Gotowe bibliografie tematyczne / Aircraft

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Gotowa bibliografia na temat „Aircraft”

Autor: Grafiati

Data publikacji: 4 czerwca 2021

Data aktualizacji: 9 września 2024

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Artykuły w czasopismach na temat "Aircraft"

Yao, Xinchi. "Differences in large aircraft design between military and civil perspectives". Theoretical and Natural Science 14, nr 1 (30.11.2023): 112–16. http://dx.doi.org/10.54254/2753-8818/14/20240908.

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Military transport aircrafts and civil aircrafts are important parts of the aviation field. With the development of aviation technology and the specificity of aircraft functions, the design of military transport aircraft and civil aircraft gradually differs according to application scenarios. However, in the aircraft design, military transport aircrafts and civil aircrafts still have a lot of mutual references. Analyzing the differences between them and the reasons for the differences may contribute to the design and development of military transport aircraft and civil aircraft in the future, and provide reference suggestions for the design of civil aircraft in the context of the civil-military integration. In this article, the application scenarios and functions of military transport aircraft and civil aircraft are analyzed, as well as the special situation of civil aircraft research and development. This article may offer a reference for the future research and development of military transport aircraft and civil aircraft.

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Olugbeji, Jemitola P., Okafor E. Gabriel i Godwin Abbe. "Wing Thickness Optimization for Box Wing Aircraft". Recent Patents on Engineering 14, nr 2 (29.10.2020): 242–49. http://dx.doi.org/10.2174/1872212113666190206123755.

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Background: In the interest of improving aircraft performance, studies have highlighted the benefits of Box wing configurations over conventional cantilever aircraft configuration. Generally, the greater an aircraft's average thickness to chord ratio (τ), the lower the structural weight as well as volumetric capacity for fuel. On the other hand, the lower the ., the greater the drag reduction. A review of patents related to the Box-wing aircraft was carried out. While methodologies for optimizing wing thickness of conventional aircrafts have been studied extensively, limited research work exist on the methodology for optimizing the wing thickness to chord ratio of the Box wing aircraft configurations. Methods: To address this gap, in this work, a two stage optimization methodology based on gradient search algorithm and regression analysis was implemented for the optimization of Box wing aircrafts wing thickness to chord ratio. The first stage involved optimizing the All Up Mass (AUM), Direct Operating Cost (DOC) and Zero Lift Drag Coefficients (CDO), with respect to the aft and fore sweep angle for some selected τ values. At the second stage, a suitability function (γ) was optimized with respect to the aft and fore sweep angle for some selected τ values. A comparative study was further carried out using the proposed methodology on similar size cantilever wing aircraft. Results: From the result, an optimal τ value was reached. Also the τ value for the cantilever aircraft found based on the proposed methodology was similar to the true τ value of the adopted aircraft, thereby validating the methodology. Conclusion: Based on the optimal τ value reached from this work, the Box wing aircraft are suitable for thin airfoils.

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Yao, Dongdong, i Qunli Xia. "Finite-Time Convergence Guidance Law for Hypersonic Morphing Vehicle". Aerospace 11, nr 8 (18.08.2024): 680. http://dx.doi.org/10.3390/aerospace11080680.

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Aiming at the interception constraint posed by defensive aircrafts against hypersonic morphing vehicles (HMVs) during the terminal guidance phase, this paper designed a guidance law with the finite-time convergence theory and control allocation methods based on the event-triggered theory, achieving evasion of the defensive aircraft and targeting objectives for a morphing vehicle in the terminal guidance phase. Firstly, this paper established the aircraft motion model; the relative motion relationships between HMV, defensive aircraft, and target; and the control equations for the guidance system. Secondly, a guidance law with finite-time convergence was designed, establishing a controller with the angle between the aircraft–target–defense aircraft triplet as the state variable and lift as the control variable. By ensuring the angle was non-zero, the aircraft maintained a certain relative distance from the defense aircraft, achieving evasion of interception. The delay characteristic of the aircraft’s flight controller was considered, analyzing its delay stability and applying control compensation. Thirdly, a multi-model switching control allocation method based on an event-triggered mechanism was designed. Optimal attack and bank angles were determined based on acceleration control variables, considering different sweep angles. Finally, simulations were conducted to validate the effectiveness and robustness of the designed guidance laws.

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Hong, Wei Jiang, i Dong Li Ma. "Influence of Control Coupling Effect on Landing Performance of Flying Wing Aircraft". Applied Mechanics and Materials 829 (marzec 2016): 110–17. http://dx.doi.org/10.4028/www.scientific.net/amm.829.110.

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As flying wing aircraft has no tail and adopts blended-wing-body design, most of flying wing aircrafts are directional unstable. Pitching moment couples seriously with rolling and yawing moment when control surfaces are deflected, bringing insecurity to landing stage. Numerical simulation method and semi-empirical equation estimate method were combined to obtain a high aspect ratio flying wing aircraft’s aerodynamic coefficients. Modeling and simulation of landing stage were established by MATLAB/Simulink. The control coupling effect on lift and drag characteristics and anti-crosswind landing capability was studied. The calculation results show that when the high aspect ratio flying wing aircraft was falling into the deceleration phase, appropriate to increase the opening angle of split drag rudder can reduce the trimming pitching moment deflection of pitch flap, thereby reduce the loss of lift caused by the deflection of pitch flaps. Flying wing aircraft can be rounded out successfully by using the pitch flap gently and steady. Both side-slip method and crabbed method can be applied to the landing of high aspect ratio flying wing aircraft in crosswind, the flying wing aircraft’s anti-crosswind landing capability was weakened by the control coupling effect of split drag rudder and elevon. Sideslip method was recommended in the crosswind landing of flying wing aircraft after calculation and analysis.

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Fujita, Etsushi, Taichi Higashioka, Manabu Sugiura i 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 (1.08.2021): 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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Rogalski, Tomasz, i Boguslaw Dołęga. "THE METHOD OF EVALUATION OF THE AIRCRAFT CONTROL SYSTEM". Aviation 9, nr 2 (30.06.2005): 29–34. http://dx.doi.org/10.3846/16487788.2005.9635901.

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The dynamical development of general aviation demands compilation of new aircraft control methods. Those methods allow people without special airborne qualifications to pilot these aircrafts. The main goals of such a control system are to reduce a pilot's load, to improve control precision, and to protect an aircraft against dangerous situations. There are many criterions applied to grading and describing an aircraft's flying characteristics and the handling qualities of general aviation airplanes equipped with classical mechanical control systems. But a modern, small, transport aircraft should be equipped with fly‐by‐wire control systems, and there are no clear, straight, rules rate and describe the handling qualities of small airplanes with fly‐by‐wire control systems. This paper presents a methodology created by the authors that classifies and compares the handling qualities of general aviation aircraft equipped with fly‐by‐wire control systems. It takes into consideration two parameters: pilot's effort during realization of ordered tasks and precision of his control.

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Xie, Naiming. "Estimating civil aircraft’s research and manufacture cost by using grey system model and neural network algorithm". Grey Systems: Theory and Application 5, nr 1 (2.02.2015): 89–104. http://dx.doi.org/10.1108/gs-12-2014-0054.

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Purpose – The purpose of this paper is to propose novel civil aircraft cost parameters’ selection method and novel cost estimation approach for civil aircraft so as to effectively simulate or forecast civil aircraft cost under poor information and small sample. Design/methodology/approach – Based on existent cost estimation indexes, this paper summarized civil aircraft research and manufacturing cost impact index system and adopted grey relational model to select most important impact factors. Consider civil aircrafts’ cost information could not be easily collected, the author must estimate their costs with limited sample and poor information. A combination model of GM (0, N) model and BP neural network algorithm is proposed. Both advantages of simulation of BP neural network algorithm and poor information generation of GM (0, N) were effectively combined. Then steps of combined model were given out. Finally, nine types of aircrafts were used to test the validity of proposed model. As comparing with the traditional multiple linear regression model and simple GM (0, N) model, results indicated that proposed model can do the work better. Findings – Grey relational model can be applied for parameters’ selection and combined GM (0, N) model and BP neural network algorithm can estimate aircraft’s cost as well. Results show that novel combined model could get high forecasting accuracy. Practical implications – Cost estimation is key problem in production management of civil aircraft. Effective cost management could promote competitiveness of aircraft manufacturing company. Proposed combined model can be applied for civil aircraft cost estimation. Similarly, it could be applied for other complex equipment cost estimation. Originality/value – The paper succeeds in proposing grey relational model for cost parameters’ selection and constructing a combination model of GM (0, N) model and BP neural network algorithm. Algorithm of the proposed model was discussed and steps were given out.

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Sharma, Vaibhav. "Fanwing Aircraft- Scope as an Agricultural Aircraft". International Journal for Research in Applied Science and Engineering Technology 9, nr VIII (15.08.2021): 603–7. http://dx.doi.org/10.22214/ijraset.2021.37436.

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The objective of this paper is to apply the concept of fan wing to agricultural aircrafts which are conventionally fixed wings aircrafts or multi-rotor drones. Fan wing is capable of producing good amount of lift at a sufficiently low speed without stalling, thus is apt for agricultural processes of irrigation, spraying pesticides, etc. Fan wing has a special ability that it doesn’t stalls (for the practical range of AOA), making this spraying method reliable. A fanwing aircraft is modelled using CATIA V5 and the flow visualizations for the same are performed on the ANSYS. This aircraft is then compared with three different existing agricultural aircrafts on different parameters, namely payload capacity, work efficiency and ease of operation. The comparison shows that such fanwing vehicle is a good substitute over the conventional fixed wings and multi-rotor drones.

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Wang, Hong Yong, Rui Ying Wen i Yi Fei Zhao. "Empirical Research on Topological Characteristics of Air Traffic Situation Network". Applied Mechanics and Materials 744-746 (marzec 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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Zuo, Yu Yu. "Analysis of Gas Turbine Engines Auxiliary Power Units". Applied Mechanics and Materials 533 (luty 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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Rozprawy doktorskie na temat "Aircraft"

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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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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Sychova, I. U., i E. I. Zolotova. "Supersonic aircraft". Thesis, Вид-во СумДУ, 2011. http://essuir.sumdu.edu.ua/handle/123456789/22211.

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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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Black, Gary Douglas. "Aircraft configuration study for experimental 2-place aircraft and RPVs". Thesis, Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA227604.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, March 1990.
Thesis Advisor(s): Howard, Richard M. Second Reader: Hauser, James P. "March 1990." Description based on signature page as viewed on August 25, 2009. DTIC Descriptor(s): Aerodynamic configurations, remotely piloted vehicles, military aircraft, lightweight, research aircraft, canard configurations, wings, aerodynamic drag, computer programs, scaling factor, aerodynamic stability, performance(engineering), comparison, microcomputers, trade off analysis, aeronautical engineering, theses. DTIC Identifier(s): Pusher propellers, Tandem wing aircraft, Joined wing aircraft, Three surface aircraft. Author(s) subject terms: Aircraft design, remotely piloted vehicle, RPV, configuration, experimental Includes bibliographical references (p. 121-123). Also available online.

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Wan, Husain Wan Mohd Sufian Bin. "Maintainability prediction for aircraft mechanical components utilising aircraft feedback information". Thesis, Cranfield University, 2011. http://dspace.lib.cranfield.ac.uk/handle/1826/7272.

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The aim of this research is to propose an alternative approach to determine the maintainability prediction for aircraft components. In this research, the author looks at certain areas of the maintainability prediction process where missteps or misapplications most commonly occur. The first of these is during the early stage of the Design for Maintainability (DfMt) process. The author discovered the importance of utilising historical information or feedback information. The second area is during the maintainability prediction where the maintenance of components is quantified; here, the author proposes having the maximum target for each individual maintainability component. This research attempts to utilise aircraft maintenance historical data and information (i.e. feedback information systems). Aircraft feedback information contains various types of information that could be used for future improvement rather than just the failure elements. Literature shows that feedback information such as Service Difficulty Reporting System (SDRS) and Air Accidents Investigation Branch, (AAIB) reports have helped to identify the critical and sensitive components that need more attention for further improvement. This research consists of two elements. The first is to identity and analyse historical data. The second is to identify existing maintainability prediction methodologies and propose an improved methodology. The 10 years’ data from Federal Aviation Administration (FAA) SDRS data of all aircraft were collected and analysed in accordance with the proposed methodology before the processes of maintainability allocation and prediction were carried out. The maintainability was predicted to identify the potential task time for each individual aircraft component. The predicted tasks time in this research has to be in accordance with industrial real tasks time were possible. One of the identified solutions is by using maintainability allocation methodology. The existing maintainability allocation methodology was improved, tested, and validated by using several case studies. The outcomes were found to be very successful. Overall, this research has proposed a new methodology for maintainability prediction by integrating two important elements: historical data information, and maintainability allocation. The study shows that the aircraft maintenance related feedback information systems analyses were very useful for deciding maintainabilityeffectiveness; these include planning, organising maintenance and design improvement. There is no doubt that historical data information has the ability to contribute an important role in design activities. The results also show that maintainability is an importance measure that can be used as a guideline for managing efforts made for the improvement of aircraft components.

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Ionescu, Irina Gabriela. "Aircraft noise regulation". Thesis, McGill University, 2004. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=82660.

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Aircraft noise is one of the most controversial environmental concerns in the aviation industry, partly due to the difficulty in harmonizing countries' regulation regarding this issue. The purpose of this thesis is to analyze the ways in which aircraft noise is regulated at the national and international levels, and to compare the legislative responses to aircraft noise issues in Europe and North America. Each of the four main chapters of the thesis takes into consideration a different aspect of the problem. The first chapter describes the objective and subjective ways of measuring aircraft noise. This process is necessary in order to allow the legislation to meet its purpose, namely, to protect the environment, the sources of the aircraft noise, and the effects of the aircraft noise on people. The second chapter describes the evolution of aircraft noise issues at the national levels in the US and throughout the EU, respectively, as well as at the international level, such as at the ICAO. The third chapter analyses the EU Regulation 925/1999, which created tension between the EU and the US due to its alleged discriminatory nature. This thesis examines the arguments of both sides. Finally, the fourth chapter analyses the noise certification standards developed by ICAO, namely the "balanced approach".

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彭遠輝 i Yuen-fai Alson Pang. "Managing aircraft noise". Thesis, The University of Hong Kong (Pokfulam, Hong Kong), 2002. http://hub.hku.hk/bib/B31255280.

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Wagner, Michael J. "AEW aircraft design". Thesis, Monterey, California. Naval Postgraduate School, 1992. http://hdl.handle.net/10945/23815.

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Książki na temat "Aircraft"

Kershaw, Andrew. Aircraft. New York: Derrydale Books, 1992.

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Buydos, John F. Aircraft. Washington, D.C. (101 Independence Ave., S.E., Washington 20540-4750): Science Reference Section, Science, Technology and Business Division, Library of Congress, 2000.

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Schaefer, Lola M. Aircraft. Oxford: Raintree, 2004.

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

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Gunston, Bill. Aircraft. New York: F. Watts, 1986.

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

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Ian, Graham. Aircraft. London: Belitha, 1997.

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Hawes, Alison. Aircraft. Oxford: Oxford University Press, 2010.

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Bill, Gunston. Aircraft. London: Franklin Watts/Aladdin, 1985.

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Steve, Parker. Aircraft. Great Bardfield: Miles Kelly, 2009.

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Części książek na temat "Aircraft"

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

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Juson, Adam, i Catherine Juson. "Aircraft". W 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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Kalić, Milica, Slavica Dožić i Danica Babić. "Aircraft". W Introduction to the Air Transport System, 30–68. Boca Raton: CRC Press, 2022. http://dx.doi.org/10.1201/9781003102533-2.

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Paluszek, Michael, i Stephanie Thomas. "Aircraft". W 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". W Fundamentals of International Aviation, 36–80. Wyd. 2. 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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Henke, Rolf. "Aircraft". W 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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Pleter, Octavian Thor. "Aircraft". W Air Navigation, 283–350. Cham: Springer Nature Switzerland, 2024. http://dx.doi.org/10.1007/978-3-031-52994-8_7.

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Joslin, Robert E. "Certification of Aircraft and Aircraft Systems". W 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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Schmitt, Dieter, i Volker Gollnick. "Aircraft Characteristics". W Air Transport System, 107–55. Vienna: Springer Vienna, 2015. http://dx.doi.org/10.1007/978-3-7091-1880-1_5.

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Schmitt, Dieter, i Volker Gollnick. "Aircraft Manufacturer". W Air Transport System, 157–86. Vienna: Springer Vienna, 2015. http://dx.doi.org/10.1007/978-3-7091-1880-1_6.

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Streszczenia konferencji na temat "Aircraft"

Prather, William. "Coupling to aircraft and aircraft hardening". W 2008 IEEE International Symposium on Electromagnetic Compatibility - EMC 2008. IEEE, 2008. http://dx.doi.org/10.1109/isemc.2008.4652198.

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Bickmeier, Laura, i Ronald Ankner. "Aircraft to Aircraft Collision Risk Modeling". W 2024 Integrated Communications, Navigation and Surveillance Conference (ICNS). IEEE, 2024. http://dx.doi.org/10.1109/icns60906.2024.10550662.

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Lou, Bin. "Preliminary Design of Several New Kinds of Martian Aircrafts". W Vertical Flight Society 77th Annual Forum & Technology Display. The Vertical Flight Society, 2021. http://dx.doi.org/10.4050/f-0077-2021-16736.

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The low-altitude Martian aircraft has become an important research direction in the field of Mars exploration recently. The traditional Martian aircrafts including floating balloons, fixed-wing aircrafts, rotorcrafts, flapping-wing aircrafts and tilt-rotor aircrafts, have been proposed and studied for decades. In this paper, several new kinds of Martian aircraft were proposed, maybe enlightening other researchers. Compressed-air jet aircraft makes use of the CO2 for airjet to control the flight. Coaxial tri-rotor autogyro is designed with three rotors, modified from "Ingenuity" with light weight and simple structure. Jumping-flying aircraft gets the utmost out of elastic potential energy to work in high energy efficiency.

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Robinson, Derek, James Bonn i Daniel Murphy. "Aircraft Turnaround Times and Aircraft Itinerary Generation". W 11th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-6848.

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Szurgyi, Stephen, Sanjiv Shresta, Dejan Neskovic, James DeArmon i Scott Williams. "Analysis of observed aircraft-to-aircraft separations". W 2008 Integrated Communications, Navigation and Surveillance Conference (ICNS). IEEE, 2008. http://dx.doi.org/10.1109/icnsurv.2008.4559166.

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Mlynarčík, Martin, i Michal Janovec. "Conversion of passenger aircraft to cargo versions". W Práce a štúdie. University of Žilina, 2022. http://dx.doi.org/10.26552/pas.z.2022.1.23.

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In this presented paper on the topic of conversion of passenger aircrafts to cargo versions, the use of this transformation in the modern history of aviation is analyzed and the current situation is analyzed. For a better introduction to the issue, the introductory part defines the fundamental terms and explains the conversion itself and its various stages. The paper also discusses the companies that provide services for the actual conversion of passenger aircraft and the location where this process takes place. The paper is further supplemented by individual types of aircraft, which are divided according to global manufacturers such as the American Boeing and its European competitor Airbus. The main goal of this paper is to bring closer and clarify this process, which has gained momentum in recent years and has great potential for the future. This paper is very significant in case of COVID-19 pandemic and its huge influence on general aviation when there is enormous demand of conversion passenger aircrafts to cargo versions. The most common causes of conversion, advantages and disadvantages are also included. The conversion process itself is described in more detail and the paper focuses on the various technical phases of the aircraft conversion itself.

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Haluzová, Kristína, Martin Bugaj i Michal Hrúz. "Aircraft airfoils". W Práce a štúdie. University of Žilina, 2023. http://dx.doi.org/10.26552/pas.z.2023.1.01.

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This work deals with the airfoils of aircraft. First of all, it focuses on the general properties of wings. Furthermore, the work deals with the issue of various types of wing shape and compares individual shapes of airfoils, their properties and gradual development. Next, current wings of commercial aircraft are described, dealing with the materials used, types of winglets, mechanization of the wing and also different uses of the airfoils. The work also describes and compares wings of two famous commercial airliners – Boeing 737-800 and Airbus A320-200. In the end, the work also focuses on various concepts of the wings of the future, and how sustainability affects future development.

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Máčadi, Marek, i Alena Novák Sedláčková. "Legislative framework for an aircraft maintenance technician". W 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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Proctor, Fred. "Interaction of Aircraft Wakes From Laterally Spaced Aircraft". W 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-343.

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Ryan, Hollis, i Mike Paglione. "Performance Metrics for Tactical Aircraft to Aircraft Conflicts". W AIAA Guidance, Navigation and Control Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-6518.

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Raporty organizacyjne na temat "Aircraft"

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

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Lee, E. U., R. Taylor, C. Lei i H. C. Sander. Aircraft Steels. Fort Belvoir, VA: Defense Technical Information Center, luty 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 i Linda Haines. Aircraft Industry. Fort Belvoir, VA: Defense Technical Information Center, styczeń 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), październik 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, czerwiec 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, październik 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, czerwiec 2013. http://dx.doi.org/10.21236/ada580613.

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

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

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Muth, Thomas R., i William H. Peter. Aircraft Propeller Hub Repair. Office of Scientific and Technical Information (OSTI), luty 2015. http://dx.doi.org/10.2172/1185928.

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