Готові списки джерел за темами / Aircraft wake

Добірка наукової літератури з теми "Aircraft wake"

Автор: Grafiati

Опубліковано: 7 липня 2024

Оновлено: 7 липня 2024

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Статті в журналах з теми "Aircraft wake":

Pan, Weijun, Yuanfei Leng, Haoran Yin, and Xiaolei Zhang. "Identification of Aircraft Wake Vortex Based on VGGNet." Wireless Communications and Mobile Computing 2022 (June 18, 2022): 1–10. http://dx.doi.org/10.1155/2022/1487854.

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The exploration of information for aircraft wake vortex enables us to obtain new knowledge of wake turbulence separation standards. Traditional manual methods cannot work satisfactorily for the identification of great number of wake vortex data with high accuracy. Fortunately, the LiDAR intensity data can be explained by integrating LiDAR products with the strategies of computer vision. To overcome the limitation of traditional manual methods, this paper is aimed at developing an automatic method to identify a given set of wake vortices from various aircrafts. The main innovation works are outlined as follows. (1) From the wake vortex data that consists of various aircrafts measured by Wind3D 6000 LiDAR, a grayscale dataset of wake flow is constructed to boost the deep learning model for identifying aircraft wake vortex. (2) Following this, we propose a new method for the identification of aircraft wake vortex by modifying the VGG16 network, providing binary classifications of uncertain behavior patterns for wake vortices. To evaluate the proposed identification model, performance evaluation was conducted on our dataset, where experimental results revealed the values of 0.984, 0.951, 0.959, and 0.955 in terms of accuracy, precision, recall, and F1-score, respectively.

Pan, Weijun, Zhengyuan Wu, and Xiaolei Zhang. "Identification of Aircraft Wake Vortex Based on SVM." Mathematical Problems in Engineering 2020 (May 12, 2020): 1–8. http://dx.doi.org/10.1155/2020/9314164.

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The aircraft wake vortex has important influence on the operation of the airspace utilization ratio. Particularly, the identification of aircraft wake vortex using the pulsed Doppler lidar characteristics provides a new knowledge of wake turbulence separation standards. This paper develops an efficient pattern recognition-based method for identifying the aircraft wake vortex measured with the pulsed Doppler lidar. The proposed method is outlined in two stages. (i) First, a classification model based on support vector machine (SVM) is introduced to extract the radial velocity features in the wind fields by combining the environmental parameters. (ii) Then, grid search and cross-validation based on soft margin SVM with kernel tricks are employed to identify the aircraft wake vortex, using the test dataset. The dataset includes wake vortices of various aircrafts collected at the Chengdu Shuangliu International Airport from Aug 16, 2018, to Oct 10, 2018. The experimental results on dataset show that the proposed method can identify the aircraft wake vortex with only a small loss, which ensures the satisfactory robustness in detection performance.

Filippov, R. N., and E. A. Titova. "Effect of the Wake Vortex on the Mutual Safety of Winged Aircraft Following the Same Route." Proceedings of Higher Educational Institutions. Маchine Building, no. 10 (739) (October 2021): 65–73. http://dx.doi.org/10.18698/0536-1044-2021-10-65-73.

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The wake vortex consists mainly of two vortices, which are formed when the stream flows around the wings of an aircraft. A semi-empirical model of a stable vortex wake is proposed and analyzed. The model allows describing the velocity field in a vortex, depending on the characteristics of the aircraft generator, as well as assessing the effect of the vortex on the subsequent aircraft. Statistical modeling was carried out to determine the safe interval between the aircrafts for the characteristic sections of the trajectory. When moving over the sea, a straight-line route, a trajectory with turns and an ascent to an altitude for flying around the island were chosen; on the land section of the movement, a flight over the relief was simulated. A significant influence of the ruggedness of the relief on the probability of an aircraft falling when it enters a wake vortex is shown. The effect of the displacement of the aircraft trajectories in the vertical and horizontal planes and the increase in the average flight speed on the safe interval between the aircrafts is investigated.

Tomaszewski, Jessica M., Julie K. Lundquist, Matthew J. Churchfield, and Patrick J. Moriarty. "Do wind turbines pose roll hazards to light aircraft?" Wind Energy Science 3, no. 2 (November 2, 2018): 833–43. http://dx.doi.org/10.5194/wes-3-833-2018.

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Abstract. Wind energy accounted for 5.6 % of all electricity generation in the United States in 2016. Much of this development has occurred in rural locations, where open spaces favorable for harnessing wind also serve general aviation airports. As such, nearly 40 % of all United States wind turbines exist within 10 km of a small airport. Wind turbines generate electricity by extracting momentum from the atmosphere, creating downwind wakes characterized by wind-speed deficits and increased turbulence. Recently, the concern that turbine wakes pose hazards for small aircraft has been used to limit wind-farm development. Herein, we assess roll hazards to small aircraft using large-eddy simulations (LES) of a utility-scale turbine wake. Wind-generated lift forces and subsequent rolling moments are calculated for hypothetical aircraft transecting the wake in various orientations. Stably and neutrally stratified cases are explored, with the stable case presenting a possible worst-case scenario due to longer-persisting wakes permitted by lower ambient turbulence. In both cases, only 0.001 % of rolling moments experienced by hypothetical aircraft during down-wake and cross-wake transects lead to an increased risk of rolling.

Whitehouse, G. R., and R. E. Brown. "Modelling a helicopter rotor’s response to wake encounters." Aeronautical Journal 108, no. 1079 (January 2004): 15–26. http://dx.doi.org/10.1017/s0001924000004954.

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In recent years, various strategies for the concurrent operation of fixed-and rotary-wing aircraft have been proposed as a means of increasing airport capacity. Some of these strategies will increase the likelihood of encounters with the wakes of aircraft operating nearby. Several studies now exist where numerical simulations have been used to assess the impact of encounters with the wakes of large transport aircraft on the safety of helicopter operations under such conditions. This paper contrasts the predictions of several commonly-used numerical simulation techniques when each is used to model the dynamics of a helicopter rotor during the same idealised wake encounter. In most previous studies the mutually-induced distortion of the wakes of the rotor and the interacting aircraft has been neglected, yielding the so-called ‘frozen vortex’ assumption. This assumption is shown to be valid only when the helicopter encounters the aircraft wake at high forward speed. At the low forward speeds most relevant to near-airfield operations, however, injudicious use of the frozen vortex assumption may lead to significant errors in predicting the severity of a helicopter’s response to a wake encounter.

Pan, Weijun, Yuming Luo, Shuai Han, and Hao Wang. "Large Eddy Simulation Research on the Evolution Mechanism of Aircraft Wake Influenced by Cubic Obstacle." Geofluids 2022 (June 24, 2022): 1–17. http://dx.doi.org/10.1155/2022/1324531.

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Aircraft wake is a kind of intense air movement, and the study of its generation, development, and dissipation law is of great significance to the flight safety. There are abundant researches on the evolution of aircraft wakes affected by weather and ground effects; however, there are few studies on the influence of a single obstacle on the evolution of aircraft wake. In this article, in order to explore the influence of a single obstacle on the evolution of aircraft wake, firstly, we develop a computational fluid dynamics-based method of simulation of aircraft wake affected by cubic obstacle of different heights in order to obtain the wake intensity changes and position changes before and after being affected by the obstacle. Then, the result data are visualized and analyzed, and we obtain the results of velocity and Q criterion contours, circulation, and data related to wake vortex structure. CFD simulations are conducted, including the cases of the vertical distance between wake vortex and obstacle which is 20 m, 60 m, 100 m, and no obstacle. The quantitative results indicate that a single obstacle also has a great influence on the evolution of the wake vortex. Obstacle will shorten the time for the wake vortex to enter the fast decay stage, and the smaller the distance the wake vortex is above the obstacle, the faster it enters the fast decay stage. In the same time, the circulation will reduce 20% more under the same calculation time when the wake is 20 m above the obstacle than when the wake is 100 m above the obstacle, and the circulation will reduce 45% more than when there is no obstacle. Single obstacle also leads to the generation of multiple secondary vortices and rotates around the wake vortex, resulting in the increase of wake vortex core radius, wake vortex core spacing, and wake vortex height.

Pan, Weijun, Zirui Yin, Yuming Luo, Anding Wang, and Yuanjing Huang. "Dynamic Aircraft Wake Separation Based on Velocity Change." Aerospace 9, no. 11 (October 22, 2022): 633. http://dx.doi.org/10.3390/aerospace9110633.

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Traditional research on static wake-vortex reduction usually considers only the influence of external environmental factors, while ignoring the dynamic change in an aircraft’s flight state. In order to solve this problem, this paper proposes a method to reduce separation using dynamic wake information based on changes in flight velocity. Firstly, relying on the wake-vortex generation and dissipation model, the initial circulations and dissipation parameters of the wake vortex at different aircraft velocities are calculated. Then, the complete evolution process of the wake vortex generated by different types of aircraft at different velocities is analyzed, and the evolution law of a wake vortex with changing velocity is obtained. Afterwards, according to the actual aerodynamic shape of CRJ-900, the aerodynamic model for CRJ-900 when it encounters a wake vortex is established. The situation of an CRJ-900 encountering a wake vortex under TBS is analyzed, which proves that TBS is safe and has a certain reduction potential. Then, taking the rolling moment coefficient as the safety index, the minimum safe separations at different velocities are calculated. Finally, a simulation for the separation reduction based on a dynamic wake vortex is carried out. Compared with the static wake-based separation, the dynamic wake-based separation technology can greatly reduce the aircraft separation requirements while ensuring the operation safety. The final simulation results show that the dynamic separation reduction in CRJ-900 following a medium and heavy aircraft can reach 44.3% and 51.6%, respectively.

Pan, Wei-Jun, Yuan-Fei Leng, Tian-Yi Wu, Ya-Xing Xu, and Xiao-Lei Zhang. "Conv-Wake: A Lightweight Framework for Aircraft Wake Recognition." Journal of Sensors 2022 (July 15, 2022): 1–11. http://dx.doi.org/10.1155/2022/3050507.

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The recognition of aircraft wake vortex can provide an indicator of early warning for civil aviation transportation safety. In this paper, several wake vortex recognition models based on deep learning and traditional machine learning were presented. Nonetheless, these models are not completely suitable owing to their dependence on the visualization of LiDAR data that yields the information loss of in reconstructing the behavior patterns of wake vortex. To tackle this problem, we proposed a lightweight deep learning framework to recognize aircraft wake vortex in the wind field of Shenzhen Baoan Airport’s arrival and departure routes. The nature of the introduced model is geared towards three aspects. First, the dilation patch embedding module is used as the input representation of the framework, attaining additional rich semantics information over long distances while maintaining parameters. Second, we combined a separable convolution module with a hybrid attention mechanism, increasing the model’s attention to the space position of wake vortex core. Third, environmental factors that affect the vortex behavior of the aircraft’s wake were encoded into the model. Experiments were conducted on a Doppler LiDAR acquisition dataset to validate the effectiveness of the proposed model. The results show that the proposed network has an accuracy of 0.9963 and a recognition speed at 100 frames per second was achieved on an experimental device with 0.51 M parameters.

Ma, Yuzhao, Jiangbei Zhao, Haoran Han, Pak-wai Chan, and Xinglong Xiong. "Aircraft Wake Recognition Based on Improved ParNet Convolutional Neural Network." Applied Sciences 13, no. 6 (March 10, 2023): 3560. http://dx.doi.org/10.3390/app13063560.

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The occurrence of wake can pose a threat to the flight safety of aircraft and affect the runway capacity and airport operation efficiency. To effectively identify aircraft wake, this paper proposes a novel convolutional neural network (CNN) method of aircraft wake recognition based on the improved parallel network (ParNet). Depthwise separable convolution (DSC) was introduced into the ParNet to make the wake recognition model lightweight. In addition, the convolutional block attention module (CBAM) was introduced into the wake recognition model to improve the capacity of the model to extract the spatial features of the wind field. The proposed aircraft wake recognition method was used to identify the aircraft wake based on the lidar wind field scanning image of Hong Kong International Airport. The best wake recognition effect was obtained with a recognition accuracy of 98.91% and an F1 value of 98.90%. As the number of parameters of the model was only 0.46 M, the aircraft wake could be identified on an ordinary computer. Thus, the proposed method can effectively identify aircraft wake.

Gerz, Thomas, Frank Holzäpfel, and Denis Darracq. "Commercial aircraft wake vortices." Progress in Aerospace Sciences 38, no. 3 (April 2002): 181–208. http://dx.doi.org/10.1016/s0376-0421(02)00004-0.

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Дисертації з теми "Aircraft wake":

Stephan, Anton. "Wake vortices of landing aircraft." Diss., Ludwig-Maximilians-Universität München, 2014. http://nbn-resolving.de/urn:nbn:de:bvb:19-167566.

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Bertényi, Tamás. "Merger of aircraft wake vortices." Thesis, University of Cambridge, 2002. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.620288.

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Rodenhiser, Rebecca J. "An Ultrasonic Method for Aircraft Wake Vortex Detection." Digital WPI, 2005. https://digitalcommons.wpi.edu/etd-theses/1004.

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"This thesis documents the experimental proof of concept study for an ultrasonic method of wake vortex detection. A new acoustic technique is utilized to measure the circulation produced in the wake of lift-generating aircraft. Ultrasonic signals are transmitted in a path around the wake vortex, and are used to determine the average in-line velocity component along the acoustic path. It is shown herein that this velocity component is directly proportional to the net circulation value within the acoustic path. This is the first study to take this methodology and implement it in a realistic airport setting. This project included constructing a prototype and conducting field tests to prove the validity of this technology in a realistic environment setting. During field tests an acoustic path enclosed the vorticity shed behind one wing of a Piper PA-28 aircraft. Fourteen initial test flights were conducted in calm atmospheric conditions, and results show circulation values measured are comparable in magnitude and direction to expected circulations generated by the Piper PA-28 aircraft. Additional testing in various atmospheric conditions revealed the scope of practice for such a measurement technology. This study demonstrates the validity of the acoustic method in detecting aircraft wake vortices. Future investigations and applications utilizing this technique are discussed within."

Rodenhiser, Rebecca J. "An ultrasonic method for aircraft wake vortex detection." Link to electronic thesis, 2004. http://www.wpi.edu/Pubs/ETD/Available/etd-083105-160931/.

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Marles, David. "Effect of an axial jet aircraft wake vortices." Thesis, University of Bath, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.488899.

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An experimental study has been performed to evaluate the effect of a cold axial jet on a variety of typical aircraft wake vortex systems in the near-field. This research attempted to alleviate the vortex hazard imposed on trailing aircraft, which is especially important in the crowded skies around airfields.

Andronache, Constantin. "A study of aerosol interactions in aircraft wake and background atmosphere." Diss., Georgia Institute of Technology, 1996. http://hdl.handle.net/1853/26008.

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Stephan, Anton [Verfasser], and George C. [Akademischer Betreuer] Craig. "Wake vortices of landing aircraft / Anton Stephan. Betreuer: George C. Craig." München : Universitätsbibliothek der Ludwig-Maximilians-Universität, 2014. http://d-nb.info/1049393155/34.

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Roa, Perez Julio Alberto. "Development of Aircraft Wake Vortex Dynamic Separations Using Computer Simulation and Modeling." Diss., Virginia Tech, 2018. http://hdl.handle.net/10919/96199.

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This dissertation presents a research effort to evaluate wake vortex mitigation procedures and technologies in order to decrease aircraft separations, which could result in a runway capacity increase. Aircraft separation is a major obstacle to increasing the operational efficiency of the final approach segment and the runway. An aircraft in motion creates an invisible movement of air called wake turbulence, which has been shown to be dangerous to aircraft that encounter it. To avoid this danger, aircraft separations were developed in the 1970s, that allows time for wake to be dissipated and displaced from an aircraft's path. Though wake vortex separations have been revised, they remain overly conservative. This research identified 16 concepts and 3 sub-concepts for wake mitigation from the literature. The dissertation describes each concept along with its associated benefits and drawbacks. All concepts are grouped, based on common dependencies required for implementation, into four categories: airport fleet dependent, parallel runway dependent, single runway dependent, and aircraft or environmental condition dependent. Dynamic wake vortex mitigation was the concept chosen for further development because of its potential to provide capacity benefit in the near term and because it is initiated by air traffic control, not the pilot. Dynamic wake vortex mitigation discretizes current wake vortex aircraft groups by analyzing characteristics for each individual pair of leader and follower aircraft as well as the environment where the aircraft travel. This results in reduced aircraft separations from current static separation standards. Monte Carlo simulations that calculate the dynamic wake vortex separation required for a follower aircraft were performed by using the National Aeronautics and Space Administration (NASA) Aircraft Vortex Spacing System (AVOSS) Prediction Algorithm (APA) model, a semi-empirical wake vortex behavior model that predicts wake vortex decay as a function of atmospheric turbulence and stratification. Maximum circulation capacities were calculated based on the Federal Aviation Administration's (FAA) proposed wake recategorization phase II (RECAT II) 123 x 123 matrix of wake vortex separations. This research identified environmental turbulence and aircraft weight as the parameters with the greatest influence on wake vortex circulation strength. Wind has the greatest influence on wake vortex lateral behavior, and aircraft mass, environmental turbulence, and wind have the greatest influence on wake vortex vertical position. The research simulated RECAT II and RECAT III dynamic wake separations for Chicago O'Hare International (ORD), Denver International Airport (DEN) and LaGuardia Airport (LGA). The simulation accounted for real-world conditions of aircraft operations during arrival and departure: static and dynamic wake vortex separations, aircraft fleet mix, runway occupancy times, aircraft approach speeds, aircraft wake vortex circulation capacity, environmental conditions, and operational error buffers. Airport data considered for this analysis were based on Airport Surface Detection Equipment Model X (ASDE-X) data records at ORD during a 10-month period in the year 2016, a 3-month period at DEN, and a 4-month period at LGA. Results indicate that further reducing wake vortex separation distances from the FAA's proposed RECAT II static matrix, of 2 nm and less, shifts the operational bottleneck from the final approach segment to the runway. Consequently, given current values of aircraft runway occupancy time under some conditions, the airport runway becomes the limiting factor for inter-arrival separations. One of the major constraints of dynamic wake vortex separation at airports is its dependence on real-time or near-real-time data collection and broadcasting technologies. These technologies would need to measure and report temperature, environmental turbulence, wind speed, air humidity, air density, and aircraft weight, altitude, and speed.
PHD

Craig, Margaret Elizabeth. "Trailing-Edge Blowing of Model Fan Blades for Wake Management." Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/30886.

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Model fan blades designed to implement the wake management technique of trailing-edge blowing were tested in a linear cascade configuration. Measurements were made on two sets of blowing blades installed in the Virginia Tech low-speed linear cascade wind tunnel. The simple blowing blades were identical to the baseline GE Rotor B blades, aside from a slight difference in trailing-edge thickness, a set of internal flow passages, and a blowing slot just upstream of the trailing-edge on the suction side of the blade. The Kuethe vane blades were also slightly thicker at the trailing-edge, and had a set of nine evenly spaced vortex generators upstream of the blowing slot on the suction side. The cascade tunnel accommodates eight blades with adjustable tip-gap heights, although only the center four blades were replaced by blowing blades in this study. The tunnel has an inlet angle of 65.1â a, a stagger angle of 56.9â a and a flow turning angle of 11.8â a. The tip-gap was set to 0.004125c and the freestream velocity of 24.7m/s led to a Reynolds number based on the chord of 385,000. Blowing slot uniformity measurements made with a single hot-wire immediately behind the trailing-edge revealed that the blowing becomes more spanwise uniform as blowing rate is increased. The same occurs with the Kuethe vane blades, despite a spanwise serrated pattern that appears as a result of the upstream vortex generators. Cross-sections made perpendicular to the blade span gave preliminary evidence that the simple blowing wake deficit increases from the passive suction case at a blowing rate of 1.4% and becomes overblown by 2.6%. The Kuethe vane wake deficit does not increase at low blowing rates. Both sets of blowing blades indicated a slight angling of the wake towards the pressure side with blowing. Pitot-static full cross-sections of the simple blowing blades at x/ca = 0.839 and 1.877 verified the increase in wake depth and width at 1.4% as compared to the passive suction and non-blowing baseline cases, and the wake overblowing that occurs as blowing rate is increased to approximately 2.6%. The Kuethe vane blades only achieve partial wake cancellation at the maximum tested rate of 2.6% for these measurements. The results of the baseline study of Geiger (2005) are used for comparison with the mid-span velocity profiles made at four downstream locations. The velocity profiles clearly confirm the results of the normal-to-span and full cross-sections, while also revealing a decrease from the baseline of at least 25% in most of the maximum Reynolds normal stresses and turbulent kinetic energies at all rates between 1.4% and 2.7% for both sets of blowing blades. Spectral measurements of the simple blowing blades show clear reductions of the energy in the wake for all blowing rates over the majority of the range of normalized frequencies, while the Kuethe vane blades show reductions at all rates and all frequencies. By performing Fourier decompositions, the tone noise benefits over the non-blowing baseline blades are directly comparable in decibels. The optimum blowing rate for the simple blowing blades is clearly 2.5%, since this rate shows the most potential tone noise reduction. The Kuethe vane blades suggest decreases in tone noise over all of the tested blowing rates.
Master of Science

Schroeder, Nataliya. "Analysis of Potential Wake Turbulence Encounters in Current and NextGen Flight Operations." Thesis, Virginia Tech, 2011. http://hdl.handle.net/10919/40924.

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Wake vortices pose a threat to a following aircraft, because they can induce a roll and compromise the safety of everyone on board. Caused by a difference in pressure between the upper and the lower part of the wings, these invisible flows of air are a major hazard and have to be avoided by separating the aircraft at considerable distances. One of the known constraints in airport capacity for both departure and arrival operations is the large headway resulting from the wake spacing separation criteria. Reducing wake vortex separations to a safe level between successive aircraft can increase capacity in the National Airspace System (NAS) with corresponding savings in delay times. One of the main goals of the Wake Encounter Model (WEM) described in this thesis is to assess the outcome from future reduced separation criteria in the NAS. The model has been used to test probable encounters in todayâ s operations, and can also be used to test NextGen scenarios, such as Close Parallel Approaches and reduced in-trail separation flights. This thesis presents model enhancements to account for aircraft turning maneuvers, giving the wake a more realistic shape. Three major airspaces, New York, Southern California and Atlanta, were analyzed using the original and the enhanced WEM to determine if the enhanced model better represents the conditions in todayâ s operations. Additionally, some analysis on the wake lateral travel for closely spaced runways is presented in this thesis. Finally, some extension tools for post -analysis, such as animation tool and various graphs depicting the interactions between wake pairs were developed.
Master of Science

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Книги з теми "Aircraft wake":

Hallock, J. N. Aircraft wake vortices: An annotated bibliography (1923-1990). Washington D.C: Research and Development Service, U.S. Dept. of Transportation, Federal Aviation Administration, 1991.

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C, Miake-Lye R., and Langley Research Center, eds. Stratospheric aircraft exhaust plume and wake chemistry studies. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1992.

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E, Marshall Robert. Radar reflectivity in wingtip-generated wake vortices. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1997.

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Blackmore, Paul. Slate and tile roofs: Avoiding damage from aircraft wake vortices. Watford: CRC, 2002.

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Center, Langley Research, ed. Feasibility of detecting aircraft wake vortices using passive microwave radiometers. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.

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Center, Langley Research, ed. Characterizing the wake vortex signature for an active line of sight remote sensor. Clemson, SC: Radar Systems Laboratory, Electrical and Computer Engineering Dept., Clemson University, 1994.

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Severin, Theresa Ann. In the wake of the storm: Living beyond the tragedy of Flight 4184. Arlington Heights, IL: North Cross Press, 2008.

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Bilanin, Alan J. Interaction of spray aircraft wake with convective surface winds in hilly terrain. Davis, CA: USDA Forest Service, 1996.

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Vyshinski, V. V. Flight safety, aircraft vortex wake and airport operation capacity: Collection of papers. Moscow: [s.n.], 2002.

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Clark, Richard A. Back to the Bennington: Tales in the wake. Bennington, VT: Merriam Press, 2010.

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Частини книг з теми "Aircraft wake":

Ginevsky, A. S., and A. I. Zhelannikov. "Far Vortex Wake Behind a Turbojet Aircraft." In Foundations of Engineering Mechanics, 39–70. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-01760-5_4.

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Ginevsky, A. S., and A. I. Zhelannikov. "The Near Vortex Wake Behind a Single Aircraft." In Foundations of Engineering Mechanics, 33–37. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-01760-5_3.

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Tekitchamroon, Theerawit, Watchapon Rojanaratanangkule, and Vejapong Juttijudata. "Breaking the Aircraft Vortex Wake Near the Ground: Mitigation of Turbulence Wake Hazard." In Research Developments in Sustainable Aviation, 237–42. Cham: Springer International Publishing, 2023. http://dx.doi.org/10.1007/978-3-031-37943-7_31.

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Bellastrada, C., and C. Breitsamter. "Large Transport Aircraft Wake Vortex Affected by Vortex Devices." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 1–9. Berlin, Heidelberg: Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-540-39604-8_1.

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Campos, L. M. B. C., and J. M. G. Marques. "On Aircraft Response and Control During a Wake Encounter." In Progress in Industrial Mathematics at ECMI 2008, 747–52. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-12110-4_120.

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Holzäpfel, Frank, and Thomas Gerz. "Aircraft Wake Vortices: From Fundamental Research to Operational Application." In Atmospheric Physics, 219–37. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-30183-4_14.

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Chatelain, Philippe, Mattia Gazzola, Stefan Kern, and Petros Koumoutsakos. "Optimization of Aircraft Wake Alleviation Schemes through an Evolution Strategy." In Lecture Notes in Computer Science, 210–21. Berlin, Heidelberg: Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-19328-6_21.

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Lv, Peijian. "A Theoretical Analysis of Boundary Layer Ingestion and Wake Ingestion." In Power-Based Study of Boundary Layer Ingestion for Aircraft Application, 43–66. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-5497-9_3.

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Ruhland, Johannes, and Christian Breitsamter. "Wake Vortex Analysis on Transport Aircraft Wing Featuring Dynamic Flap Motion." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 739–48. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-79561-0_70.

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Politz, Christina, Benedikt Over, and Tania Kirmse. "The Application of Background Oriented Schlieren Method to Aircraft Wake Vortex Investigations." In Research Topics in Aerospace, 321–29. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-34738-2_19.

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Тези доповідей конференцій з теми "Aircraft wake":

Gaifullin, A. M., and G. G. Soudakov. "Aircraft Vortex Wake Dynamics." In World Aviation Congress & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1996. http://dx.doi.org/10.4271/965547.

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"NASA wake vortex research." In Aircraft Design, Systems, and Operations Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1993. http://dx.doi.org/10.2514/6.1993-4004.

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Nelson, Robert, and Eric Jumper. "Aircraft wake vortices and their effect on following aircraft." In AIAA Atmospheric Flight Mechanics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-4073.

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COUSTOLS, Eric, Eike STUMPF, Laurent JACQUIN, Frederic MOENS, Heinrich VOLLMERS, and Thomas GERZ. ""Minimised Wake": a Collaborative Research Programme on Aircraft Wake Vortices." In 41st Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-938.

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Schauerhamer, Daniel G., and Stephen K. Robinson. "Simulating Aircraft Wake Vortices with OVERFLOW." In 33rd AIAA Applied Aerodynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-3301.

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Vyshinsky, V. V. "Aircraft Vortex Wake and Airport Capacity." In World Aviation Congress & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1997. http://dx.doi.org/10.4271/975519.

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Huenecke, Klaus. "Wake vortex investigations of transport aircraft." In 13th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-1773.

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Hemati, Maziar, Jeff Eldredge, and Jason Speyer. "Wake Sensing for Aircraft Formation Flight." In AIAA Guidance, Navigation, and Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-4768.

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GREENE, GEORGE, JOHN LAMAR, and L. KUBENDRAN. "Aircraft vortices - Juncture, wing, and wake." In 1st National Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-3742.

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Baranov, N. A., and L. I. Turchak. "Investigation of aircraft vortex wake structure." In APPLICATION OF MATHEMATICS IN TECHNICAL AND NATURAL SCIENCES: 6th International Conference for Promoting the Application of Mathematics in Technical and Natural Sciences ‐ AMiTaNS ’14. AIP Publishing LLC, 2014. http://dx.doi.org/10.1063/1.4902258.

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Звіти організацій з теми "Aircraft wake":

Strickland, J., E. Tadios, and D. Powers. Wind tunnel study of wake downwash behind A 6% scale model B1-B aircraft. Office of Scientific and Technical Information (OSTI), May 1990. http://dx.doi.org/10.2172/6839285.

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Doyle, James D., M. A. Shapiro, Robert Gall, and Diana Bartels. Research Aircraft Observations and the Numerical Simulation of a Breaking Gravity Wave Event over Greenland Observed during FASTEX,. Fort Belvoir, VA: Defense Technical Information Center, January 1997. http://dx.doi.org/10.21236/ada330935.

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Brodie, Katherine, Brittany Bruder, Richard Slocum, and Nicholas Spore. Simultaneous mapping of coastal topography and bathymetry from a lightweight multicamera UAS. Engineer Research and Development Center (U.S.), August 2021. http://dx.doi.org/10.21079/11681/41440.

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Анотація:

A low-cost multicamera Unmanned Aircraft System (UAS) is used to simultaneously estimate open-coast topography and bathymetry from a single longitudinal coastal flight. The UAS combines nadir and oblique imagery to create a wide field of view (FOV), which enables collection of mobile, long dwell timeseries of the littoral zone suitable for structure-from motion (SfM), and wave speed inversion algorithms. Resultant digital surface models (DSMs) compare well with terrestrial topographic lidar and bathymetric survey data at Duck, NC, USA, with root-mean-square error (RMSE)/bias of 0.26/–0.05 and 0.34/–0.05 m, respectively. Bathymetric data from another flight at Virginia Beach, VA, USA, demonstrates successful comparison (RMSE/bias of 0.17/0.06 m) in a secondary environment. UAS-derived engineering data products, total volume profiles and shoreline position, were congruent with those calculated from traditional topo-bathymetric surveys at Duck. Capturing both topography and bathymetry within a single flight, the presented multicamera system is more efficient than data acquisition with a single camera UAS; this advantage grows for longer stretches of coastline (10 km). Efficiency increases further with an on-board Global Navigation Satellite System–Inertial Navigation System (GNSS-INS) to eliminate ground control point (GCP) placement. The Appendix reprocesses the Virginia Beach flight with the GNSS–INS input and no GCPs.