Academic literature on the topic 'Runways (Aeronautics) Mathematical models'
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Journal articles on the topic "Runways (Aeronautics) Mathematical models"
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Cao, Yihua, Yong Chen, and Yong Zhou. "Studies of capacity estimation of the airport with two parallel runways." Aeronautical Journal 109, no. 1098 (2005): 395–401. http://dx.doi.org/10.1017/s0001924000000816.
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Abstract The analytical capacity models of an airport with two runways system are developed in this paper and the theoretical capacity curves yielded by this model are analysed. The statistic airport capacity estimation methodology based on historical data is introduced as well. Both analytical models and statistic strategy are applied to estimate the capacity of the two runways system of a typical airport. Two sets of airport capacity curves obtained in different ways are compared and analysed. The result of the analysis indicates that the mathematical model works effectively in a fairly accurate way in the estimation of airport capacity.
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Ilie, Constantin Ovidiu, Dănuț Grosu, Oana Mocian, Radu Vilău, and Daniela Bartiș. "Using Statistically Based Modeling for Vehicle Dynamics." Advanced Materials Research 1036 (October 2014): 564–67. http://dx.doi.org/10.4028/www.scientific.net/amr.1036.564.
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This paper is a result of a research focused on statistical vehicles dynamics. Its main purpose is to establish mathematical description of vehicle dynamics based on statistically sufficient experimental data and using statistical instruments. The results are analytical expressions and graphical representations that can be used in situations other than those the data were obtained. Experimental research program objective was to obtain a variety of data to define the dynamics of a vehicle. It involved a large number of tests, more than 100, on different runways, pavement, mosaic tiles or asphalt. They were performed in various weather conditions, sunny and warm weather or rain or sleet and snow. The driving style varied between normal and sport ones. The experimental data were used in obtaining mathematical models that define certain dependency between dynamic parameters. There were issued multiple linear regressions with one resulting parameter. If we analyzed the models we issued we notice that the more factorial parameters are involved, the higher the accuracy of the model we get.
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Chen, Haotian, Yijun Liu, and Yunuo Zhang. "Research on the Aerodynamic Performance of an Airfoil." Journal of Physics: Conference Series 2469, no. 1 (2023): 012029. http://dx.doi.org/10.1088/1742-6596/2469/1/012029.
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Abstract Airfoils provide lift force for planes and keep planes flying in the atmosphere. Different airfoils have distinct performance characteristics based on their shapes, influencing the flying condition of planes and people’s safety. Therefore, an airfoil’s shape must be carefully studied and deliberated on because it’s an engineer’s professional duty to protect people’s safety with engineering knowledge. In this paper, physical and mathematical models are applied to analyze the shape and corresponding characteristics of an airfoil. Models, including Bernoulli’s Equation and Ideal gas Law, are applied, which are fundamental engineering models. Professional computational tools, including Matlab, are also utilized for the accuracy of data and plots and convenience in data analysis. As aeronautics technology keeps developing, more challenges will arise. Based on the data of existing airfoils, this paper also brings some considerations for the future of airfoil designs which are going to need to satisfy more flying conditions and types of aircraft.
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Li, Daijin, and Kai Luo. "One-Dimensional Model Incorporated with Mechanical Loss and Auxiliary Power for Evaluating Thermodynamic Performance of Stirling Engine." International Journal of Nonlinear Sciences and Numerical Simulation 17, no. 3-4 (2016): 137–48. http://dx.doi.org/10.1515/ijnsns-2014-0063.
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AbstractStirling engines are regarded as an efficient and promising power system for underwater devices. Currently, many models have been used to evaluate thermodynamic performance of Stirling engine, but in which mechanical loss and auxiliary power still cannot be modeled with proper mathematical models. A four-cylinder double-acting Stirling engine for Unmanned Underwater Vehicle (UUV) is discussed in this paper. Referring to the Stirling engine experimental results from National Aeronautics and Space Administration (NASA), a one-dimensional model incorporated with empirical equations of mechanical loss and auxiliary power obtained from experiments is presented. The P-40 Stirling engine with sufficient testing results from NASA is utilized to validate the accuracy of the modified one-dimensional model. And the comparison results suggest good agreement between testing and simulation results. The output power maximum error of theoretical analysis results is less than 18 % over testing results, and the maximum error of input power is no more than 9 %. In short, the one-dimensional model is adequate to evaluate the thermodynamic performance of the Stirling engine.
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Kretulis, V. S. "INVESTIGATION OF THE INFLUENCE OF CORRELATED COLOR TEMPERATURE OF LED illuminatorS AS A FACTOR OF SAFETY LIGHTING OF HIGHWAYS FOR DIFFICULT WEATHER CONDITIONS." Optoelektronìka ta napìvprovìdnikova tehnìka 56 (December 7, 2021): 89–96. http://dx.doi.org/10.15407/iopt.2021.56.089.
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A investigation of the dependence of relative horizontal illumination level and brightness of the most common types of road surface in Ukraine when using LED illuminators with different spectral distribution of radiation in the presence of aerial aerosols of different optical densities (strong, moderate, weak fog and haze) is performed. Mathematical models of LED illuminators with correlated color temperature Tcc = (2200÷8400) K in the visible range of the spectrum λ = (380÷780) nm have been created. Their use together with the selected model of the spectral dependence of the scattering index β (λ) (Ferdinandоv’s model) of the atmospheric environment with the presence of aqueous aerosols, which cause a limited meteorological range of visibility MOR = (0.1÷3) km, showed a slight (1%) advantage in creation of illumination from lamps of a warm spectrum of radiation (TCC = 2200 K) in comparison with cold (Tcc = 8400 K) for cases of strong fogs with MOR = 100 m. Calculations involving the analysis of mathematical modeling of the spectral distribution of the reflection coefficients for two types of road surface (new and worn asphalt) proved that when using warm spectrum illuminators the brightness of the most common in Ukraine old asphalt pavement in the conditions of MOR = 100 m by 5% exceeds the corresponding value of the cold spectrum emitters. This difference gradually decreases as visibility is improved due to the weaker spectral dependence of β (λ) and at MV = 3 km is 4.5%. The advantage of using warm spectrum illuminators will be significantly enhanced for the case of estimating the brightness of the coverage over long distances, for example, airfield runways, which will significantly improve flight safety.
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Nzao, Anthony Bassesuka Sandoka. "Study of the Simulation and Application of the PEEC Method for Modeling the Prediction of Emissions Radiated by the Onboard Electronic Wiring System." Computer and Information Science 17, no. 2 (2024): 7. http://dx.doi.org/10.5539/cis.v17n2p7.
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The coexistence of electronic power and control systems in the same box presents a serious threat to the proper functioning of electronic systems integrated into automobiles, aeronautics and space. Thus, managing the electromagnetic compatibility of these systems constitutes a challenge, particularly given electromagnetic phenomena. This paper describes a simulation study and application of the partial element equivalent circuit method to model the prediction of radiated emissions from the onboard electronic cable system. In this article, we first explain the use of the partial cell equivalent circuit modeling method, then describe its mathematical formulation and introduce the different electromagnetic phenomena it considers in connection with wiring, then propose radiation calculations electromagnetic as a function of the geometry of the discrete cells taking into account the increase in frequency. The goal is to get as close to the structure as possible. To balance the accuracy and speed of the proposed method, we replaced the partial capacities with the equivalent capacities so as to considerably minimize the number of capacities, the complexity of the system and the computational time requirement. This option adapts the partial element equivalent circuit method to the study of larger structures such as cable structures and provides an efficient and rapid way to simulate electromagnetic radiation. To achieve this objective, we have associated the physical laws of electromagnetic wave propagation with the method of modeling equivalent circuits using partial elements because it is easy to manipulate flat surfaces and cables. 2D simulations based on the proposed models were developed as well as the verification of the consistency of the different models, by comparing the fractal dimensions of the program results with those of the figures obtained experimentally.
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Vyshinsky, V. V., та K. T. Zoan. "Аtmospheric wind flow around the mountain landscape in the vicinity of Danang airport and flight safety issues". Civil Aviation High Technologies 24, № 6 (2021): 27–41. http://dx.doi.org/10.26467/2079-0619-2021-24-6-27-41.
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Wind boundary layer flow over the mountain landscape and large structures located around runways (RWs) creates coherent vortex structures (CVSs) that can cross a glideslope and airspace in the vicinity of an airport. The aircraft, encountering a vortex structure, experiences significant changes of the aerodynamic forces and moments, what is especially hazardous due to proximity to terrain. From a mathematical point of view, the solution of this problem presents a challenge due to extremely large space – time scale of the phenomenon, the lack of relevant atmospheric models, as well as comprehensive initial – boundary conditions in numerical modeling. In this paper, a composite solution is constructed: the CVSs area generation is computed in sufficient details within the framework of the grid method. Based on the data obtained in the approximation of analytical functions, an initial vortex structure is formed, the evolution and stochastics of which are modeled within the potential approximation by means of Rankine vortices. The evaluation of the forces and moments increment from the impact of vortex structures on the aircraft was carried out by the panel method using the engineering approach. As an example, the CVSs, resulting from wind flow around the mountainous area of the Son Tra Peninsula, that is located short of RWs 35R-17L and 35L-17R of Da Nang airport, are investigated. To improve the computational grids quality and verify the method of solving the boundary value problem for the Reynolds-averaged Navier-Stokes equations, we used the criteria based on the principle of maximum pressure, requiring Q-parameter positivity property in the vortices cores and flow separation regions. A CVS related aviation event, involving a passenger aircraft MC-21, is studied. The aircraft, after takeoff from RW 35R-17L setting the course close to the direction of the vortex wind structure axis from the Son Tra Peninsula, encountered the mountainous area CVS.
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Ketabdari, Misagh, Ignacio P. Millán, Emanuele Toraldo, Maurizio Crispino, and Mariano Pernetti. "Analytical Optimization Model to Locate and Design Runway-Taxiway Junctions." Open Civil Engineering Journal 15, no. 1 (2021): 347–59. http://dx.doi.org/10.2174/1874149502115010347.
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Aims: Air traffic and airport operations are expected to experience significant growth worldwide in the upcoming years. One of the possible approaches to adapt to this demand-led growth in the sector, while guaranteeing optimal levels of airport services and operations safety, is to maximize the capacities of busy airport infrastructures (in particular runways) by evacuating them in the shortest time possible to be ready for hosting next operations. Background: The main research areas in this field range from statistical risk analyses based on the registered accidents databases to simulation analyses modelling the behaviour of the aircraft during landing operations. Objective: The main objective of this study is to determine precisely the optimal distances of runway-taxiway junctions from the runway’s threshold, according to numerous impact parameters such as airport climate pattern, operating aircraft categories, infrastructure type, and capacity, route connections, operating costs, and associated risks. Methods: The authors developed a mathematical model with the goal of simulating the dynamic behaviour of the aircraft during landing and possible consequences introduced by the presence of contaminants over the pavement surface, by calculating their braking distances, and finally to optimize the use of existing infrastructures, specially runway-taxiway junctions, of a commercial airport. In this regard, the interactions between landing gear, pavement, and fluid were carefully analysed. The dynamic pavement skid resistance values in wet pavement conditions were evaluated for optimizing the required landing distances, which are setting the base for optimizing the location of the taxiway junctions. An Italian international airport was selected as the case study to be simulated by the developed model in order to optimize its runway capacity and maximize its rate of operations. Results: In the process, two different scenarios are simulated with the developed model; a modified design of an existing runway and an alternative design solution for constructing a new runway. The developed model offers improvements for both scenarios with respect to the current runway configurations in terms of reduction in mean rolling distances. The simulation of the selected case study shows that the taxiway modification scenario achieves a reduction of 23% in the mean rolling distance for wet and 25% for dry pavement conditions. While, for designing a new runway, greater reductions of 27% for wet and 39% for dry pavement conditions are obtained due to the higher flexibilities and degrees of freedom in designing a runway from the beginning. Conclusion: The developed model can precisely propose new configurations of the runway-taxiway junctions with lower mean rolling distances, which lower the operation costs and fuel consumption, decrease the runway evacuation times and increase the capacity of the airfield. The main advantage of this model is its ability to cover a wider spectrum of boundary conditions with respect to the existing models and its applicability for designing new runways, plus to optimize the configuration of existing infrastructures in order to satisfy the evolution of the industry.
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De Lemos, Hugo, Michel M. Verstraete, and Mary Scholes. "Parametric Models to Characterize the Phenology of the Lowveld Savanna at Skukuza, South Africa." Remote Sensing 12, no. 23 (2020): 3927. http://dx.doi.org/10.3390/rs12233927.
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Mathematical models, such as the logistic curve, have been extensively used to model the temporal evolution of biological processes, though other similarly shaped functions could be (and sometimes have been) used for this purpose. Most previous studies focused on agricultural regions in the Northern Hemisphere and were based on the Normalized Difference Vegetation Index (NDVI). This paper compares the capacity of four parametric double S-shaped models (Gaussian, Hyperbolic Tangent, Logistic, and Sine) to represent the seasonal phenology of an unmanaged, protected savanna biome in South Africa’s Lowveld, using the Fraction of Absorbed Photosynthetically Active Radiation (FAPAR) generated by the Multi-angle Imaging SpectroRadiometer-High Resolution (MISR-HR) processing system on the basis of data originally collected by National Aeronautics and Space Administration (NASA)’s Multi-angle Imaging SpectroRadiometer (MISR) instrument since 24 February 2000. FAPAR time series are automatically split into successive vegetative seasons, and the models are inverted against those irregularly spaced data to provide a description of the seasonal fluctuations despite the presence of noise and missing values. The performance of these models is assessed by quantifying their ability to account for the variability of remote sensing data and to evaluate the Gross Primary Productivity (GPP) of vegetation, as well as by evaluating their numerical efficiency. Simulated results retrieved from remote sensing are compared to GPP estimates derived from field measurements acquired at Skukuza’s flux tower in the Kruger National Park, which has also been operational since 2000. Preliminary results indicate that (1) all four models considered can be adjusted to fit an FAPAR time series when the temporal distribution of the data is sufficiently dense in both the growing and the senescence phases of the vegetative season, (2) the Gaussian and especially the Sine models are more sensitive than the Hyperbolic Tangent and Logistic to the temporal distribution of FAPAR values during the vegetative season, and, in particular, to the presence of long temporal gaps in the observational data, and (3) the performance of these models to simulate the phenology of plants is generally quite sensitive to the presence of unexpectedly low FAPAR values during the peak period of activity and to the presence of long gaps in the observational data. Consequently, efforts to screen out outliers and to minimize those gaps, especially during the rainy season (vegetation’s growth phase), would go a long way to improve the capacity of the models to adequately account for the evolution of the canopy cover and to better assess the relation between FAPAR and GPP.
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Soelem, Aafnan Bhuiyan. "Formulation of Flood Inundation Map in Jamalpur District by Mathematical Modeling using HEC Packages." Journal of Water Resources and Pollution Studies 3, no. 3 (2018): 33–66. https://doi.org/10.5281/zenodo.1560739.
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Bangladesh lies in the convergence zone of three large rivers of the world-Ganges, Brahmaputra, Meghna, which is called the GBM basin. The Ganges, Brahmaputra and Meghna (GBM) river basins occupy about 1.75 x 106 km<sup>2</sup> of the Himalayan region. More than half a billion people in Nepal, India, Bhutan and Bangladesh are directly or indirectly dependent on the water resources of the GBM rivers. Being in this zone, Bangladesh faces heavy rainfall in the monsoon season of June to October, thus a huge amount of water drains out each year through the country. This drain out, along with various other reasons, causes frequent flooding all over Bangladesh. Thus, it is necessary to develop tools for the hydrological study of these three river basins or prediction tools to understand the consequence of different rainfall patterns. The reason of flood in the northern and mid-northern part of Bangladesh is overflowing of Brahmaputra (Jamuna) river. In this thesis work, different hydrologic and hydrodynamic models have been used to go through a number of steps and ultimately, a flood inundation map of Jamalpur district, which lies in the bank of Jamuna river, has been generated. The hydrologic model, HEC-HMS (Hydrologic Engineering Center-Hydrologic Modeling System) has been used to delineate the whole Brahmaputra watershed which lies mostly in the Indian north-eastern region, on the foothills of the Himalayas. Gridded rainfall gages from NASA (National Aeronautics and Space Administration) were used for precipitation input. The model was calibrated and validated for 2 different years at Bahadurabad point at Jamalpur. The purpose of calibration and validation was to set up a certain set of model parameters for different rainfall patterns. HECRAS (Hydrologic Engineering Center-River Analysis System) mathematical model was used to point out the water level for the resultant discharge. With the help of Arc-GIS (Geographical Information System) and HEC-GeoRAS (Hydrologic Engineering Center-Geographic River Analysis System), the flood inundation map of Jamalpur was generated for some of the highest water levels. Expectedly, the highest amount of inundation was observed in the months of July, August and September, the months of high monsoon rainfall. Some of the shortcomings of the thesis work were not counting on the land use pattern of the Brahmaputra basin for discharge, using arithmetic mean for sub basin rainfall gage weights, using observed water level in the downstream boundary condition for HEC-RAS etc. The flood inundation mapping can be used for future flood hazard management for predicted rainfall and help mitigate the damage and further losses. The hydrologic modeling can be used for further calibration for future precipitation prediction, also can be used for categorizing hydrologic characteristics for Brahmaputra basin.
Dissertations / Theses on the topic "Runways (Aeronautics) Mathematical models"
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Kim, Byung Jong. "Optimal runway exit design and capacity enhancement." Diss., Virginia Tech, 1993. http://hdl.handle.net/10919/38637.
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Congestion and delay problems at airports have received much attention in recent years because of the unbalanced condition between demand and supply. Recent demand forecasts indicate that the problems are expected to increase in the next decade. Relieving congestion of the air transportation networks requires several strategies to enhance the runway capacity. Among these strategies is reducing the runway occupancy time a critical factor in affecting runway capacity. And one approach to reducing the runway occupancy time (ROT) is locating the high speed exits optimally.
In addressing the reduction of the runway occupancy time, a full information on the distribution of aircraft landing distance is required. The landing performance at a specific airport may be found by observing the actual landings. However, this is costly and may not be transferable to other airports. An alternative approach is to use a simulation model. A simulation model was built at Center for Transportation Research at Virginia Tech based on point mass kinematics in the flying phase over runway and the ground roll phase on runway to predict the landing roll distance and time to a specified exit speed. Many influencing parameters were incorporated into the model, and then were calibrated using the field data obtained from real operations.
The prediction of a nominal landing roll distance and time to decelerate to a specified exit speed is not sufficient for estimating ROT because the additional time to reach a designated exit should be taken into account. To compute the additional time, a braking adjustment scheme is selected from several alternative schemes. The combination of the selected braking adjustment scheme and the simulation model approximates very closely the observed ROT.
An optimization model is formulated to determine the exit locations so as to minimize the weighted average ROT of the defined aircraft mix. A polynomial-time solution algorithm is developed for this model using Dynamic Programming technique. The major input parameters for the model are the distribution of the landing roll distance to the specified exit speed and the information on the aircraft mix. The model structured to address the problem of designing a new runway as well as the problem of improving an existing runway.
A runway capacity model is used to convert the optimized ROT into capacity gains. Four scenarios are analyzed. Among the scenarios, one is based on the present Air Traffic Control procedures, and three are based on the future developments. The capacity analysis reveals that the ROT does not affect the runway capacity for landing operations. However, the ROT is found as a critical factor for the runway capacity for mixed operations. Hence, the ROT should be optimized for the current system and more crucially for the future developments. The capacity gains by optimizing the ROT under the current Air Traffic Control systems and standards are estimated 2 to 7 more operations per hour. These gains will increase to 20 more operations per hour in the future environment.<br>Ph. D.
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Knight, Peter Robin. "Artificial intelligence and mathematical models for intelligent management of aircraft data." Thesis, University of Southampton, 2012. https://eprints.soton.ac.uk/355717/.
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Increasingly, large volumes of aircraft data are being recorded in an effort to adapt aircraft maintenance procedures from being time-based towards condition-based techniques. This study uses techniques of artificial intelligence and develops mathematical models to analyse this data to enable improvements to be made in aircraft management, affordability, availability, airworthiness and performance. In addition, it highlights the need to assess the integrity of data before further analysis and presents the benefits of fusing all relevant data sources together. The research effort consists of three separate investigations that were undertaken and brought together in order to provide a unified set of methods aimed at providing a safe, reliable, effective and efficient overall procedure. The three investigations are: 1. The management of helicopter Health Usage Monitoring System (HUMS) Condition Indicators (CIs) and their analysis, using a number of techniques, including adaptive thresholds and clustering. These techniques were applied to millions of CI values from Chinook HUMS data. 2. The identification of fixed-wing turbojet engine performance degradation, using anomaly detection techniques, applied to thousands of in-service engine runs from Tornado aircraft. 3. The creation of models to identify unusual aircraft behaviour, such as uncommanded flight control movements. Two Chinook helicopter systems were modelled and the models were applied to over seven hundred in-service flights. In each case, the existing techniques were directed toward a condition-based maintenance approach, giving improved detection and earlier warning of faults.
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Kumar, Niraj. "A genetic algorithm based approach for air cargo loading problem." Thesis, Click to view the E-thesis via HKUTO, 2006. http://sunzi.lib.hku.hk/hkuto/record/B38576818.
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Yao, Yufeng. "Topics in Fractional Airlines." Diss., Georgia Institute of Technology, 2007. http://hdl.handle.net/1853/14563.
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Fractional aircraft ownership programs offer companies and individuals all the benefits of owning private jet, such as safety, consistency, and guaranteed availability, at a fraction of the cost of owning an aircraft. In the fractional ownership model, the partial owners of an aircraft are entitled to certain number of hours per year, and the management company is responsible for all the operational considerations and making sure an aircraft is available to the owners at the requested time and location.
This thesis research proposes advance optimization techniques to help the management company to optimally operate its available resources and provides tools for strategic decision making. The contributions of this thesis are:
(i) The development of optimization methodologies to assign and schedule aircraft and crews so that all flight requests are covered at the lowest possible cost. First, a simple model is developed to solve the crew pairing and aircraft routing problem with column generation assuming that a crew stays with one specific aircraft during its duty period. Secondly, this assumption is partially relaxed to improve resource utilization by revising the simple model to allow a crew to use another aircraft when its original aircraft goes under long maintenance. Thirdly, a new comprehensive model utilizing Benders decomposition technique and a fleet-station time line is proposed to completely relax the assumption that crew stays with one specific aircraft. It combines the fleet assignment, aircraft routing, and crew pairing problems. In the proposed methodologies, real world details are taken into consideration, such as crew transportation and overtime costs, scheduled and unscheduled maintenance effects, crew rules, and the presence of non-crew-compatible fleets. Scheduling with time windows is also discussed.
(ii) The analysis of operational strategies to provide decision making support. Scenario analyses are performed to provide insights on improving business profitability and aircraft availability, such as impact of aircraft maintenance, crew swapping, effect of increasing demand by Jet-card and geographical business expansion, size of company owned aircraft, and strategies to deal with the stochastic feature of unscheduled maintenance and demand.
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Baig, Saood Saeed. "A simple moving boundary technique and its application to supersonic inlet starting /." Thesis, McGill University, 2008. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=112555.
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In this thesis, a simple moving boundary technique has been suggested, implemented and verified. The technique may be considered as a generalization of the well-known "ghost" cell approach for boundary condition implementation. According to the proposed idea, the moving body does not appear on the computational grid and is allowed to move over the grid. The impermeable wall boundary condition is enforced by assigning proper gasdynamic values at the grid nodes located inside the moving body close to its boundaries (ghost nodes). The reflection principle taking into account the velocity of the boundaries assigns values at the ghost nodes. The new method does not impose any particular restrictions on the geometry, deformation and law of motion of the moving body.<br>The developed technique is rather general and can be used with virtually any finite-volume or finite-difference scheme, since the modifications of the schemes themselves are not required. In the present study the proposed technique has been incorporated into a one-dimensional non-adaptive Euler code and a two-dimensional locally adaptive unstructured Euler code.<br>It is shown that the new approach is conservative with the order of approximation near the moving boundaries. To reduce the conservation error, it is beneficial to use the method in conjunction with local grid adaptation.<br>The technique is verified for a number of one and two dimensional test cases with analytical solutions. It is applied to the problem of supersonic inlet starting via variable geometry approach. At first, a classical starting technique of changing exit area by a moving wedge is numerically simulated. Then, the feasibility of some novel ideas such as a collapsing frontal body and "tractor-rocket" are explored.
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Zhao, Yiming. "Efficient and robust aircraft landing trajectory optimization." Diss., Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/43586.
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This thesis addresses the challenges in the efficient and robust generation and optimization of three-dimensional landing trajectories for fixed-wing aircraft subject to prescribed boundary conditions and constraints on maneuverability and collision avoidance. In particular, this thesis focuses on the airliner emergency landing scenario and the minimization of landing time.
The main contribution of the thesis is two-fold. First, it provides a hierarchical scheme for integrating the complementary strength of a variety of methods in path planning and trajectory optimization for the improvement in efficiency and robustness of the overall landing trajectory optimization algorithm. The second contribution is the development of new techniques and results in mesh refinement for numerical optimal control, optimal path tracking, and smooth path generation, which are all integrated in a hierarchical scheme and applied to the landing trajectory optimization problem.
A density function based grid generation method is developed for the mesh refinement process during numerical optimal control. A numerical algorithm is developed based on this technique for solving general optimal control problems, and is used for optimizing aircraft landing trajectories. A path smoothing technique is proposed for recovering feasibility of the path and improving the tracking performance by modifying the path geometry. The optimal aircraft path tracking problem is studied and analytical results are presented for both the minimum-time, and minimum-energy tracking with fixed time of arrival. The path smoothing and optimal path tracking methods work together with the geometric path planner to provide a set of feasible initial guess to the numerical optimal control algorithm.
The trajectory optimization algorithm in this thesis was tested by simulation experiments using flight data from two previous airliner accidents under emergency landing scenarios.The real-time application of the landing trajectory optimization algorithm as part of the aircraft on-board automation avionics system has the potential to provide effective guidelines to the pilots for improving the fuel consumption during normal landing process, and help enhancing flight safety under emergency landing scenarios. The proposed algorithms can also help design optimal take-off and landing trajectories and procedures for airports.
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"Growth, competitions and strategies in the air transport industry in Pearl River Delta of China." 2008. http://library.cuhk.edu.hk/record=b5893637.
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Xu, Fang.<br>Thesis (M.Phil.)--Chinese University of Hong Kong, 2008.<br>Includes bibliographical references (leaves 75-79).<br>Abstracts in English and Chinese.<br>Abstract --- p.i<br>Acknowledgement --- p.ii<br>Chapter 1 --- Introduction --- p.1<br>Chapter 2 --- Background Information --- p.3<br>Chapter 2.1 --- Growth of Air-Transportation Industry --- p.3<br>Chapter 2.1.1 --- General Figures --- p.3<br>Chapter 2.1.2 --- Growth of Air Cargo Market --- p.3<br>Chapter 2.1.3 --- Regulatory Support --- p.5<br>Chapter 2.2 --- The Focus: Pearl River Delta --- p.6<br>Chapter 2.2.1 --- Strategic Moves of Airports --- p.8<br>Chapter 2.2.2 --- Investment and Development of Airlines --- p.12<br>Chapter 2.2.3 --- Hong Kong VS Shen Zhen --- p.13<br>Chapter 3 --- Airport Competition --- p.14<br>Chapter 3.1 --- Introduction --- p.14<br>Chapter 3.2 --- One-period two port competition model --- p.15<br>Chapter 3.2.1 --- The basic model --- p.15<br>Chapter 3.2.2 --- Stackelberg Game --- p.23<br>Chapter 3.2.3 --- Location factor --- p.26<br>Chapter 3.3 --- Two-period two port competition model --- p.27<br>Chapter 3.3.1 --- The basic model --- p.27<br>Chapter 3.3.2 --- Switching cost --- p.30<br>Chapter 3.4 --- Conclusion --- p.33<br>Chapter 4 --- Combined airline VS full-cargo airline --- p.34<br>Chapter 4.1 --- Introduction --- p.34<br>Chapter 4.2 --- Model Setup --- p.35<br>Chapter 4.2.1 --- Modelling Capacity and Cost --- p.35<br>Chapter 4.2.2 --- Modelling Demand --- p.37<br>Chapter 4.2.3 --- The Optimization Framework --- p.37<br>Chapter 4.2.4 --- Decomposition of the Decision Process --- p.39<br>Chapter 4.3 --- Step 1: Strategies in the Passenger Market --- p.40<br>Chapter 4.3.1 --- Carriers enter the game with zero-inventory --- p.40<br>Chapter 4.3.2 --- Incumbent carrier has established initial capacity --- p.42<br>Chapter 4.4 --- Step 2: Strategies in the Cargo Market --- p.45<br>Chapter 4.5 --- Centralized decision --- p.49<br>Chapter 4.5.1 --- Both airlines have zero initial capacity in the passenger market --- p.50<br>Chapter 4.5.2 --- One airline has non-zero initial capacity in the passenger market --- p.51<br>Chapter 4.5.3 --- Both airlines have initial capacity in the cargo market --- p.53<br>Chapter 4.6 --- Conclusion --- p.53<br>Chapter 5 --- Demand growth and shifting --- p.55<br>Chapter 5.1 --- Introduction --- p.55<br>Chapter 5.2 --- Competition Scenario --- p.56<br>Chapter 5.2.1 --- Growth and shifting of passenger demand --- p.56<br>Chapter 5.2.2 --- Growth and shifting of cargo demand --- p.60<br>Chapter 5.3 --- Centralized decision making --- p.64<br>Chapter 5.4 --- conclusion --- p.72<br>Chapter 6 --- Conclusion --- p.73<br>Bibliography --- p.75
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"Monitoring air cargo shipments: a framework for detecting potential delays and prescribing corrective measures." 2007. http://library.cuhk.edu.hk/record=b5893196.
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Wan, Yulai.<br>Thesis (M.Phil.)--Chinese University of Hong Kong, 2007.<br>Includes bibliographical references (leaves 42-44).<br>Abstracts in English and Chinese.<br>Abstract --- p.i<br>Acknowledgement --- p.iii<br>Chapter Chapter 1 --- Introduction --- p.1<br>Chapter Chapter 2 --- Literature Review --- p.6<br>Chapter Chapter 3 --- Framework --- p.10<br>Chapter Chapter 4 --- The Simulation Model --- p.13<br>Chapter Chapter 5 --- Phase 1: Detect Potential Delay --- p.15<br>Chapter 5.1 --- The delay indicator --- p.15<br>Chapter 5.2 --- Setting tolerance level --- p.20<br>Chapter Chapter 6 --- Phase 2: Prescribe Corrective Measures --- p.22<br>Chapter 6.1 --- Corrective measures --- p.22<br>Chapter 6.2 --- Criteria of selecting measures --- p.24<br>Chapter Chapter 7 --- Phase 3: Validate Corrective Measures --- p.30<br>Chapter Chapter 8 --- Managerial Insights --- p.34<br>Chapter 8.1 --- "Improvement potential, tolerance level and lateness of correction" --- p.34<br>Chapter 8.2 --- Taking corrective measure before consolidation is helpful --- p.36<br>Chapter 8.3 --- Reducing activity duration is a better way to lower activity criticality --- p.37<br>Chapter Chapter 9 --- Conclusion and Future Research --- p.40<br>References --- p.42<br>Appendix: Program code for the simulation model --- p.45
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Weldon, John Phillips. "Dimensioned system dynamics modeling with external subprograms for Air Force aviation fuel." Phd thesis, 1993. http://hdl.handle.net/1885/145688.
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Turner, Sheelah Anne. "An application of a gravity model to air cargo at Vancouver International Airport." Thesis, 2002. http://hdl.handle.net/2429/12234.
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There has been very little research in the area of air cargo demand analysis and
forecasting. This thesis attempts to investigate the application of gravity models to air
cargo. Using international export volumes from Vancouver International Airport in 1998,
a gravity model was built. The inclusion of tariffs as an impedance factor allowed testing
of the effect of tariffs as predicted by gravity models. The results were consistent with
international trade theory that tariffs provide a barrier to international trade. Further, a
comparison is made between aggregate and disaggregate models (across commodities).
It was found that aggregation eliminates commodity specific characteristics.
In using the gravity model, there are two adjustments which need to be made to reduce
the bias in the model: firstly, adjustment is necessary to the bias inherent in the constant
term of a log-linear model; and a further adjustment is required when forecasting actual
levels rather than log levels. Even after adjustments for both types of bias, the gravity
model did not produce accurate forecasts. The aggregate model produced better forecasts
than the disaggregate model, but both sets of forecasts did not accurately predict the
actual volumes transported. This could be as a result of the stable nature of the variables
included in the model, which tend to change very slowly over time. Further, it is
apparent that other additional explanatory variables should be included in the models to
better capture the short-term changes in air cargo.
Books on the topic "Runways (Aeronautics) Mathematical models"
1
Szydło, Antoni. Statyczna identyfikacja parametrów modeli nawierzchni lotniskowych. Oficyna Wydawnicza Politechniki Wrocławskiej, 1995.
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2
Samanant, Paul. Description of the AILS alerting algorithm. National Aeronautics and Space Administration, Langley Research Center, 2000.
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3
Waller, Marvin C. An analysis of the role of ATC in the AILS concept. National Aeronautics and Space Administration, Langley Research Center, 2000.
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4
National Research Council (U.S.). Transportation Research Board., ed. Modeling and analysis of airport and aircraft operations. Transportation Research Board, 1989.
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5
G, Totiashvili L., and Rīgas civīlās aviācijas inženieru institūts., eds. Matematicheskoe modelirovanie zadach dinamiki i bezopasnosti poletov v grazhdanskoĭ aviat͡s︡ii: Sbornik nauchnykh trudov. RIO RKIIGA, 1987.
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6
Zhivetin, Vladimir. Metody i sredstva obespechenii︠a︡ bezopasnosti poleta: Riski i bezopasnostʹ aviat︠s︡ionnykh sistem. In-t problem riska, 2010.
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G, T͡S︡ipenko V., and Moskovskiĭ institut inzhenerov grazhdanskoĭ aviat͡s︡ii., eds. Matematicheskoe modelirovanie v zadachakh letnoĭ ėkspluatat͡s︡ii vozdushnykh sudov: Sbornik nauchnykh trudov. Moskovskiĭ in-t inzhenerov grazhdanskoĭ aviat͡s︡ii, 1993.
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8
Center, Langley Research, ed. Numerical simulation of swept-wing flows: A progress report for graduate program in aeronautics. National Aeronautics and Space Administration, Langley Research Center, 1991.
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9
M, Adelman Howard, Haftka Raphael T, United States. National Aeronautics and Space Administration., and Virginia Polytechnic Institute and State University., eds. Sensitivity analysis in engineering: Proceedings of a symposium sponsored by the National Aeronautics and Space Administration and Virginia Polytechnic Institute and State University, and held at Langley Research Center, Hampton, Virginia, September 25-26, 1986. NASA, Scientific and Technical Information Branch, 1987.
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Ozoka, Angus Ifeanyi. Aviation facilities planning, research, and development: A global experience. Nigerian Gong Press, 1997.
Find full textBook chapters on the topic "Runways (Aeronautics) Mathematical models"
1
Feistauer, M., J. Felcman, and I. Straskraba. "Finite Difference and Finite Volume Methods for Nonlinear Hyperbolic Systems and the Euler Equations." In Mathematical and Computational Methods for Compressible Flow. Oxford University PressOxford, 2003. http://dx.doi.org/10.1093/oso/9780198505884.003.0004.
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Abstract In modern technologies one often encounters the necessity to solve compressible flow with a complicated structure. There are several conceivable models of compressible flow. Let us mention, for example, the model of inviscid, stationary, irrotational or rotational subsonic flow using the stream function formulation, and the models of transonic flow based on the small perturbation equation or full potential equation. There exists an extensive literature about the finite difference or finite element methods for the numerical solution of these models. (For a survey of mathematical and numerical methods for these models, see (Feistauer, 1998).) In a number of problems, the potential models are not sufficiently accurate, particularly in high speed (transonic or hypersonic) flow, because of the appearance of the so-called strong shocks with large entropy and vorticity production. This leads to the necessity of using the complete system of conservation laws consisting of the continuity equation, the Euler equations of motion and the energy equation (called the Euler equations in brief), which has been widely used during the last few decades for the modelling of flows in aeronautics, the aviation industry and steam or gas turbine design. Successively, the Euler equations have begun to be applied also to low Mach number problems on the one hand and to problems with chemical reactions on the other. These models neglect, of course, viscosity, but in many situations they give good results, reliable from the point of view of comparisons with experiments.
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Oukassi, Abdellah. "Implementing ADRC and PI Controls for a Sensorless Induction Motor Supplied by a Multi-Level Converter and Using PV Sources." In Induction Motors - Latest Research and Applications. IntechOpen, 2025. https://doi.org/10.5772/intechopen.1006027.
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The proposed book will focus on the controls of induction machines aimed at exploiting them in the field of speed variation (electric vehicles, aeronautics, etc.). In this work, the authors utilize cascaded multi-level converters to reduce the harmonic distortion rate of the voltages at the machine’s input. The converter is controlled by pulse width modulation (PWM) technique. The use of active disturbance rejection control (ADRC) will contribute to eliminating internal disturbances (undesired variations in machine resistances) as well as minimizing external effects (inertia, resisting torque). State observers are employed to estimate mechanical speed, allowing the elimination of the speed sensor in the system. The mathematical models obtained have been simulated using MATLAB/Simulink software. Several scenarios have been tested through simulation, including comparing ADRC and PI control, and the effect of varying atmospheric conditions on PV power supply and consequently on the machine.
Conference papers on the topic "Runways (Aeronautics) Mathematical models"
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Pawlus, W., J. E. Nielsen, H. R. Karimi, and K. G. Robbersmyr. "Further results on mathematical models of vehicle localized impact." In 2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics (ISSCAA 2010). IEEE, 2010. http://dx.doi.org/10.1109/isscaa.2010.5634041.
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Fonzi, N. "New insights on limit cycle oscillations due to control surface freeplay." In Aeronautics and Astronautics. Materials Research Forum LLC, 2023. http://dx.doi.org/10.21741/9781644902813-9.
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Abstract. A new experimental wind tunnel test-bed has been developed for the study of limit cycle oscillations induced by control surface freeplay. Studies of the effects of a single nonlinearity, made possible by the new horizontal tail plane, are described here. Several effects are considered, starting from a reference configuration: the effect of changes in inertia and stiffness, a time-varying gap size, and an aerodynamic preload due to an angle of attack. Both time marching simulations and describing functions analytical methods have been used to understand the experimental measurements and study the capability of the methods to capture the physical behavior. Good agreement was found in all cases and physical insights are gained from the mathematical models. Limitations of the analytical tools are also addressed, focusing on the important difference between the self-excited dynamics of the nonlinear system and its forced response to external excitations.
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Maroufkhani, Aida, Claire Charpentier, Francois Morency, and Gelareh Momen. "Effect of Variable Melting Temperature on the Enthalpy Model for Runway Deicing." In International Conference on Icing of Aircraft, Engines, and Structures. SAE International, 2023. http://dx.doi.org/10.4271/2023-01-1441.
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<div class="section abstract"><div class="htmlview paragraph">One of the most significant challenges for the aviation industry in the winter is the deicing operations on runways. As a result, deicer chemicals can pollute the environment if used in a large amount. A mathematical model could help optimize the use of deicer chemicals. Road deicing models exist to predict pavement temperature covered by snow/ice during deicing operations. However, the specificity of airport operations requires a model for the runway deicing to simulate the mass of ice melted with usage of deicing agents. Here we propose a model for runway deicing and validate it against experimental results. Our model considers temperature, diffusive flux, and time changes in a normal direction. It also calculates the mass and heat transfer in three regions (liquid, mushy, and solid). We used the enthalpy method to determine the temperature and the interface location at each time step. In the liquid and solid, the deicer concentration is obtained by Fick’s law and updated at each time step and location. The melting point temperature is variable due to the dilution of the deicer in the solution. Therefore, melting points are updated depending on the concentration at each location and time. The model uses the phases diagram for water and deicer agent mixture, considering eutectic point, for melting point calculation. The mesh dependency of the model is first investigated. To verify the model sensitivity, the paper proposes parametric studies for the heat transfer coefficient and the diffusion coefficients. Then, to validate the model, the Anti-Icing Materials International Laboratory (AMIL) in Chicoutimi conducted experimental tests on deicer agents for runways. Validation of the model is achieved for potassium acetate and potassium formate, two types of deicers.</div></div>