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1
Kuzmin, Yu V. „Passenger airplane manufacturing in the 20th century. Quantitative analysis“. Civil Aviation High Technologies 26, Nr. 3 (23.06.2023): 8–24. http://dx.doi.org/10.26467/2079-0619-2023-26-3-8-24.
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The statistics on the production and development of passenger airplanes in the world is presented in this article for the first time. The methods for obtaining the results are described, uncertainties of the results are estimated. It is specified what exactly is considered to be a passenger airplane. It is shown that only 60,000 passenger airplanes were built during the entire 20th century. This is less than 3% of the total production of airplanes of all classes. Their total capacity amounts less than 5 million people, or less than a thousandth of the world’s population by the end of the last century. These 60,000 airplanes provided unprecedented mobility of the population. It was revealed that the leading role in the passenger airplane manufacturing belonged to the USA, the USSR took a steady second place. The ups-and-downs in airplane production are described, including the recessions during the Great Depression, World War II and the global economic decline (in the USSR, the USA and other countries) in the early 1960s, which was replaced by a rapid increase in output. It is indicated that the number of airplanes produced in the last third of the 20th century remained approximately constant, but their average capacity was growing rapidly, which largely ensured the explosive growth of air transportation during this period. The dynamics of the dead weight per one passenger is given. The dynamics of the number of the new passenger airplane models is presented. It is shown that for the last 30 years of the century their number was approximately constant, and almost all the models that reached the test stage were put into serial production. In the period between the world wars, however, about half of all models tested in flight remained prototypes. The change in the ratio of the number of airplanes by the number of engines is given. The renaissance of three-engine airplanes in the 1960s, the almost complete disappearance of singleengine passenger airplanes by the end of the century and the stable amount of a small proportion of four-engine airplanes for the last 30 years of the past century are noted.
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Rogalski, Tomasz, und Boguslaw Dołęga. „ALGORITHMS IMPROVING FLYING QUALITIES OF GENERAL AVIATION AIRCRAFT“. Aviation 10, Nr. 2 (30.06.2006): 17–21. http://dx.doi.org/10.3846/16487788.2006.9635930.
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The dynamic growth of general aviation as a mean of transport over medium distances means that people having no extraordinary qualifications or extraordinary physical or mental abilities more often pilot such types of airplanes. This phenomenon creates the necessity of giving planes flying qualities that allow them to be safely piloted by ordinary people. One way of solving this problem is equipping airplanes with fly‐by‐wire control systems that modify their handling qualities. Then the computer included into such control systems modifies the actions taken by the pilot, making the airplane both easier and more comfortable to control. This paper presents sample software tools – control algorithms that allowing an airplane's handling qualities to be improved. They are prepared by the authors and tested on board an experimental plane. That plane was equipped with a prototypical fly‐by‐wire control system, which can modify a plane's responses to a pilot's actions.
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Morad, Alaa M. „Multidisciplinary conceptual investigation for integrating stores, not in the original configuration of a subsonic airplane“. Journal of Physics: Conference Series 2616, Nr. 1 (01.11.2023): 012005. http://dx.doi.org/10.1088/1742-6596/2616/1/012005.
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Abstract Subsonic airplanes are widely used around the world in applications such as pilot training, transportation, sports activities, insect fighting, and field monitoring. This research deals with airplanes that already own the capability of carrying suspended loads. Increasing the airplane’s capabilities and configurations by integrating different suspended loads like smaller or larger external fuel tanks or insecticide tanks that are not in the original configuration of the airplane is a great advantage. This modification can be done without dramatic changes to the airplane and with minimum cost. In this research, a multidisciplinary methodology is used to integrate a commercially-available premade external fuel tank into the Embraer E312 Tucano airplane which is not in the original configuration of the airplane. First, a geometrical analysis is performed to ensure the availability of proper installation. This study leads to the design of an adaptor between the tank and the airplane pylon, then, a computational fluid dynamics (CFD) modeling using ANSYS-CFX is performed to evaluate aerodynamic forces and moments applied on the new fuel tank. Furthermore, finite element modeling using ANSYS-Static structure is performed by applying the aerodynamic and inertial loads to calculate the adaptor’s stresses and structure safety factor. Finally, vibration fatigue analysis-based power spectral densities are developed using ANSYS-Random vibration to calculate the adaptor’s estimated lifetime to ensure the store system’s safety by applying airplane vibration acceleration spectral density pattern selected from applicable standard. In this typical example, the above-mentioned methodology is applied and the results are acceptable.
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Shi, Fan, Fang Qiu, Xiao Li, Yunwei Tang, Ruofei Zhong und Cankun Yang. „A Method to Detect and Track Moving Airplanes from a Satellite Video“. Remote Sensing 12, Nr. 15 (25.07.2020): 2390. http://dx.doi.org/10.3390/rs12152390.
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In recent years, satellites capable of capturing videos have been developed and launched to provide high definition satellite videos that enable applications far beyond the capabilities of remotely sensed imagery. Moving object detection and moving object tracking are among the most essential and challenging tasks, but existing studies have mainly focused on vehicles. To accurately detect and then track more complex moving objects, specifically airplanes, we need to address the challenges posed by the new data. First, slow-moving airplanes may cause foreground aperture problem during detection. Second, various disturbances, especially parallax motion, may cause false detection. Third, airplanes may perform complex motions, which requires a rotation-invariant and scale-invariant tracking algorithm. To tackle these difficulties, we first develop an Improved Gaussian-based Background Subtractor (IPGBBS) algorithm for moving airplane detection. This algorithm adopts a novel strategy for background and foreground adaptation, which can effectively deal with the foreground aperture problem. Then, the detected moving airplanes are tracked by a Primary Scale Invariant Feature Transform (P-SIFT) keypoint matching algorithm. The P-SIFT keypoint of an airplane exhibits high distinctiveness and repeatability. More importantly, it provides a highly rotation-invariant and scale-invariant feature vector that can be used in the matching process to determine the new locations of the airplane in the frame sequence. The method was tested on a satellite video with eight moving airplanes. Compared with state-of-the-art algorithms, our IPGBBS algorithm achieved the best detection accuracy with the highest F1 score of 0.94 and also demonstrated its superiority on parallax motion suppression. The P-SIFT keypoint matching algorithm could successfully track seven out of the eight airplanes. Based on the tracking results, movement trajectories of the airplanes and their dynamic properties were also estimated.
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Endara Julio, Álvarez, Susan Sardinas Castellón, Parra Nigañes Patricia, Arancibia Marianela und Nuñes Prado Natalia. „Case report: Thrombosis in children“. Hematology & Transfusion International Journal 8, Nr. 5 (30.10.2020): 105–6. http://dx.doi.org/10.15406/htij.2020.08.00235.
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Objective: We examined the effects of passenger air transport by regular airplanes for air transportation on blood for transfusion. Materials and methods: Irradiated red blood cell (RBC) solutions were transported by regular passenger airplanes which and were static in the cabin during the flight. Blood samples were evaluated visually and biochemically before and after transport. Hemolysis of the transported samples was compared to that of the non-transported ones. The vibration in the airplanes was also measured using a vibration data logger. Results: There was no significant hemolysis of RBCs during airplane transport. The vibration in the airplane was lower than that in automobiles. The temperature in the active transport refrigerator (ATR) room was maintained at 2−6°C. There was no significant hemolysis of RBCs during the two transport routes. Conclusion: Temperature-controlled air transport of blood transport in the ATR 700 airplane maintained a the blood at a good quality that rendered blood it fit for blood transfusion.
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Yakushiji, Koki, Takanori Yokochi, Hiroshi Fujita und Fumiatsu Yakushiji. „Effects of passenger airplane transport on blood“. Hematology & Transfusion International Journal 8, Nr. 5 (30.10.2020): 108–9. http://dx.doi.org/10.15406/htij.2020.08.00236.
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Objective: We examined the effects of passenger air transport by regular airplanes for air transportation on blood for transfusion. Materials and methods: Irradiated red blood cell (RBC) solutions were transported by regular passenger airplanes which and were static in the cabin during the flight. Blood samples were evaluated visually and biochemically before and after transport. Hemolysis of the transported samples was compared to that of the non-transported ones. The vibration in the airplanes was also measured using a vibration data logger. Results: There was no significant hemolysis of RBCs during airplane transport. The vibration in the airplane was lower than that in automobiles. The temperature in the active transport refrigerator (ATR) room was maintained at 2−6°C. There was no significant hemolysis of RBCs during the two transport routes. Conclusion: Temperature-controlled air transport of blood transport in the ATR 700 airplane maintained a the blood at a good quality that rendered blood it fit for blood transfusion.
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Xiao, Boming. „Analysis on the relation between the vertex angle of a tube airplane and its flying time“. Theoretical and Natural Science 5, Nr. 1 (25.05.2023): 514–18. http://dx.doi.org/10.54254/2753-8818/5/20230310.
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The tube is a type of airplane that is shaped as a hollow cylinder. In common sense, it seems impossible that an airplane has no wings, however, the tube airplane can fly even longer in the sky comparing with normal airplanes. In this paper, the practical experiment related to Bernoullis theorem and Magnus Force will be introduced. In order to understand those equations more deeply with logic, a paper airplane model called the tube is going to be studied. The author makes the models with different shapes and angles so as to figure out the relationship between the angle of the index and the flying time of the airplane. Results show that the angle of the index has an impact on the time of the airplane staying in the sky, and the angle affects the angular and linear rotating speed of the airplane so that the time required for the airplanes varies.
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Kakinuma, Taro, und Masaki Hisada. „A Numerical Study on the Response of a Very Large Floating Airport to Airplane Movement“. Eng 4, Nr. 2 (21.04.2023): 1236–64. http://dx.doi.org/10.3390/eng4020073.
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Numerical simulations were generated to investigate the response of a floating airport to airplane movement using the nonlinear shallow water equations of velocity potential for water waves interacting with a floating thin plate. First, in the 1D calculations, the airplanes were B747 and B737. At touch-and-go, when the airplane speed is closer to the water wave speed, even B737 produced large waves based on the resonance. The impacts due to both the touchdown and leaving of the airplanes generated other forward and backward waves. At landing, when the airplane speed approached the water wave speed, a forced wave was generated and amplified, with many free waves ahead. At takeoff, a wave clump, generated shortly after starting to run, propagated in front of the airplanes. Although the wave height increased from superposition with the reflected waves, the wave reflectance was reduced by lowering the flexural rigidity near the airport edge. Second, in the 2D calculations, B787 performed landing and takeoff. When the still water depth is shallower, a grid-like pattern was formed at the floating airport and appeared more remarkably in landing than in takeoff. The effective amplification occurred from a sufficient load applied when the airplane speed approached the water wave speed. Furthermore, the maximum upslope gradient beneath the airplane increased as the still water depth decreased, and it was larger in takeoff than in landing.
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Sieradzki, Adam, Adam Dziubiński und Cezary Galiński. „Performance Comparison of the Optimized Inverted Joined Wing Airplane Concept and Classical Configuration Airplanes“. Archive of Mechanical Engineering 63, Nr. 3 (01.09.2016): 455–70. http://dx.doi.org/10.1515/meceng-2016-0026.
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Abstract The joined wing concept is an unconventional airplane configuration, known since the mid-twenties of the last century. It has several possible advantages, like reduction of the induced drag and weight due to the closed wing concept. The inverted joined wing variant is its rarely considered version, with the front wing being situated above the aft wing. The following paper presents a performance prediction of the recently optimized configuration of this airplane. Flight characteristics obtained numerically were compared with the performance of two classical configuration airplanes of similar category. Their computational fluid dynamics (CFD) models were created basing on available documentation, photographs and some inverse engineering methods. The analysis included simulations performed for a scale of 3-meter wingspan inverted joined wing demonstrator and also for real-scale manned airplanes. Therefore, the results of CFD calculations allowed us to assess the competitiveness of the presented concept, as compared to the most technologically advanced airplanes designed and manufactured to date. At the end of the paper, the areas where the inverted joined wing is better than conventional airplane were predicted and new research possibilities were described.
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A. B. „Paper Airplanes“. Departures in Critical Qualitative Research 7, Nr. 4 (2018): 146–47. http://dx.doi.org/10.1525/dcqr.2018.7.4.146.
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This short poetic response explores my experience performing the play Heavier than Air as a queer teacher; folding my body into these characters, feeling the tensions in the stories, and their resonances with my own. The form of the poem mirrors the process of folding the paper airplanes referenced and used as props throughout the play. As I performed the poem, I folded a paper airplane, and let it take flight on the last line.
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Wei, Yajun, Xiaotong Chen, Wanrong Luo, Qingsong Zou und Xiaopan Zhang. „Innovative flight control explanation and demonstration: bridging theory and practice in secondary education“. Physics Education 59, Nr. 3 (10.04.2024): 035017. http://dx.doi.org/10.1088/1361-6552/ad3594.
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Abstract How do airplanes turn, pitch, and roll? This fundamental question about airplane control captivates many pupils. Offering a comprehensible explanation to secondary school students is challenging due to the complex nature of fluid dynamics and mechanics. In this paper, we provide an accessible explanation of flight control principles, supported by carefully designed illustrations. Furthermore, we address the gap in educational resources by introducing a novel indoor demonstration apparatus. This design employs universal joints and remote-controlled model airplanes to visually demonstrate the principles of airplane control, particularly focusing on the maneuvers of turning, pitching, and rolling. This method is cost-effective, straightforward to implement, and offers students and aviation enthusiasts a highly intuitive and engaging learning experience.
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Magdy, Ahmed, M. Zakaria, O. Farouk und Ashraf M. Kamal. „Development and verification of AeroMech tool for rapid estimation of airplane aerodynamic characteristics during early design stages“. Journal of Physics: Conference Series 2616, Nr. 1 (01.11.2023): 012009. http://dx.doi.org/10.1088/1742-6596/2616/1/012009.
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Abstract The aerodynamic characteristics of airplanes (i.e., coefficients and derivatives) are essential for the airplane design and optimization process. Generally, accurate calculations of these characteristics are complex and time-consuming. However, the level of accuracy can be adjusted depending on the design phase, problem complexity, and available time for analysis. Thus, diverse tools ranging from simple analytical methods to complex numerical simulations are used to calculate these characteristics during different design steps. This paper presents an efficient tool to expedite the calculation of the aerodynamic characteristics of airplanes with acceptable accuracy based on a combination of analytical and empirical approaches. The goal is to develop a a program tool (AeroMech) that can be used during the airplane preliminary design steps to rapidly assess a large number of alternative configurations and select the best ones for further detailed analysis. For this, enormous empirical relations that are typically represented in charts are digitized and implemented in the developed tool together with the analytical-empirical equations to facilitate and speed up the calculations. Cessna-182 and Cessna-310 airplanes are selected as two case-studies to verify the developed tool against the most common tools such as Digital DATCOM and XFLR5. Finally, the developed tool is partially validated with the available published experimental data for the case-study airplanes. The results show that the tool is able to predict the aerodynamic characteristics with reasonable accuracy for the preliminary design steps, which saves time and resources in the early design stages.
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Kuzmin, Yuri V. „The role of the USA aviation industry in the development of general aviation“. Tambov University Review. Series: Humanities, Nr. 4 (2022): 1108–20. http://dx.doi.org/10.20310/1810-0201-2022-27-4-1108-1120.
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The history of a relatively little-studied sub-sector of aircraft manufacturing is described: the development and production of general purpose airplanes. Data on 2690 aircraft models and their production are collected by the author. It is shown that the USA share in the production in the 20th century exceeds 80 %, although in 1930–1945 European countries were the leaders. Assumptions are made about the reasons for the change of leaders. The definition of “general purpose airplane” is given with references to the regulatory documents of the USA, European Union and Russia. It is shown that the most popular subclass of such airplanes is four-seaters, its share in the total production of aircraft with the number of seats from 3 to 11 exceeds 50 %. For the first time, the year-by-year dynamics of the development and production of general purpose airplanes in the 20th century in the world is published. Strong declines in production are mentioned during the Great Depression and in the first half of the 1980s. It is shown that the demand for general purpose airplanes decreased significantly during the aggravation of the political situation, which correlates with the confidence of potential buyers in their future. Probably, such dependence should be observed for other long-time used consumer goods. The development of new models of general-purpose aircraft was also studied. It is shown that the peak of its intensity falls on 1929, and the post-war decline in the number of developments began even during the period of growth in production – in the mid-1960s. A very strong geographic concentration has been found: almost half of all general purpose airplanes in the world are built in one town (Wichita, Kansas), where more than a dozen airplane manufacturers have located their enterprises.
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Kuzmin, Yury Viktorovich. „Development of designs of four-seat airplanes in the XX century“. Историческая информатика, Nr. 3 (März 2022): 56–80. http://dx.doi.org/10.7256/2585-7797.2022.3.38633.
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The work is devoted to the analysis of a specific sub-branch of airplane construction and, at the same time, to the search of general laws of technology development. For the first time, a global picture of the development of designs of four-seat airplanes in the XX century is given, priority designs are identified. It is shown that the development of four-seat airplanes goes through two stages: the search (until the end of the 1940s), when popular airplane schemes periodically replaced each other, the airplane characteristics varied greatly, and the second stage of mature technology. In the second half of the XX century, both the qualitative and quantitative characteristics of four-seat airplanes remain almost constant and attempts to improve them did not lead to an increase in demand. The change of technology generations was replaced by coexistence, when each type of construction worked out during the previous period found its market niche. The division of phases, the transition from generation’s change to their coexistence, is clearly visible when analyzing both qualitative and quantitative data of airplanes. A paradoxical reaction of aircraft manufacturers to the decline in sales was found, expressed in increased design activity and an attempt to offer products with better technical characteristics. The inefficiency of such a reaction was shown. It is revealed that, contrary to widespread opinion, the change of technological solutions in production is faster than in development. As a result, most of the market is captured not by pioneers and not by retrogrades, but by followers – those who use modern, but already tested technologies in their products. At the same time, attempts to create and offer aircraft to consumers in a methodology that is no longer in demand have persisted unsuccessfully for decades.
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Coutinho, E., und J. Pereira-Monteiro. „‘Bad Trips’: Airplane Headache not Just in Airplanes?“ Cephalalgia 28, Nr. 9 (September 2008): 986–87. http://dx.doi.org/10.1111/j.1468-2982.2008.01632.x.
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A type of headache associated with altitude variations in airplane travellers is increasingly reported and has recently become a subject of debate for experts. We present a patient with headache related to altitude variations in two different settings: airplane and mountain descent, suggesting that different kinds of triggers for pressure variation can cause the same type of pain.
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Baar, Thomas, und Horst Schulte. „Safety Analysis of Longitudinal Motion Controllers during Climb Flight“. Modeling and Analysis of Information Systems 26, Nr. 4 (27.12.2019): 488–501. http://dx.doi.org/10.18255/1818-1015-2019-4-488-501.
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During the climb flight of big passenger airplanes, the airplane’s vertical movement, i.e. its pitch angle, results from the elevator deflection angle chosen by the pilot. If the pitch angle becomes too large, the airplane is in danger of an airflow disruption at the wings, which can cause the airplane to crash. In some airplanes, the pilot is assisted by a software whose task is to prevent airflow disruptions. When the pitch angle becomes greater than a certain threshold, the software overrides the pilot’s decisions with respect to the elevator deflection angle and enforces presumably safe values. While the assistance software can help to prevent human failures, the software itself is also prone to errors and is - generally - a risk to be assessed carefully. For example, if software designers have forgotten that sensors might yield wrong data, the software might cause the pitch angle to become negative. Consequently, the airplane loses height and can - eventually - crash.In this paper, we provide an executable model written in Matlab/Simulink® for the control system of a passenger airplane. Our model takes also into account the software assisting the pilot to prevent airflow disruptions. When simulating the climb flight using our model, it is easy to see that the airplane might lose height in case the data provided by the pitch angle sensor are wrong. For the opposite case of correct sensor data, the simulation suggests that the control system works correctly and is able to prevent airflow disruptions effectively.The simulation, however, is not a guarantee for the control system to be safe. For this reason, we translate the Matlab/Simulink® -model into a hybrid program (HP), i.e. into the input syntax of the theorem prover KeYmaera. This paves the way to formally verify safety properties of control systems modelled in Matlab/Simulink®. As an additional contribution of this paper, we discuss the current limitations of our transformation. For example, it turns out that simple proportional (P) controllers can be easily represented by HP programs, but more advanced PD (proportional-derivative) or PID (proportional-integral-derivative) controllers can be represented as HP programs only in exceptional cases.
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Mieloszyk, Jacek, und Cezary Galinski. „Assessment of the Concept of a Propeller Working in a Slot in the Middle of Wing of a Micro Air Vehicle“. Archive of Mechanical Engineering 60, Nr. 2 (01.06.2013): 269–82. http://dx.doi.org/10.2478/meceng-2013-0017.
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Two configurations of micro-airplanes are compared in this paper. The first, very innovative one, has a propeller working in a slot in the middle of the wing. The second airplane has more classical configuration with a pusher propeller. Advantages and disadvantages of both configurations are evaluated, which makes it possible to assess what are the best possible mission types for each micro-airplane.
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Cohen-Nir, D., und R. Marchi. „Preliminary Analysis of Taxiway Deviation Data and Estimates of Airplane Wingtip Collision Probability“. Transportation Research Record: Journal of the Transportation Research Board 1850, Nr. 1 (Januar 2003): 49–60. http://dx.doi.org/10.3141/1850-06.
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The introduction of new large airplanes (NLAs), initially the Airbus A380, into existing older airports poses a wide range of dimensional clearance issues, primarily related to wingspan and tail height. Many existing airports cannot meet FAA’s Airplane Design Group VI (ADG VI) design standards appropriate to NLA. FAA is conducting ongoing data collection of measured deviations from taxiway centerlines experienced by Boeing-747 airplanes under various weather and visibility conditions, to allow the estimation of the collision risk while taxiing. A preliminary analysis was conducted on the risk of collisions involving airplanes in common taxiing situations, based on FAA data collected at Anchorage International Airport in Alaska from September 2000 to April 2002, and at New York’s John F. Kennedy Airport (JFK) from June 1999 to February 2000. Investigated were 29,544 deviations at Anchorage and 20,702 deviations at JFK. Analyses were performed to assess probabilities of large deviations. The probabilities were finally used to assess the risk of NLA wingtip contact with fixed or movable objects and the joint probability of collision between two airplanes that are taxiing simultaneously. The probability of wingtip collision between two taxiing A380 airplanes is calculated as 1.74 × 10-2 for ADG Code V taxiways, 4.91 × 10-15 for a JFK taxiway separation of 300 ft, and 4.42 × 10-23 for ADG Code VI taxi-ways. The probability of collision between a taxiing B-747-400 and an A380 is 1.5 × 10-11 for ADG Code V taxiways, 4.91 × 10-15 for a JFK taxiway separation of 300 ft, and 2.12 × 10-23 for ADG Code VI taxiways.
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Hernando, JL, und R. Martínez-Val. „Carrier deck launching of adapted land-based airplanes“. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, Nr. 10 (22.11.2019): 1661–74. http://dx.doi.org/10.1177/0954410019890233.
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VTOL Harrier aircraft has been the basic combat airplane for many Navies, but it will soon be retired from service. Three main alternatives appear: to incorporate another, already existing or under development airplane; to design a completely new aircraft; or to modify an existing land-based airplane to achieve carrier suitability. The present paper is part of a study to assess the feasibility of the third option. In former papers, the authors have addressed, firstly, the compatibility criteria of land-based airplanes with aircraft carriers and, secondly, the details of the approach guidance and the recovery manoeuvre, which showed the need of major modifications in wing structure and landing gear. The research proposed here studies the airplane performance during the take-off manoeuvre from mid-size carriers, formed by a flat deck take-off run followed by a ski-jump and the subsequent flyaway.
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Al-Mahadin, Aziz, und Serdar Dalkilic. „DEVELOPED CRITERIA TO IMPROVE PILOT REPORTING OF AIRPLANE VORTEX ENCOUNTERS“. Aviation 23, Nr. 4 (27.02.2020): 133–42. http://dx.doi.org/10.3846/aviation.2019.12038.
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Leading airplane vortices can be hazardous to following airplanes. The regulated minimum separations between following and leading airplanes are sometimes overjudged, hence causing reduction in the capacity of airports. In other instances, they are underjudged and subsequently causing airplane incidences. A vital contribution to the establishment and adjustment of vortex-related minimum airplane separations rely on the identification of vortex encounters through pilot reporting with a manual analysis of flight data from FDRs (flight data recorders). This current process relies on judgment of both the pilot and the airline analysist. Hence, it is subjective and sometimes lacks the required accuracy. Therefore, it is desirable to set a number of criteria, which can be utilized to evaluate the accuracy of wake vortex encounter identification. These criteria can save time, and are both accurate and simple. This study investigates 54 pilot reports of flight events to establish a set of criteria that enable concerned aviation organizations to confirm airplane vortex encounters with higher accuracy. This also helps airlines and aviation stakeholders to introduce new regulations and enhancements such as pilots and FDR analysts training on vortex identification. Such measures will enhance safety, improve aviation operation efficiency and allow revision of vortex-separation regulations.
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Altamirano, Isabel. „TRAIL Spotlight“. DttP: Documents to the People 47, Nr. 3 (12.09.2019): 5. http://dx.doi.org/10.5860/dttp.v47i3.7120.
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The first thing that you feel when an airplane lands is the effect of the brakes to slow it down. But, as the report “The Use of Wheel Brakes on Airplanes” points out, the use of brakes had to be proven to be safe before becoming part of standard operating procedures.
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Song, Jae-Hoon, und Han-Lim Choi. „Efficient airplane arrival scheduling using a set partitioning-based branch-and-price method“. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, Nr. 16 (19.07.2017): 2939–51. http://dx.doi.org/10.1177/0954410017718566.
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This article presents an exact algorithm that is combined with a heuristic method to find the optimal solution for an airplane landing problem. For a given set of airplanes and runways, the objective is to minimize the accumulated deviations from the target landing time of the airplanes. A cost associated with landing either earlier or later than the target landing time is incurred for each airplane within its predetermined time window. In order to manage this type of large-scale optimization problem, a set partitioning formulation that results in a mixed integer linear program is proposed. One key contribution of this article is the development of a branch-and-price methodology, in which the column generation method is integrated with the branch-and-bound method in order to find the optimal integer solution. In addition to the exact algorithm, a simple heuristic method is also presented to tighten the solution space. Numerical experiments are undertaken for the proposed algorithm in order to confirm its effectiveness using public data from the OR-Library. As an application in the real-world situation of airplane landing, air traffic data from Incheon International Airport is employed to assure the efficiency of the proposed algorithm.
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DeCelles, Katherine A., und Michael I. Norton. „Physical and situational inequality on airplanes predicts air rage“. Proceedings of the National Academy of Sciences 113, Nr. 20 (02.05.2016): 5588–91. http://dx.doi.org/10.1073/pnas.1521727113.
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We posit that the modern airplane is a social microcosm of class-based society, and that the increasing incidence of “air rage” can be understood through the lens of inequality. Research on inequality typically examines the effects of relatively fixed, macrostructural forms of inequality, such as socioeconomic status; we examine how temporary exposure to both physical and situational inequality, induced by the design of environments, can foster antisocial behavior. We use a complete set of all onboard air rage incidents over several years from a large, international airline to test our predictions. Physical inequality on airplanes—that is, the presence of a first class cabin—is associated with more frequent air rage incidents in economy class. Situational inequality—boarding from the front (requiring walking through the first class cabin) versus the middle of the plane—also significantly increases the odds of air rage in both economy and first class. We show that physical design that highlights inequality can trigger antisocial behavior on airplanes. More broadly, these results point to the importance of considering the design of environments—from airplanes to office layouts to stadium seating—in understanding both the form and emergence of antisocial behavior.
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Li, Songlin, Junwen Shao und Yuze Sun. „Study on vortex generator on automobile and airplane“. Theoretical and Natural Science 26, Nr. 1 (20.12.2023): 139–44. http://dx.doi.org/10.54254/2753-8818/26/20241049.
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A vortex generator is a compact device that can be installed on automobiles and airplanes to enhance aerodynamic efficiency. The use of vortex generators on automobiles and airplanes is briefly described in this study. It begins by outlining the working theories and categorizations of vortex generators, which reactivate the boundary layer to postpone airflow separation. Second, this study examines the use of vortex generators on automobiles and trucks, positioned at the back of these vehicles to reduce air drag and improve fuel efficiency. Studies show that vortex generators can increase vehicle fuel economy by 10% to 20%. This study examines how vortex generators improve airplane efficiency and lift by controlling the airflow above the wings. In general, if a vortex generators design is appropriate for automobiles and airplanes, it can improve aerodynamic performance. This article lists several sources regarding the use of vortex generators and their benefits. In short, the future development of vortex generators will tend to be intelligent, material optimization, and environmental protection, aiming to provide more efficient, reliable, and intelligent fluid control solutions, and bring greater economic and social benefits to various industrial applications.
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Olejnik, Aleksander, Łukasz Kiszkowiak und Adam Dziubiński. „Aerodynamic analysis of General Aviation airplanes using computational fluid dynamics methods“. Mechanik 90, Nr. 8-9 (11.09.2017): 802–4. http://dx.doi.org/10.17814/mechanik.2017.8-9.118.
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The problems of an aircraft aerodynamic analysis based on the example of Very Light Aeroplanes and Very Light Jet category airplanes have been presented. A numerical calculations using finite volume method implemented in specialized software were performed. A method of preparing a numerical model of an airplane and the aerodynamic analysis methodology have been presented. An influence of an airplane propulsion on aerodynamic characteristics have been analyzed. A results have been shown in the graphs form of aerodynamic force and moment components as function of angle of attack.
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Fu, Muyi. „Research on the aerodynamic causes of airplane wings“. Theoretical and Natural Science 36, Nr. 1 (28.05.2024): 77–84. http://dx.doi.org/10.54254/2753-8818/36/20240519.
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As the fastest means of transportation in the globe for people, airplanes are receiving more and more attention in the fields of science and engineering. Experts around the world try to figure out methods of increasing safety for airplanes, while it may elicit an ongoing debate on how to explain wing aerodynamics. This essay delves into the intricate world of wing aerodynamics, first presenting an analysis of forces acting on the airplane which could help provide basic knowledge and serve as background information. Three main theories, Bernoullis equation, Newtons third law, and the Coanda effect are analyzed and compared here to get a relatively accurate explanation. By figuring out how wings work to make a plane uplift in the air, the results help improve the design of traditional airliners and increase their stability.
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Hasibuzzaman, MD, und Md Kamrul Hasan. „ANALYSIS OF FLIGHT CHARACTERISTICS OF PAPER AIRPLANES“. International Journal of Engineering Applied Sciences and Technology 7, Nr. 9 (01.01.2023): 161–66. http://dx.doi.org/10.33564/ijeast.2023.v07i09.024.
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The trajectory of a paper airplane is dependent on its lift and drag performance and aerodynamic stability. Historically, darts were the perfect choice for distance competitions because of their excellent stability, but John Collins has changed this tradition with his incredible design, Susanne, by making a new distance record in 2012. In this paper, differences between this world record design and other typical paper airplanes are represented using typical models of a dart and glider since the wingspan of Susanne fits in between them. Solid models of these three airplanes are created with Solid Works and analyzed with ANSYS Fluent at different attack and sideslip angles. Finally, a comparison is made considering lift, drag, and aerodynamic stability. From the simulated results, it is observed that Susanne performed moderately in terms of lift and drag performance and yaw stability; however, it possesses the maximum amount of roll stability
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Elova, Dilnoza, und Olimjon Ahmadov. „Bukhara from the history of the events of the organization of the air fleet of modern new technology and the introduction of aircraft“. E3S Web of Conferences 515 (2024): 04007. http://dx.doi.org/10.1051/e3sconf/202451504007.
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In 1920-1924, the activities carried out in Bukhara regarding the establishment of the air fleet and the establishment of airplane traffic were covered through the analysis of primary sources and literature. The discovery of airplanes as a means of transport and the beginning of their use is related to the history of countries in Europe such as France and Germany. In 1924, a total of 1,000 passengers, 200 kg of mail, and 5 tons of cargo were transported by air in our country. The history of the establishment of the air fleet and the arrival of the first airplanes in Turkestan dates back to the first decade of the 20th century. On March 28-29, 1912, the pilot Sedov flew over Tashkent in his plane, and on March 29, 4 women and 3 men flew over Tashkent. The guests who visited Tashkent also flew in an airplane and watched the city view from above. The article serves to improve state programs aimed at creating a new generation of history textbooks and training manuals, writing fundamental works, organizing special courses, and implementing socio-economic and cultural innovations.
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Wang, Jinfeng, und Edwin E. Herricks. „Risk Assessment of Bird–Aircraft Strikes at Commercial Airports“. Transportation Research Record: Journal of the Transportation Research Board 2266, Nr. 1 (Januar 2012): 78–84. http://dx.doi.org/10.3141/2266-09.
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Bird strikes are a continuing problem in aviation. Despite the number and severity of reported bird strikes, quantification of the effect of contributory factors has been limited because of the absence of data, especially data on bird activity around airfields. The purpose of this study is to provide initial insight into this important problem by combining a number of databases and information resources available at the Seattle–Tacoma International Airport in Washington, including airplane operations, bird strike reports, and the avian radar data on bird movements. Logistic regression and multinomial regression models were used to analyze, respectively, bird strike occurrence and severity. The results indicate that bird track density and airplane movement frequency significantly correlate with bird strike occurrence. High altitude and cloudy weather increase the probability of serious damage. Airplanes weighing less than 27,000 kg and those with turbofan engines and struck positions including tail and light move the propensity toward minor damage compared with no damage. Factors such as single-engine airplanes, medium and large birds, and strikes occurring at engines and wings increase the chance of both serious and minor damage. The findings of this study could provide support for potential changes in airport bird hazard management, airplane operations, and engineering designs of engines and airframes. The study highlights the importance of managing accurate bird strike reports and applying new statistical approaches as more data become available.
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Sousa, Marcelo Santiago, Pedro Paglione, Roberto Gil Annes Silva, Flavio Luiz Cardoso-Ribeiro und Sebastião Simões Cunha. „Mathematical model of one flexible transport category aircraft“. Aircraft Engineering and Aerospace Technology 89, Nr. 3 (02.05.2017): 384–96. http://dx.doi.org/10.1108/aeat-12-2013-0230.
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Purpose The purpose of this paper is to present a mathematical model of one very flexible transport category airplane whose structural dynamics was modeled with the strain-based formulation. This model can be used for the analysis of couplings between the flight dynamics and structural dynamics. Design/methodology/approach The model was developed with the use of Hamiltonian mechanics and strain-based formulation. Nonlinear flight dynamics, nonlinear structural dynamics and inertial couplings are considered. Findings The mathematical model allows the analysis of effects of high structural deformations on airplane flight dynamics. Research limitations/implications The mathematical model has more than 60 degrees of freedom. The computational burden is too high, if compared to the traditional rigid body flight dynamics simulations. Practical implications The mathematical model presented in this work allows a detailed analysis of the couplings between flight dynamics and structural dynamics in very flexible airplanes. The better comprehension of these couplings will contribute to the development of flexible airplanes. Originality/value This work presents the application of nonlinear flight dynamics-nonlinear structural dynamics-strain-based formulation (NFNS_s) methodology to model the flight dynamics of one very flexible transport category airplane. This paper addresses also the way as the analysis of results obtained in nonlinear simulations can be made. Comparisons of the NFNS_s and nonlinear flight dynamics-linear structural dynamics methodologies are presented in this work.
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Kraus, Jakub, und Ladislav Capoušek. „Transformation of Helicopter PinS Procedures for Airplanes“. MAD - Magazine of Aviation Development 1, Nr. 5 (15.09.2013): 3. http://dx.doi.org/10.14311/mad.2013.05.01.
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<span style="line-height: 115%; font-family: 'Times New Roman','serif'; font-size: 9pt; mso-bidi-font-size: 10.0pt; mso-fareast-font-family: Calibri; mso-ansi-language: EN-GB; mso-fareast-language: EN-US; mso-bidi-language: AR-SA;" lang="EN-GB">This article deals with the possibility to use existing helicopter Point in Space procedures with minor changes for airplanes. The basis is to find parts of PinS procedures that need to be changed, suggest these changes, and then determine whether the revised procedures could be usable and could bring the benefits for airplane operations</span>.
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Bautista-Medina, José Antonio, Rogelio Lozano und Antonio Osorio-Cordero. „Position Periodic Control of Two Rotating Airplanes“. Drones 6, Nr. 8 (19.08.2022): 214. http://dx.doi.org/10.3390/drones6080214.
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The increasing development in aerial vehicles shows a wide range of configurations for different requirements. Many of them combine conventional configurations’ features to take advantage of their qualities, such as performing a cruise flight as an airplane and hovering like a helicopter. Thereby, this study analyzes the modeling and control of a pair of fixed-wing airplanes joined together to form a larger rotor that incorporates valuable features in missions with aerial vehicles. The model uses the Lagrange approach to obtain the motion equations in the flight plane, and two control strategies are proposed to regulate the movement in the horizontal plane: a cyclic proportional derivative control and a positive function. Both controls generate a sinusoidal signal to regulate the thrust of the motors, and this leads to the generation of pulses that direct and move the vehicle toward a desired position until it is reached. Our analysis is validated by simulation that shows how both controls govern the center of mass position of the rotating planes, and it also shows the airplanes’ trajectory. The results show good performance.
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Li, Li. „Information Estimation of Civil Airplane in Interference Localization Background“. Applied Mechanics and Materials 513-517 (Februar 2014): 3389–92. http://dx.doi.org/10.4028/www.scientific.net/amm.513-517.3389.
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The ground-air communication of civil aviation is interfered by radios, which has seriously endangered the normal flight of civil airplanes. This paper proposes an airplane information estimation algorithm based on the study of the problem of interference localization. Firstly, a novel signal model to accurately estimate parameters of the airplane is proposed. A method of Doppler estimation based on peak searching is proposed, and the 2D-MUSIC algorithm is applied to estimate the azimuth angle and elevation angle. Furthermore, the velocity and location of the airplane are estimated by employing array geometry. As a result, the airplane localization is achieved in bistatic radar, laying the foundations for interference localization. The correctness and effectiveness of the proposed method are verified with the computer simulation.
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Budde, Don, Jochen Hinkelbein und Douglas D. Boyd. „Analysis of Air Taxi Accidents (20042018) and Associated Human Factors by Aircraft Performance Class“. Aerospace Medicine and Human Performance 92, Nr. 5 (01.05.2021): 294–302. http://dx.doi.org/10.3357/amhp.5799.2021.
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INTRODUCTION: Air taxis conduct nonscheduled transport and employ aircraft in various performance categories hereafter referred to as low, medium, and high performance, respectively. No study has yet addressed fixed-wing air taxi safety by performance category. Herein, we compared accident rates/occupant injury across air taxi airplane fleets grouped by performance category and identified human factors contributing to fatal accidents for airplanes in that category with the highest mishap rate.METHODS: Accidents (20042018) in the United States were identified from the National Transportation Safety Board database. General Aviation/Part 135 Activity Surveys provided annual fleet times. Fatal accident contributing factors were per the Human Factors Classification System (HFACS). Statistics utilized Poisson distributions, Chi-Square/Fisher, and Mann-Whitney tests.RESULTS: There were 269 air taxi mishaps (53 fatal) identified. Over the 15 yr, the accident rate (1.10/million flight hours-all categories) declined 50%, largely due to a reduction in medium/high performance category airplane crashes. However, little temporal change was observed for low performance airplanes (1.5/million flight hours) and injury severity trended higher. At the aircrew/physical environment levels, HFACS revealed decision (improper choices), skill-based (stick and rudder) and perceptual (night, instrument conditions) errors contributing to > 60% of fatal accidents involving low performance airplanes. At the organizational level, failing to correct problems, time pressures, and incentive systems contributed to 16% of fatal mishaps.CONCLUSION: Safety deficits remain for the low performance category air taxi fleet warranting increased pilot instrument flight training/utilization of the mandatory 3-axis autopilot in degraded visibility. Safety culture improvements to address issues of personnel/equipment/training deficiencies, failing to correct problems, and time pressures/a safety-compromising incentive system all need to be addressed.Budde D, Hinkelbein J, Boyd DD. Analysis of air taxi accidents (20042018) and associated human factors by aircraft performance class. Aerosp Med Hum Perform. 2021; 92(5):294302.
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Hamid, Ali. „Unsteady nonlinear panel method with mixed boundary conditions“. FME Transactions 49, Nr. 1 (2021): 135–46. http://dx.doi.org/10.5937/fme2101135a.
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A new panel method had been developed to account for unsteady nonlinear subsonic flow. Two boundary conditions were used to solve the potential flow about complex configurations of airplanes. Dirichlet boundary condition and Neumann formulation are frequently applied to the configurations that have thick and thin surfaces respectively. Mixed boundary conditions were used in the present work to simulate the connection between thick fuselage and thin wing surfaces. The matrix of linear equations was solved every time step in a marching technique with Kelvin's theorem for the unsteady wake modeling. To make the method closer to the experimental data, a Nonlinear stripe theory which is based on a two-dimensional viscous-inviscid interaction method for each station along the wing spanwise direction and Prandtle-Glauert rule for compressibility effect were used to enhance the potential results of the method. The fast turnaround time and the ability to model arbitrary geometries is the goal of the present work. Different airplanes configurations were simulated (DLR-F4, light jet, cargo and four engine commercial airplanes). The results of pressure and forces coefficients were compared with the DLR-F4 airplane. The comparisons showed a satisfying agreement with the experimental data. The method is simple and fast as compared with other singularity methods, which may be dependent as a preliminary method to design aircrafts.
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Fakhreddine, Omar, Yousef Gharbia, Javad Farrokhi Derakhshandeh und A. M. Amer. „Challenges and Solutions of Hydrogen Fuel Cells in Transportation Systems: A Review and Prospects“. World Electric Vehicle Journal 14, Nr. 6 (13.06.2023): 156. http://dx.doi.org/10.3390/wevj14060156.
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Conventional transportation systems are facing many challenges related to reducing fuel consumption, noise, and pollutants to satisfy rising environmental and economic criteria. These requirements have prompted many researchers and manufacturers in the transportation sector to look for cleaner, more efficient, and more sustainable alternatives. Powertrains based on fuel cell systems could partially or completely replace their conventional counterparts used in all modes of transport, starting from small ones, such as scooters, to large mechanisms such as commercial airplanes. Since hydrogen fuel cells (HFCs) emit only water and heat as byproducts and have higher energy conversion efficiency in comparison with other conventional systems, it has become tempting for many scholars to explore their potential for resolving the environmental and economic concerns associated with the transportation sector. This paper thoroughly reviews the principles and applications of fuel cell systems for the main transportation schemes, including scooters, bicycles, motorcycles, cars, buses, trains, and aerial vehicles. The review showed that fuel cells would soon become the powertrain of choice for most modes of transportation. For commercial long-rage airplanes, however, employing fuel cells will be limited due to the replacement of the axillary power unit (APU) in the foreseeable future. Using fuel cells to propel such large airplanes would necessitate redesigning the airplane structure to accommodate the required hydrogen tanks, which could take a bit more time.
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Kabakchiev, Hristo, Vera Behar, Ivan Garvanov, Dorina Kabakchieva, Avgust Kabakchiev und Hermann Rohling. „FSR Systems for Detection of Air Objects Using Cosmic Radio Emissions“. Sensors 21, Nr. 2 (11.01.2021): 465. http://dx.doi.org/10.3390/s21020465.
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The paper analyses the possibility of Forward Scatter Radar (FSR) systems to detect airplanes using cosmic emission from pulsars and planets (pulsar, Sun, Moon). A suboptimal multichannel algorithm for joint detection and evaluation of the parameters of the forward scattering signal created by an airplane (duration and velocity) is proposed, with preliminary compensation of the powerful direct signal emitted by cosmic sources (pulsar, Sun and Moon). The expressions for calculation of the Signal-to-Noise Ratio (SNR) at the input of the detector and the compensator are obtained. The detection characteristics are also obtained, and the requirements for the suppression coefficient of the compensator are evaluated. A methodology for calculating the maximum distance for detecting an aircraft using a described algorithm is proposed. The obtained results show that due to the Forward Scatter (FS) effect, there is the theoretical possibility to detect airplanes at close ranges by FSRs, which use very weak signals from cosmic sources.
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Kabakchiev, Hristo, Vera Behar, Ivan Garvanov, Dorina Kabakchieva, Avgust Kabakchiev und Hermann Rohling. „FSR Systems for Detection of Air Objects Using Cosmic Radio Emissions“. Sensors 21, Nr. 2 (11.01.2021): 465. http://dx.doi.org/10.3390/s21020465.
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The paper analyses the possibility of Forward Scatter Radar (FSR) systems to detect airplanes using cosmic emission from pulsars and planets (pulsar, Sun, Moon). A suboptimal multichannel algorithm for joint detection and evaluation of the parameters of the forward scattering signal created by an airplane (duration and velocity) is proposed, with preliminary compensation of the powerful direct signal emitted by cosmic sources (pulsar, Sun and Moon). The expressions for calculation of the Signal-to-Noise Ratio (SNR) at the input of the detector and the compensator are obtained. The detection characteristics are also obtained, and the requirements for the suppression coefficient of the compensator are evaluated. A methodology for calculating the maximum distance for detecting an aircraft using a described algorithm is proposed. The obtained results show that due to the Forward Scatter (FS) effect, there is the theoretical possibility to detect airplanes at close ranges by FSRs, which use very weak signals from cosmic sources.
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Rostami, M., und SA Bagherzadeh. „Development and validation of an enhanced semi-empirical method for estimation of aerodynamic characteristics of light, propeller-driven airplanes“. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, Nr. 4 (26.12.2016): 638–48. http://dx.doi.org/10.1177/0954410016683415.
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This study is intended to introduce an enhanced semi-empirical method for estimation of longitudinal and lateral-directional stability and control derivatives in the preliminary design phase of light airplanes. Specialised for light, single or twin propeller-driven airplanes, available state-of-the-art analytical procedures and design data compendia are combined and modified in a unique compatible method, and automated in NAMAYEH software. In the present study, modified procedures and the software structure are presented. Afterwards, the proposed method is applied to a four-place, low wing, single-engine, propeller-driven general aviation airplane. In order to validate the proposed method, the estimated aerodynamic characteristics are compared with the wind tunnel test data as well as DATCOM and VLM-based method estimations. The results indicate that the proposed method is able to predict the aerodynamic characteristics in an acceptable range of accuracy from zero-lift to stall conditions in all configurations.
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Lin, L., Y. X. Ren, M. Y. Huang, X. D. Zhi und D. Z. Wang. „Failure Modes of a Reticulated Dome in a Small Airplane Crash“. Advances in Civil Engineering 2019 (08.08.2019): 1–10. http://dx.doi.org/10.1155/2019/5025637.
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Since the 9/11 incident, many engineering research works have been conducted on the impact resistance of large-span space structures. In the present study, a small airplane, Bombardier Challenger 850, was chosen as the test subject. An airplane crash on a single-layered Kiewitt-8 reticulated dome with span 60 m considering roof sheathing effect was simulated using ANSYS/LS-DYNA software. The principles of establishing the numerical model of small airplanes were determined. In addition, the impact styles of small airplane and impact positions on the dome were investigated. The failure modes of reticulated dome with roof sheathing due to small airplane crash were identified. Furthermore, the failure modes between reticulated domes with and without roof sheathing were compared and the effect of roof sheathing on the failure modes of reticulated dome under a small airplane crash was investigated.
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Lü, Zhi, Zhan Gao und Yi Lü. „A Flight Simulator that Grouping Aircrafts Simultaneously Take off and Land in Open Grid Computing Environment“. Applied Mechanics and Materials 182-183 (Juni 2012): 1292–97. http://dx.doi.org/10.4028/www.scientific.net/amm.182-183.1292.
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The performance of airplane in commercial airline environment is determined by, and therefore an indicator of performance measure of, the thermodynamic properties of airplane. The aim of this study was to establish the use of simulators to determine aircraft accident for a flight of airplanes and evaluate the potential of new airspace structure and airport’s runway. This indicates that there is a possibility of obtaining airplane performance from analysis and verification simulating airplane. As compared with AIRBUS Full Flight Simulator, a multiple aircrafts flight simulator that grouping aircrafts simultaneously take off and land was presented, which is basis on a parallel distributed computing in Open Grid Computing Environment (OGCE), and service oriented architecture (SOA) of software in multiple aircraft simulator, the performance of collaborative flight of multiple aircrafts is evaluated.
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Du, Cuicui, Deren Kong und Chundong Xu. „Development of a Fault Detection Instrument for Fiber Bragg Grating Sensing System on Airplane“. Micromachines 13, Nr. 6 (31.05.2022): 882. http://dx.doi.org/10.3390/mi13060882.
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This study develops a fault detection device for the fiber Bragg grating (FBG) sensing system and a fault detection method to realize the rapid detection of the FBG sensing system on airplanes. According to the distribution of FBG sensors on airplanes, the FBG sensing system is built based on wavelength division multiplexing (WDM) and space division multiplexing (SDM) technologies. Furthermore, the hardware and software of the fault detection device and the relevant FBG demodulator are studied in detail. Additionally, in view of the similar features of the healthy FBG sensor in the same measuring point, a rapid fault diagnosis method based on a synthetical anomaly index is proposed. The features (light intensity I, signal length L, standard deviation of original sample σ and energy value in time-domain P) of FBG sensors are extracted. The aggregation center value of the above feature values is obtained through the loop iteration method. Furthermore, the separation degrees of features are calculated and then form the synthetical anomaly index so as to make an effective diagnosis of the state of the FBG sensor. Finally, the designed fault detection instrument and proposed fault detection method are used to monitor the 25 FBG sensors on the airplane, the results indicated that three faulty and two abnormal FBG sensors on the airplane are identified, showing the effectiveness of the proposed fault detection method.
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bin Abu Bakar, Mohd Ridh, Bambang Basuno und Sulaiman Hasan. „Aerodynamics Analysis on Unsymmetrical Fuselage Models“. Applied Mechanics and Materials 315 (April 2013): 273–77. http://dx.doi.org/10.4028/www.scientific.net/amm.315.273.
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The large commercial passengers airplanes are mostly designed to have symmetrical body with respect to the longitudinal axis. However for small passengers airplanes or for the airplane designed as UAV plat form is normally having an unsymmetrical fuselage. The aerodynamics characteristics fuselage may give a strong influence to the overall aerodynamics characteristics of the airplane. The present work investigates the aerodynamics characteristics of the unsymmetrical fuselage with respect to the longitudinal axis. The fuselage assumed to have circular cross section and the coordinate of the fuselage are created by using the same equation which had been used in defining the coordinate of cambered airfoil NACA series four digits. The fuselage had been set to have the same maximum thickness 15 % of the fuselage length and different fuselage models are obtained through varying the position as well as the value of the maximum camber line. The semi empirical aerodynamic method for estimating the fuselage lift coefficient CL, drag coefficient CDand the fuselage pitching moment coefficient CMsuch as given by DATCOM are well established. However when it came to the unsymmetrical fuselage, this approach can not be adopted easily. The required of angle attack at zero lift of the corresponding unsymmetrical fuselage is difficult to define. The result for particular cambered fuselage indicates that the aerodynamics characteristics strongly influenced by how the fuselages camber lines look likes.
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Askue, Vaughan. „Airfoils for airplanes“. Air Medical Journal 23, Nr. 1 (Januar 2004): 10–11. http://dx.doi.org/10.1016/j.amj.2003.11.001.
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Houchin, Ron. „Painting Paper Airplanes“. Appalachian Heritage 46, Nr. 4 (2018): 109–10. http://dx.doi.org/10.1353/aph.2018.0072.
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Liu, J., J. Zhang und F. Zhao. „Feature for Distinguishing Propeller-Driven Airplanes from Turbine-Driven Airplanes“. IEEE Transactions on Aerospace and Electronic Systems 46, Nr. 1 (Januar 2010): 222–29. http://dx.doi.org/10.1109/taes.2010.5417158.
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Zhuravlev, P. V., und V. N. Zhuravlev. „Models of early stages of design of trunk-route passenger airplanes with taking families into account“. Civil Aviation High Technologies 25, Nr. 5 (02.11.2022): 59–69. http://dx.doi.org/10.26467/2079-0619-2022-25-5-59-69.
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There is a tight connection between the Pre-Design (development of requirements for the designed airplane) and Conceptual Design stages while creating a new aircraft. Taking this connection into account would result in the design of more optimal aircraft that would have the appropriate advantage during operation. Previously when the ability to take such interconnections into the account was lacking the designers were forced to allocate certain reserves in the project based on previous design experience. The advancement of design, modeling and manufacturing methods allowed transitioning from allocating these reserves as means for possible error compensation to their planning or management. In particular, such planned reserves should be allocated in wing and landing gear at the Conceptual Design stage for the creation of passenger airplane families. The values of these reserves should be substantiated based on the evaluation of future functioning of the whole created airplane family within the airline fleet. This requires solving a problem of Pre-Design and requirements creation. Thus, the reserves become new design variables. The values of these new variables should be optimized together with the values of the existing “traditional” variables during airplane design. A model, which takes management of the aforementioned reserves into the account during airplane design, was constructed. The presented model is intended for usage within the framework of the models, which solve the problem of creation of a passenger airplane fleet at Pre-Design stage with taking the presence of an airplane family within this fleet into the account as well as optimization of this passenger airplane family. The model calculation results were verified for the trunk-route passenger airplanes of all main types with taking the existence of the appropriate families into the account. During verification the wing of each considered passenger airplane was sized for the appropriate family version with the maximum take-off weight. After that this wing was “fixed” and processed as initial data for the family version, statistics on which was used for checking the model calculation results. The verification demonstrated good correlation between the model calculation results and the available statistics. It also showed that the presented model can be used for the design of individual trunk-route passenger airplanes and families of all main types (short-, medium- and long-range).
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Radmanesh, Hamid, Seyed Saeid Heidari Yazdi, G. B. Gharehpetian und S. H. Fathi. „Modelling and Simulation of Fuel Cell Dynamics for Electrical Energy Usage of Hercules Airplanes“. Scientific World Journal 2014 (2014): 1–10. http://dx.doi.org/10.1155/2014/593121.
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Dynamics of proton exchange membrane fuel cells (PEMFC) with hydrogen storage system for generating part of Hercules airplanes electrical energy is presented. Feasibility of using fuel cell (FC) for this airplane is evaluated by means of simulations. Temperature change and dual layer capacity effect are considered in all simulations. Using a three-level 3-phase inverter, FC’s output voltage is connected to the essential bus of the airplane. Moreover, it is possible to connect FC’s output voltage to airplane DC bus alternatively. PID controller is presented to control flow of hydrogen and oxygen to FC and improve transient and steady state responses of the output voltage to load disturbances. FC’s output voltage is regulated via an ultracapacitor. Simulations are carried out via MATLAB/SIMULINK and results show that the load tracking and output voltage regulation are acceptable. The proposed system utilizes an electrolyser to generate hydrogen and a tank for storage. Therefore, there is no need for batteries. Moreover, the generated oxygen could be used in other applications in airplane.
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Lindblom, Gordon P. „MEASUREMENT AND PREDICTION OF DEPOSITIONAL ACCURACY IN DISPERSANT SPRAYING FROM LARGE AIRPLANES“. International Oil Spill Conference Proceedings 1987, Nr. 1 (01.04.1987): 325–28. http://dx.doi.org/10.7901/2169-3358-1987-1-325.
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ABSTRACT Aerial application of dispersants has progressed to include very large airplanes, such as the Hercules C-130, for which a portable spray unit has been developed. This unit, which can be rapidly placed in the cargo aircraft (without any mechanical alterations) was flight tested with spraying of a dispersant concentrate in 1982. The tests measured actual deposition of chemical under various conditions. The most definitive data were collected using a “deposition track,” positioned on the ground across the flight path of the airplane. The dyed dispersant was recovered from this track and the data converted to amount per unit area, and to percent of total pumped fluid on-target. The results led to correlation of depositional accuracy in terms of the air shear experienced by the sprayed fluid. The data has been further used to develop a mathematical prediction for design of dispersant treatment procedures using high-speed airplanes. Use of these considerations in operational planning can improve dispersant dosage control by preventing both under-treatment and wasteful off-target drift.
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Wei, Kaixiang. „Turbofan and turbojet engines: Working process and future development“. Theoretical and Natural Science 12, Nr. 1 (17.11.2023): 114–19. http://dx.doi.org/10.54254/2753-8818/12/20230447.
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This article is based on the fundamental thermodynamics theory to analyze the difference between the turbojet and turbofan engines. The result of this article is that the turbofan engine is suitable for commercial use since it consumes less fuel and has a higher bypass ratio than the turbojet engine. But low bypass ratio engines can serve the military since they have a smaller volume and higher speed, suitable for air combat. The turbojet engine can travel at a supersonic speed since it has extremely high jet flow from the nozzle and much higher fuel consumption, so it is for military use. This article also analyses two cases: i) How the number of fan blades and outlet guide vans affects the noise of the engine produced. ii) When airplanes fly through volcanic ash, how does the ash damage the airplane and the engine? The engineer found that 55 outlet guide vans are better than 37. To prevent airplanes from flying through volcanic ash, satellite weather photos start to show the volcanic ash area.