximalt antal anslutningar per flygplan, max antennstyrvinkel, strålbredd och bandbredd.Våra resultat visar att flygplan till flygplansförbindelser är genomförbart om alla flygbolag samarbetar och mer än 80% av flygplanet kan sammankoppla, när flygplansdensiteten är högre än 1 flygplan per ungefär 150000 km2. Median datahastigheten uppnådd i mitten av havet är begränsad till 25 Mbps med en 20 MHz bandbredd, vilket inte är tillräckligt hög för att bringa tillgång till krävande applikationer, såsom videostreaming. Ö kning av bandbredd till 200 MHz kan öka datahastigheten mer än 184 Mbps, för 50% av de anslutna flygplanen, vilketöverträffar prestanda för de nuvarande satellitkommunikationssystemen.

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Federico, Claudio Antonio. „Dosimetria da radiação cósmica no interior de aeronaves no espaço aéreo Brasileiro“. Universidade de São Paulo, 2011. http://www.teses.usp.br/teses/disponiveis/85/85131/tde-26012012-104504/.

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Neste trabalho, cujo objetivo foi fornecer subsídios que permitam estabelecer um sistema de dosimetria para as tripulações de aeronaves que operam no território nacional, foi desenvolvida uma técnica para realizar medições do equivalente de dose ambiente em aeronaves. Foi testado um detector ativo, para uso embarcado em aeronaves, avaliando-se sua adequação a este tipo específico de medição, assim como sua suscetibilidade às interferências magnética e eletromagnética. O equipamento foi calibrado em campos metrologicamente rastreados e foi verificado em um campo especial do laboratório europeu CERN, que reproduz com grande proximidade o espectro de partículas existentes em altitudes de voo de aeronaves, sendo a seguir testado em diversos ensaios em voo, em uma aeronave da Força Aérea Brasileira. Os resultados foram avaliados e comparados com aqueles obtidos por diversos programas computacionais de estimativa de dose oriunda de radiação cósmica, com respeito à sua adequação para uso na região da América do Sul e foi selecionado o programa CARI-6 para avaliar as doses efetivas médias estimadas a que estão sujeitas as tripulações que operam nesta região. Foi efetuada uma avaliação estatística da distribuição de doses efetivas das tripulações dos voos que operam na região da América do Sul e Caribe e concluiu-se que grande parte destas tripulações estão sujeitas a doses efetivas anuais que ultrapassam o limite estabelecido para membros do público. Adicionalmente, foi proposto um dosímetro passivo preliminar, baseado em detectores termoluminescentes, e foram ainda estabelecidas colaborações internacionais com grupos de pesquisa do Reino Unido e da Itália, para a realização de medições conjuntas do equivalente de dose ambiente em aeronaves.
The objective of this work is the establishment of a dosimetric system for the aircrew in the domestic territory. A technique to perform measurements of ambient dose equivalent in aircrafts was developed. An active detector was evaluated for onboard aircraft use, testing its adequacy to this specific type of measurement as well as its susceptibility to the magnetic and electromagnetic interferences. The equipment was calibrated in standard radiation beams and in a special field of the European Laboratory CERN, that reproduces with great proximity the real spectrum in aircraft flight altitudes; it was also tested in several flights, in an Brazilian Air Force\'s aircraft. The results were evaluated and compared with those obtained from several computational programs for cosmic radiation estimatives, with respect to its adequacy for use in the South American region. The program CARI-6 was selected to evaluate the estimated averaged effective doses for the aircrew who operate in this region. A statistical distribution of aircrew effective doses in South America and Caribe was made, and the results show that a great part of this aircrew members are subjected to annual effective doses that exceed the dose limits for the members of the public. Additionally, a preliminary passive dosemeter, based in thermoluminescent detectors, was proposed; international collaborations with United Kingdom and Italy were established for joint measurements of the ambient equivalent doses in aircrafts.

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Serrano, Ignacio. „Unmanned Aircraft System (UAS) vs. Manned Aircraft System (MAS): A Military Aircraft Study“. Digital Commons at Loyola Marymount University and Loyola Law School, 2015. https://digitalcommons.lmu.edu/etd/430.

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Unmanned Aerial Vehicles (UAVs) are common place in the 21st century, whether they are small to medium sized remotely piloted vehicles (aka drones) or large advanced Unmanned Aerial Systems with a preprogrammed flight path. There is anticipation that these Unmanned Systems will, in the future assume the roles of their traditional manned aircraft counterparts. There is also the perception that these Unmanned Systems should be developed partly because they would be less expensive when compared to their manned aircraft. This integrative paper asserts that this perception is not reality with regards to developing a newly designed UAV to replace its manned counterpart, for the same mission. Through the examination of systems engineering principles between the unmanned RQ-4 Global Hawk and the manned U-2 Dragon Lady one will understand why this perception is not correct. Both aircraft perform the same mission of providing High Altitude Intelligence, Surveillance, and Reconnaissance (ISR). Through evaluation of requirements analysis both aircraft flowed down the requirements to all the various subsystems in a similar manner, creating similar subsystems for Imagery Intelligence (!MINT) and Signals Intelligence (SIGINT). However, the additional requirement for long endurance required that the Global Hawk systems engineers had additional requirements to flow down to the software, communications, data processing, and ground support subsystems in order to control an unmanned aircraft for greater than 24 hours. This one additional requirement had various derived requirements that needed to be verified, and validated during analysis, manufacturing, subsystem build and test, and final system integration. By using both System Integration Laboratories (SIL) and Flight Tests both systems requirements were verified and validated by the systems engineers. The Global Hawk since it was unmanned was required to perform more verification of subsystems and software as it was the first UAV to achieve flight airworthiness. The future of ISR missions requires that the aircraft become more adaptable to future technologies and situations. The U-2 has a modular configuration to change out to and from different subsystems depending on the mission. However, these subsystems were designed 20 to 30 years ago, and were not designed for lower level modularity or interoperability. The Global Hawk systems engineering team understood the future needs and the high level demand and data to be gathered and processed. The SE's developed modularity and interoperability requirements and flowed them down to the various subsystems. The Global Hawk system is more useful in highly contested areas of interest as there is no pilot; however resilient communications of the data and data link must be robust with anti-jamming capabilities to ensure the data is secure from cyber-attack. However,the U-2 is more survivable since it has a defense system, and can provide greater situational awareness. Taking all the general ISR requirements into consideration a trade study using a matrix was performed indicating that the Global Hawk is the most optimal solution to meeting both the current and future requirements for ISR missions. Even though the overall acquisition cost of the Global Hawk is equivalent to the U-2, systems engineering for Global Hawk had the responsibility to flow down requirements to all subsystems with consideration of the entire systems lifecycle. This is exemplified in that the Global Hawk is cost effective to fly in terms of cost per flight hour. Therefore, the Global Hawk can fulfill all the requirements of the given stakeholders with the lowest operational cost.

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Iskender, Hani. „Aircraft Simulator“. Thesis, Linköping University, Department of Electrical Engineering, 2005. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-2936.

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At Saab Bofors Dynamics there are projects running which purpose are to develop simulators for various weapon systems like RBS 70. In order to manage creating real working simulators Saab Bofors Dynamics has to do more research and this final thesis is a part of this process.

This final thesis has been performed at Saab Bofors Dynamics in the department of modelling and simulation, RTRKM, in Karlskoga. The purpose was to develop a control algorithm which makes it possible for an aircraft to behave real when controlling through a joystick.

The conclusions show that further improvements are needed before the aircraft behaves entirely by the laws of physics. Among other things it is necessary to decrease the number of delimitations that have been done.

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Thompson, Brian G. „Aircraft agility“. Thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-09192009-040436/.

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Hacker, Earl W. „One-year UDP: a cost/benefit analysis of a proposed alternative to the Marine Corps' Unit Deployment Program for fighter aviation“. Thesis, Monterey, California. Naval Postgraduate School, 1988. http://hdl.handle.net/10945/23337.

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Approved for public release; distribution is unlimited
The author examines the incremental costs and benefits associated with a change from six-month unit deployments to one-year unit deployments. The analysis is based primarily on five fighter squadrons participating in the Marine Corps' Unit Deployment Program and takes in the period July 1976 to October 1988. Regression analysis is used to project transportation cost savings of $4 million in real terms from FY 1989 through FY 1993. With a change to a one-year Unit Deployment Program, fighter squadrons should experience net increases in aircraft readiness, aircrew training readiness, and personnel retention.
http://archive.org/details/oneyearudpcostbe00hack
Lieutenant Colonel, United States Marine Corps

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Bücher zum Thema "Aircraf"

Bauer, David O. A historical perspective of aircrew systems effects on aircraft design. Monterey, Calif: Naval Postgraduate School, 1996.

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Parker, Steve. Aircraft. Broomall, Pa: Mason Crest, 2011.

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Aircraft. New York, N.Y: Universe, 1988.

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Maynard, Christopher. Aircraft. Minneapolis, MN: Lerner Publications, 1999.

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Langley, Andrew. Aircraft. New York: Bookwright Press, 1989.

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Aircraft. London: Reaktion, 2003.

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1928-, Roffe Michael, Hrsg. Aircraft. London: Piccolo, 1985.

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Langley, Andrew. Aircraft. London: Puffin, 1991.

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Santos, Julie Dos. Aircraft. New York: Marshall Cavendish Benchmark, 2010.

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Aircraft. London: Trefoil, 1987.

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Buchteile zum Thema "Aircraf"

Juson, Adam, und Catherine Juson. „Aircraft“. In Advances in the Biology and Management of Modern Bed Bugs, 363–67. Chichester, UK: John Wiley & Sons, Ltd, 2018. http://dx.doi.org/10.1002/9781119171539.ch38.

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Henke, Rolf. „Aircraft“. In Technology Guide, 304–9. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-88546-7_58.

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Paluszek, Michael, und Stephanie Thomas. „Aircraft“. In MATLAB Recipes, 249–72. Berkeley, CA: Apress, 2015. http://dx.doi.org/10.1007/978-1-4842-0559-4_11.

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Paluszek, Michael, und Stephanie Thomas. „Aircraft“. In MATLAB Recipes, 327–57. Berkeley, CA: Apress, 2020. http://dx.doi.org/10.1007/978-1-4842-6124-8_12.

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Kearns, Suzanne K. „Aircraft“. In Fundamentals of International Aviation, 36–80. 2. Aufl. Second edition. | Milton Park, Abingdon, Oxon; New York, NY: Routledge, 2021. |: Routledge, 2021. http://dx.doi.org/10.4324/9781003031154-2.

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Joslin, Robert E. „Certification of Aircraft and Aircraft Systems“. In Handbook of Human Factors in Air Transportation Systems, 147–93. Boca Raton : CRC Press, Taylor & Francis, [2018]: CRC Press, 2017. http://dx.doi.org/10.1201/9781315116549-8.

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Hadcock, Richard N. „Aircraft Applications“. In Handbook of Composites, 1022–43. Boston, MA: Springer US, 1998. http://dx.doi.org/10.1007/978-1-4615-6389-1_49.

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Isaksson, Marléne. „Aircraft Industry“. In Kanerva's Occupational Dermatology, 1257–60. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-02035-3_116.

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Isaksson, Marléne. „Aircraft Industry“. In Kanerva’s Occupational Dermatology, 1701–6. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-68617-2_116.

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Howe, Denis. „Aircraft Configuration“. In Aircraft Conceptual Design Synthesis, 23–52. Chichester, UK: John Wiley & Sons, Ltd, 2014. http://dx.doi.org/10.1002/9781118903094.ch2.

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Konferenzberichte zum Thema "Aircraf"

Xiao, Kun, Yuxin Chen, Wuyao Jiang, Chenyao Wang und Longfei Zhao. „Modeling, Simulation and Implementation of a Bird-Inspired Morphing Wing Aircraf“. In 2019 3rd International Conference on Robotics and Automation Sciences (ICRAS). IEEE, 2019. http://dx.doi.org/10.1109/icras.2019.8808959.

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Matula, Dominik, und Martin Bugaj. „Analysis of selected aircrafts suitable for PPL training“. In Práce a štúdie. University of Zilina, 2021. http://dx.doi.org/10.26552/pas.z.2021.2.25.

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The main goal of the paper is based on the analysis to define the criteria for selecting an aircraft suitable for PPL training. We achieved the main goal by meeting two sub-goals. The first sub-objective is the analysis of training organizations in Slovakia, on the basis of which we have selected entities for the second sub-objective thus the analysis of selected aircrafts suitable for PPL training. In this work we analyze three, most used training aircrafts for PPL training in Slovakia. We analyze selected aircrafts in terms of three main parts, which include, analysis of technical parameters, analysis of flight characteristics and analysis of operating parameters. Based on the given analyzes, we obtained an evaluation of the characteristics of selected aircrafts, their individual advantages and disadvantages. Other results of the work include the evaluation of criteria that are suitable for aircrafts designed for PPL training. This work can be applied in practice, especially when deciding on the selection of a training aircraft for a student or training organization.

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Venkatesan, Yaamunan, Rohitha Paruchuri und T. S. Ravigururajan. „A CFD Analysis of Transverse Airflow Around the Exterior of an Aircraft Fuselage Inside a Large Enclosure“. In ASME/JSME 2011 8th Thermal Engineering Joint Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/ajtec2011-44431.

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A model for predicting the airflow over the aircraft exterior with in a hangar is presented in this paper. The main reason behind this was to analyze the amount of air flowing over the aircraft at the time of painting, in order to dry the paint effectively and avoid possible hazardous effects on the people painting the aircraft. The air flow was supplied through the HVAC system in the hangar area. The HVAC system was available at the ceiling and air flows from the diffuser at the ceiling level. Grills were placed at the floor level in order to capture the air that flows down in the hangar area. The hangar area was split into three regions such that three aircrafts are placed for the purpose of painting. The three regions were separated with curtains between them which act as walls on the two sides for the aircraft at the center and walls on one side for aircrafts at the corner of the hangar area. A 2D model was simulated for the exterior airflow. Velocity of the air passing out of the diffuser was fixed at 0.56 m/s. The simulations were run at five different sections of the aircraft in order to simulate the airflow over the entire aircraft region on the exterior. The angle at which air flows from the diffuser is varied as 0°, 22.5°, 45°. This was performed in order to obtain the best possible angle at which air could be distributed in the hangar area, such that the aircraft is dried effectively at the time of painting. It was evident that the distribution of air along the aircraft exterior was more effective at diffuser angles of 0° and 22.5°. At 45° the airflow is directed away from the aircraft resulting in the circulation of air inside the hangar area.

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Templalexis, Ioannis, Ioannis Lionis und Sotiris Kitinos. „Correlation Between Engine and Aircraft Loadings for Several Mission Types“. In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15611.

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Abstract Fighter aircraft constitutes a well-defined class of aircraft. Their extensive use on a daily basis by operators stands as a strong motive behind studies that concern their rate of “exhaustion ”. For an aircraft operator either civil or military, it is very important at any point in time to have a clear view of the engines’ and the aircrafts’ operating condition. This is valuable information in order to foresee undesired incidences and in order to schedule missions in accordance to the actual and anticipated maintenance needs. For the latter, the operator would also need to know the rate of the engine and the aircraft life consumption per mission. The current study concerns the F-16 Block 52M aircraft, powered by the Pratt and Whitney F100-PW-229 engine. Aircraft is continuously subjected to crack growth mechanisms while flying. On the other hand, engines also go through Low Cycle Fatigue (LCF) cycles and creep prominent conditions while being in operation. The engine and the aircraft structural condition are continuously monitored, based on real time data recordings. To the extent of the authors’ knowledge, that is a common practice for most F-16 users. However, what was found to be missing from the international literature was a study to quantify any potential correlation between the aircraft loading and the engine loading for all typical mission types an aircraft of this type undertakes. For users that have already installed an aircraft loading monitoring system like “Aircraft Structural Integrity Program” (ASIP) it would be very useful to set a “rule of thumb” aside regarding the degree of correlation between aircraft and engine loading. Engine life consumption rate was estimated based on the creep and LCF failure mechanisms applied on the most critical engine section, the turbine. Engine recordings were picked from an arbitrary sample of 200 flights of a certain aircraft, wherein most typical mission types could be found. Turbine and subsequently blade temperature as well as blade stress were calculated using a very narrow time step. These data along with blade material data were fed in the Larson Miller model, to set an algorithm for estimating life consumption due to creep. Engine Total Accumulated Cycles (TACs) which account for LCF loading, are directly measured by the engine recorder, based on an embedded algorithm. Aircraft loading is calculated based on the accelerations the aircraft structures encounter during flight. These are also recorded under a very narrow time step. Last step was the correlation of the engine life consumption against the aircrafts’ loading for typical mission types. Scatter diagrams and statistical measures were used, in order to define the degree of correlation between them.

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Wesołowski, Mariusz, und Krzysztof Blacha. „The Impact of Load Bearing Capacity of Airfield Pavement Structures on the Air Traffic Safety“. In Environmental Engineering. VGTU Technika, 2017. http://dx.doi.org/10.3846/enviro.2017.124.

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Airfield pavement is a marked and appropriately prepared surface of an airfield functional element that performs a definite function in aircraft operations. The structure of airfield pavement is most often composed of a set of layers whose task is to absorb and transfer loads coming from moving aircraft onto the ground in a way that ensures its definite durability. Structures of airfield pavements are designed for a definite exploitation period on the assumption of predicted volume and structure of the air traffic. Safety of air operations conducted by aircrafts on airfield pavements depends mainly on the state of bearing capacity of their construction. Due to the above, control tests of bearing capacity shall be periodically conducted, since information regarding the current state of an airfield pavement constitutes the basis for decisions concerning the types of aircrafts permitted to land and take off, traffic volume and dates of starting renovation or modernization works. In addition to loads generated by aircraft, on the condition of airfield pavement load bearing capacity is influenced by many external factors, including weather conditions. The ACN-PCN non-destructive method is currently used in the assessment of airfield bearing capacity, which has been introduced by ICAO (ICAO 2013). According to its assumptions, the airfield construction bearing capacity may be expressed in PCN or permissible number of air operations. The fundamental problem by measuring airfield pavements is to assume the correct computational model of a structure, which describes the way of cooperation and mechanical properties of individual layers. This paper contains the way of assessing and description of PCN as well as presentation of the possibility of expressing bearing capacity results by determination of permissible number of aircraft operations. There is also interrelation between PCN and the permissible number of aircraft operations presented in a graphic way.

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Paruchuri, Rohitha, Yaamunan Venkatesan und T. S. Ravigururajan. „Modeling Airflow Inside an Aircraft Interior With Multiple Inlets and Outlets“. In ASME/JSME 2011 8th Thermal Engineering Joint Conference. ASMEDC, 2011. http://dx.doi.org/10.1115/ajtec2011-44432.

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A model for predicting the airflow inside an aircraft interior is presented in this paper. The objective was to optimize the amount of air flowing inside the aircraft at the time of painting, in order to dry the paint effectively and to minimize hazardous effects on the painting crew. The hangar area was split into three regions such that three aircrafts were placed for the purpose of painting. The three regions were separated with curtains between them which acted as separators between the aircraft. A 3D model of the aircraft fuselage with its openings was developed. The fuselage has two pilot doors, two escape hatches and two rear doors on each side of the aircraft. There are two dog houses at the bottom of the aircraft as doors to cargo section of the aircraft. Air flowing over the aircraft on the exterior is forced through into the aircraft through these eight openings provided. Air is forced out through the dog houses. The analysis was carried out for seven different scenarios in which the pilot and rear doors were chosen to be closed randomly. Two major constraints to maintain a minimum velocity of 100fpm (0.51 m/sec) throughout the inside of the aircraft and 12000 cfm (5.64 m3/sec) of air at each exit (dog houses). A minimum of 12000 cfm (5.64 m3/sec) at each exit was available in all scenarios, but the minimum requirement of 100 fpm (0.51 m/sec) was satisfactorily achieved only in which all the doors were open.

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Máčadi, Marek, und Alena Novák Sedláčková. „Legislative framework for an aircraft maintenance technician“. In Práce a štúdie. University of Žilina, 2021. http://dx.doi.org/10.26552/pas.z.2021.1.13.

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The purpose of this paper is to create up-to-date aviation legislations study material focused on the continuing airworthiness of aircraft and aeronautical products, parts and appliances, and on the approval of organisations and personnel involved in these tasks for future students of aircraft maintenance technology at the Air Transport Department, FPEDAS of the University of Žilina. As a relatively new studying programme, it has a lack of study materials in the field of aviation legislation, mainly in the field of aviation maintenance, whether in terms of technical requirements of aircrafts airworthiness or their certification. The first chapter of the paper is focused on a brief acquaintance with the history of aircraft maintenance and procedures applied in aircraft maintenance. We point to the modern history of aircraft maintenance, including EU legislation. In the second chapter, the work focuses on the international legal regulation of this issue as well as on the position of the International Civil Aviation Organization (ICAO) and the European Civil Aviation Safety Agency (EASA) and their activities in this area. In the following chapters, the paper deals with the current regulations of the EU Commission and Parts important not only for aircraft maintenance technicians, but also for training organizations in the field of aviation maintenance. In the end the paper deals with legislation necessary for the certification of an aircraft and requirements that are applied in the operation procedures of any civil aircraft for the purposes of commercial air transport.

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Hernandez-Rivera, Ricardo, Abel Hernandez-Guerrero, Cuauhtemoc Rubio-Arana und Raul Lesso-Arroyo. „Numerical Study in Wing Tip Vortex for a Modified Commercial Boeing Aircraft“. In ASME 2008 International Mechanical Engineering Congress and Exposition. ASMEDC, 2008. http://dx.doi.org/10.1115/imece2008-68149.

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Recent studies have shown that the use of winglets in aircrafts wing tips have been able to reduce fuel consumption by reducing the lift-induced drag caused by wing tip vortex. This paper presents a 3-D numerical study to analyze the drag and lift forces, and the behavior of the vortexes generated in the wing tips from a modified commercial Boeing aircraft 767-300/ER. This type of aircraft does not contain winglets to control the wing tip vortex, therefore, the aerodynamic effects were analyzed adding two models of winglets to the wing tip. The first one is the vortex diffuser winglet and the second one is the tip fence winglet. The analyses were made for steady state and compressible flow, for a constant Mach number. The results show that the vortex diffuser winglet gives the best results, reducing the core velocity of the wing tip vortex up to 19%, the total drag force of the aircraft up to 3.6% and it leads to a lift increase of up to 2.4% with respect to the original aircraft without winglets.

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Hallez, Raphael, Claudio Colangeli, Jacques Cuenca und Laurent De Ryck. „Impact of electric propulsion on aircraft noise – all-electric light aircrafts case study“. In 2018 AIAA/IEEE Electric Aircraft Technologies Symposium. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-4982.

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Kupciuniene, Kristina, und Robertas Alzbutas. „External Events Importance for Safety of the Ignalina Nuclear Power Plant“. In 16th International Conference on Nuclear Engineering. ASMEDC, 2008. http://dx.doi.org/10.1115/icone16-48230.

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Probabilistic risk analysis of external events impact on the safety important systems of Ignalina nuclear power plant (NPP) is performed. At first, the methodology was established for screening out external events, which impact on Ignalina NPP safety is not significant. In order to estimate probabilities of external events occurrences the statistical data were collected, mathematical models were constructed and probabilities of these events occurrences were determined. For risk estimation, the following external events were studied: forest fires, external floods, aircraft crash, seismic events, extreme winds, fall of frequency in electricity network and loss of an external electricity supply. The aircraft crash event was modeled and analyzed in more detail. The crash probability estimation model is improved considering uncertain data. The aircraft crash probability on the territory of the Ignalina NPP with the radius r is expressed by the derived analytical formula. This formula is used to calculate the aircraft crash probability applying the most recent statistical data. The aircraft crash dependencies upon the amount of flights and crashes in the different radius territories were analyzed. Relationship of non-flying zone around Ignalina NPP and aircraft crash frequency was investigated. As a part of the initial conditions and parameters of aircraft crash model are not well-known or have different values for various types of aircrafts, the sensitivity analysis was performed for the model. This analysis determines the parameters that have the greatest influence on the model results. Conclusions about the importance of the parameters and sensitivity of the results are obtained using a sensitivity measures of the model under analysis.

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Berichte der Organisationen zum Thema "Aircraf"

Reason, William. Helicopter Aircrew Integrated Life Support System (HAILSS) Aircraft Integration Tests. Fort Belvoir, VA: Defense Technical Information Center, April 1999. http://dx.doi.org/10.21236/ada377892.

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Anderson, Jay, Dan Bowman, Douglas Burke, Edward Campbell und Barry Coble. Aircraft. Fort Belvoir, VA: Defense Technical Information Center, Januar 2002. http://dx.doi.org/10.21236/ada424435.

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Lee, E. U., R. Taylor, C. Lei und H. C. Sander. Aircraft Steels. Fort Belvoir, VA: Defense Technical Information Center, Februar 2009. http://dx.doi.org/10.21236/ada494348.

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Spicer, John, Fadel M. Al Garni, Deborah Bereda, Janusz Bojarski, Bill Braley, John Celigoy, David Chandler, Bruce Crawford, Brian Goodwin und Linda Haines. Aircraft Industry. Fort Belvoir, VA: Defense Technical Information Center, Januar 2007. http://dx.doi.org/10.21236/ada475111.

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Ehst, David A. Commercial Aircraft Protection. Office of Scientific and Technical Information (OSTI), Oktober 2016. http://dx.doi.org/10.2172/1346573.

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Chapa, Mark A. Predicting Aircraft Availability. Fort Belvoir, VA: Defense Technical Information Center, Juni 2013. http://dx.doi.org/10.21236/ada580972.

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ARMY WAR COLL CARLISLE BARRACKS PA. Aircraft Rotor Surface Coating Qualification Testing Aircraft Rotor Surface Coating. Fort Belvoir, VA: Defense Technical Information Center, Oktober 2006. http://dx.doi.org/10.21236/ada481301.

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Simoncic, Adam D. Aircraft Block Speed Calculations for JOSAC/USTRANSCOM Aircraft Using Linear Regression. Fort Belvoir, VA: Defense Technical Information Center, Juni 2013. http://dx.doi.org/10.21236/ada580613.

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Teague, Edward, Jr Kewley und Robert H. Swarming Unmanned Aircraft Systems. Fort Belvoir, VA: Defense Technical Information Center, September 2008. http://dx.doi.org/10.21236/ada488664.

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K. Ashley. Identification of Aircraft Hazards. Office of Scientific and Technical Information (OSTI), Dezember 2006. http://dx.doi.org/10.2172/899282.

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