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Journal articles on the topic 'Aircraft'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Yao, Xinchi. "Differences in large aircraft design between military and civil perspectives." Theoretical and Natural Science 14, no. 1 (2023): 112–16. http://dx.doi.org/10.54254/2753-8818/14/20240908.

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Military transport aircrafts and civil aircrafts are important parts of the aviation field. With the development of aviation technology and the specificity of aircraft functions, the design of military transport aircraft and civil aircraft gradually differs according to application scenarios. However, in the aircraft design, military transport aircrafts and civil aircrafts still have a lot of mutual references. Analyzing the differences between them and the reasons for the differences may contribute to the design and development of military transport aircraft and civil aircraft in the future,

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DUEE, Raphael, Alexis MARTIN, Hugo VASSEUR, and Jean-Frédéric DESJARDINS. "Aircraft automatic detection on Station7hz interface using signal processing and artificial intelligence - ACOUDET - First method." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 270, no. 6 (2024): 5767–75. http://dx.doi.org/10.3397/in_2024_3644.

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The global project is to design a automatic noise event detection and classification system in real time using signal processing and artificial intelligence (AI). The first phase focuses on transport noise (aircrafts, trains, road vehicles, etc.). Secondly, the plan is to extend detection to construction site noise and any natural or life sources. This paper presents the first method developed to detect audible aircrafts pass-by. It focused on the development of a prototype detection algorithm, its results in situ conditions, and insights on future developments to create a robust aircraft and

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Olugbeji, Jemitola P., Okafor E. Gabriel, and Godwin Abbe. "Wing Thickness Optimization for Box Wing Aircraft." Recent Patents on Engineering 14, no. 2 (2020): 242–49. http://dx.doi.org/10.2174/1872212113666190206123755.

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Background: In the interest of improving aircraft performance, studies have highlighted the benefits of Box wing configurations over conventional cantilever aircraft configuration. Generally, the greater an aircraft's average thickness to chord ratio (τ), the lower the structural weight as well as volumetric capacity for fuel. On the other hand, the lower the ., the greater the drag reduction. A review of patents related to the Box-wing aircraft was carried out. While methodologies for optimizing wing thickness of conventional aircrafts have been studied extensively, limited research work exis

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Yao, Dongdong, and Qunli Xia. "Finite-Time Convergence Guidance Law for Hypersonic Morphing Vehicle." Aerospace 11, no. 8 (2024): 680. http://dx.doi.org/10.3390/aerospace11080680.

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Aiming at the interception constraint posed by defensive aircrafts against hypersonic morphing vehicles (HMVs) during the terminal guidance phase, this paper designed a guidance law with the finite-time convergence theory and control allocation methods based on the event-triggered theory, achieving evasion of the defensive aircraft and targeting objectives for a morphing vehicle in the terminal guidance phase. Firstly, this paper established the aircraft motion model; the relative motion relationships between HMV, defensive aircraft, and target; and the control equations for the guidance syste

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

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As flying wing aircraft has no tail and adopts blended-wing-body design, most of flying wing aircrafts are directional unstable. Pitching moment couples seriously with rolling and yawing moment when control surfaces are deflected, bringing insecurity to landing stage. Numerical simulation method and semi-empirical equation estimate method were combined to obtain a high aspect ratio flying wing aircraft’s aerodynamic coefficients. Modeling and simulation of landing stage were established by MATLAB/Simulink. The control coupling effect on lift and drag characteristics and anti-crosswind landing

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Rogalski, Tomasz, and Boguslaw Dołęga. "THE METHOD OF EVALUATION OF THE AIRCRAFT CONTROL SYSTEM." Aviation 9, no. 2 (2005): 29–34. http://dx.doi.org/10.3846/16487788.2005.9635901.

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The dynamical development of general aviation demands compilation of new aircraft control methods. Those methods allow people without special airborne qualifications to pilot these aircrafts. The main goals of such a control system are to reduce a pilot's load, to improve control precision, and to protect an aircraft against dangerous situations. There are many criterions applied to grading and describing an aircraft's flying characteristics and the handling qualities of general aviation airplanes equipped with classical mechanical control systems. But a modern, small, transport aircraft shoul

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Fujita, Etsushi, Taichi Higashioka, Manabu Sugiura, and Osamu Kohashi. "Evaluation method of military aircraft noise using AI analysis of aircraft images." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 6 (2021): 854–62. http://dx.doi.org/10.3397/in-2021-1668.

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In recent aircraft noise survey in Japan, noise data is associated with each aircraft by flight log or by radio information including transponder signals. Especially, above Tokyo metropolitan area, flight tracks are tangled extremely each other, therefore assessments from various perspectives such as departure / arrival airport, used runway, aircraft model, and operator have been demanded for determining noise policies. However, for military aircrafts, it is not easy to identify their information with the same way as commercial aircrafts, because their flight logs are not disclosed and many of

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8

Xie, Naiming. "Estimating civil aircraft’s research and manufacture cost by using grey system model and neural network algorithm." Grey Systems: Theory and Application 5, no. 1 (2015): 89–104. http://dx.doi.org/10.1108/gs-12-2014-0054.

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Purpose – The purpose of this paper is to propose novel civil aircraft cost parameters’ selection method and novel cost estimation approach for civil aircraft so as to effectively simulate or forecast civil aircraft cost under poor information and small sample. Design/methodology/approach – Based on existent cost estimation indexes, this paper summarized civil aircraft research and manufacturing cost impact index system and adopted grey relational model to select most important impact factors. Consider civil aircrafts’ cost information could not be easily collected, the author must estimate th

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

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

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10

Sharma, Vaibhav. "Fanwing Aircraft- Scope as an Agricultural Aircraft." International Journal for Research in Applied Science and Engineering Technology 9, no. VIII (2021): 603–7. http://dx.doi.org/10.22214/ijraset.2021.37436.

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The objective of this paper is to apply the concept of fan wing to agricultural aircrafts which are conventionally fixed wings aircrafts or multi-rotor drones. Fan wing is capable of producing good amount of lift at a sufficiently low speed without stalling, thus is apt for agricultural processes of irrigation, spraying pesticides, etc. Fan wing has a special ability that it doesn’t stalls (for the practical range of AOA), making this spraying method reliable. A fanwing aircraft is modelled using CATIA V5 and the flow visualizations for the same are performed on the ANSYS. This aircraft is the

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11

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

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

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Idres, Moumen. "Assessment of the Range of an Electric Aircraft." Journal of Advanced Research in Applied Sciences and Engineering Technology 50, no. 2 (2024): 155–70. http://dx.doi.org/10.37934/araset.50.2.155170.

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Electrification of aircraft is a rapidly developing area of the aerospace industry. Thus, there are many electric aircrafts in development, testing, or production. Electric aircrafts are currently viable for short range and short time flight missions due to battery-specific energy limitations. Hence, training and commuter aircrafts are feasible targets for electrification. Pipistrel Velis Electro is the world's first certified crewed electric aircraft for pilot training. In this work, Pipistrel Velis Electro aircraft range is evaluated based on solution of longitudinal equations of motion. A s

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13

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

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

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Zhaohui, Ming, Zhang Ming, Tang Xinmin, and Han Song-Chen. "Structural Modelling and Deceleration Algorithm for a Follow Aircraft on Performance-Based Navigation Airway Based on Multi-Agent Technique." Cybernetics and Information Technologies 15, no. 6 (2015): 46–56. http://dx.doi.org/10.1515/cait-2015-0066.

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Abstract Considering the operation characteristics of the high-speed PBN airway, we propose an aircraft agent structural model and a basic algorithm flow of decision-making by Multi-agent technique. According to the constraint of safe separation and speed with the aircrafts, making use of the car-following theory, the deceleration constraint model is built for a flight management system. When the front aircraft decelerates, the model can offer a speed adjustment proposal for the following aircraft. The model is built based on the minimal safe separation and speed interval constraint; each vari

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15

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

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

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Yadav, Bharosh Kumar, Ramhit Yadav, and K. Sudhakar. "Stress Distribution Analysis using ANSYS of the Nose Landing Gear of STOL Aircrafts Considering Runway Gradient: A Simulation Study." Orchid Academia Siraha 2, no. 1 (2023): 1–20. http://dx.doi.org/10.3126/oas.v2i1.65618.

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Landing gear failures are a major cause of aircraft failures because they are an integral part of the aircraft's development. According to the Federal Aviation Administration (FAA), 50% of all aircraft failures occur during take-offs and landing. The landing gear of a short take-offs and landing (STOL) aircraft has had its static and dynamic forces analyzed analytically and numerically. SOLIWORKS is used to model the landing gear, and ANSYS is used to perform the numerical simulation results. Following it, the model is examined for stress and deformation with the boundary conditions and comput

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17

Qin, Derek Xiao. "Vertical takeoff and landing aircraft: Categories, applications, and technology." Theoretical and Natural Science 13, no. 1 (2023): 126–29. http://dx.doi.org/10.54254/2753-8818/13/20240810.

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A Vertical Take-Off and Landing (VTOL) aircraft is an aircraft with the ability to take off and land vertically. The ability of removing the need for a runway allows VTOL aircraft to be used for applications that standard aircraft cannot be used for. These applications include military, firefighting, and transportation applications. For the purposes of this paper, helicopters will be considered to be VTOL aircraft, as they fit the general criteria and are among the first to be widely used. VTOL aircraft can be split into several categories, including hybrid VTOL aircraft, VTOL Unmanned Aerial

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18

Li, Jun, Wei Yang, and Yang Pei. "Vulnerability Assessment for Fire and Explosion Suppression Measures of Aircraft Fuel System." Advanced Materials Research 510 (April 2012): 64–69. http://dx.doi.org/10.4028/www.scientific.net/amr.510.64.

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Fuel system is the most vulnerable system on fixed wing aircraft. When penetrated by threat propagators, it is liable to be damaged by combustion and explosion. Thus, fire/explosion suppression for fuel system are important measures to improve the aircrafts survivability. In this paper, the whole aircraft vulnerability model which consists of aircraft configuration, structure, and systems is constructed by CATIA software, the basic steps for vulnerability quantitative computation are descried, and the computing formulas of three kill modes are presented. The vulnerability of one aircraft befor

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19

Zhang, Yuhang, Hao Sun, Jiawei Zuo, Hongqi Wang, Guangluan Xu, and Xian Sun. "Aircraft Type Recognition in Remote Sensing Images Based on Feature Learning with Conditional Generative Adversarial Networks." Remote Sensing 10, no. 7 (2018): 1123. http://dx.doi.org/10.3390/rs10071123.

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Aircraft type recognition plays an important role in remote sensing image interpretation. Traditional methods suffer from bad generalization performance, while deep learning methods require large amounts of data with type labels, which are quite expensive and time-consuming to obtain. To overcome the aforementioned problems, in this paper, we propose an aircraft type recognition framework based on conditional generative adversarial networks (GANs). First, we design a new method to precisely detect aircrafts’ keypoints, which are used to generate aircraft masks and locate the positions of the a

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20

Sun, Ji Ku, Zong Jie Cao, De Jian Sun, and Yi Chen. "Characteristic of Corrosive Damages about Aircraft Structures in Service." Applied Mechanics and Materials 543-547 (March 2014): 316–19. http://dx.doi.org/10.4028/www.scientific.net/amm.543-547.316.

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In engineering practices, aircraft structures have been damaged due to the structural corrosion, the corrosive problem of aircrafts needs to call high attentions for researchers because aircraft structures are composed of metals and compound metals. In this paper, corrosion problems and structural reliability of aircraft structures are discussed. Corrosion morphology and mechanism of aircraft structures are analyzed based on metal corrosion theory. The characteristics of the various types of corrosions of aircraft structures have been enumerated. The effect of environments in corrosion process

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21

Shao, Haoyuan, Daochun Li, Zi Kan, Shiwei Zhao, Jinwu Xiang, and Chunsheng Wang. "Analysis of Catapult-Assisted Takeoff of Carrier-Based Aircraft Based on Finite Element Method and Multibody Dynamics Coupling Method." Aerospace 10, no. 12 (2023): 1005. http://dx.doi.org/10.3390/aerospace10121005.

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Catapult-assisted takeoff is the initiation of flight missions for carrier-based aircrafts. Ensuring the safety of aircrafts during catapult-assisted takeoff requires a thorough analysis of their motion characteristics. In this paper, a rigid–flexible coupling model using the Finite Element Method and Multibody Dynamics (FEM-MBD) approach is developed to simulate the aircraft catapult process. This model encompasses the aircraft frame, landing gear, carrier deck, and catapult launch system. Firstly, reasonable assumptions were made for the dynamic modeling of catapult-assisted takeoff. An enha

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Fang, Jie, and Hong Shan Xia. "Aircraft Dynamic Scheduling Algorithm Research Based on Heuristic Column Generation Algorithm." Applied Mechanics and Materials 411-414 (September 2013): 2364–68. http://dx.doi.org/10.4028/www.scientific.net/amm.411-414.2364.

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Aircraft dynamic scheduling affects the operation efficiency and flight benefits. Airlines make a rational organization of surplus aircraft to generate the best scheduling solution. The present research constructs an aircraft dynamic scheduling network diagram, define the surplus aircrafts available routings and create aircraft dynamic scheduling mathematical model. Through a mixture column generation algorithm with heuristic methods, the research find the routings in the optimal aircraft dynamic scheduling program. The given instance verifies the model and algorithm generate reasonable and pr

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23

Kwiek, Agnieszka. "Conceptual design of an aircraft for Mars mission." Aircraft Engineering and Aerospace Technology 91, no. 6 (2019): 886–92. http://dx.doi.org/10.1108/aeat-08-2018-0231.

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Purpose The purpose of this paper is to present the results of a conceptual design of Martian aircraft. This study focuses on the aerodynamic and longitudinal dynamic stability analysis. The main research questions are as follows: Does a tailless aircraft configuration can be used for Martian aircraft? How to the short period characteristic can be improved by side plates modification? Design/methodology/approach Because of a conceptual design stage of this Martian aircraft, aerodynamic characterises were computed by the Panukl package by using the potential flow model. The longitudinal dynamic

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Zhu, Hongchang. "History and Future Development of Morphing-Wing Aircrafts." Theoretical and Natural Science 86, no. 1 (2025): 120–25. https://doi.org/10.54254/2753-8818/2025.20190.

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Morphing-wing aircraft can alter the shape of their wings to achieve different flight performances. Such changes are made to achieve the optimum aerodynamic profile for the current flight environment. The morphing wings greatly improve the flight efficiency and reduces the energy loss in different environments. Morphing designs can be categorized into three distinct types based on their fundamental mechanisms: rotation of specific segments or the entire wing, telescoping, and inflation of particular components or the entire wing. With the continuous technological innovation and practical appli

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Shi, Qiongyan, and Jianghua Zhang. "Mechanical Structure Design of the Aircraft ASD Control Isolation Control." Journal of Applied Mathematics 2022 (November 16, 2022): 1–16. http://dx.doi.org/10.1155/2022/8306216.

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Aircraft control system is of key importance for flight attitude control of aircrafts. Its normal function directly determines whether the aircraft flies safely, flight delay, and dispatch reliability. Therefore, this paper designs the mechanical structure of the aircraft ASD control isolation control. Firstly, the mechanical control principle of the driving rod system is analyzed, and the isolation mechanism of pitch and roll control is designed; secondly, the control lines are classified, the transmission characteristic requirements of the aircraft control isolation system are given, the tra

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26

Wang, Zhipeng, Zhiqin Qian, Ziye Song, Hongzhou Liu, Wenjun Zhang, and Zhuming Bi. "Instrumentation and self-repairing control for resilient multi-rotor aircrafts." Industrial Robot: An International Journal 45, no. 5 (2018): 647–56. http://dx.doi.org/10.1108/ir-03-2018-0053.

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Purpose Even though multi-rotor aircrafts are becoming more and more prevalent in the fields of aerial photography, agricultural spraying, disaster searching and rescuing, how to achieve higher reliability and robustness of an aircraft still poses a big challenge. It is not a rare case that a multi-rotor aircraft is severely damaged or crushed when an actuator or sensor is malfunctioned. This paper aims at the resilience of an aircraft when a rotor is malfunctioned. Design/methodology/approach The reliability of a multi-rotor aircraft can be measured in terms of stability, robustness, resilien

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Kim, Min-Seong, Byung Hyuk Kwon, and Tae-Young Goo. "Comparisons between Mean and Turbulent Parameters of Aircraft-Based and Ship-Based Measurements in the Marine Atmospheric Boundary Layer." Atmosphere 12, no. 9 (2021): 1088. http://dx.doi.org/10.3390/atmos12091088.

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The Structure des Echanges Mer-Atmosphère, Propriétés Océaniques/ Recherche Expérimentale (SEMAPHORE) experiment was conducted over the oceanic Azores current located in the Azores Basin. The evolution of the marine atmospheric boundary layer (MABL) was studied based on the evaluation of mean and turbulent data using in situ measurements by a ship and two aircrafts. The sea surface temperature (SST) field was characterized by a gradient of approximately 1 °C/100 km. The SST measured by aircraft decreased at a ratio of 0.25 °C/100 m of altitude due to the divergence of the infrared radiation fl

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Liu, Ruiwei, Siqi Hao, Yaping Zhang, Chonghang Xu, Wenjing Li, and Yunrui Mo. "A Novel Strategic Aircraft Track Planning Method Considering Conflict Probability." Aerospace 9, no. 12 (2022): 848. http://dx.doi.org/10.3390/aerospace9120848.

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Generally, air track planning is conducted in real time and takes modified track distance minimization as objective. Next-generation air transport systems provide aircrafts with more flexibility in track planning and more responsibilities in self-separation, which present a great challenge for aircraft optimal track planning, especially in some high-density airspaces and some complex conflict scenarios. This paper proposes a novel aircraft track planning method by taking aircraft conflict probability into consideration. First, the concepts of aircraft potential motion space and the estimation

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Kartyshev, Mikhail. "Ecoflight Monitoring - new aircraft noise monitoring system with neural network-based data filtering." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 268, no. 8 (2023): 511–16. http://dx.doi.org/10.3397/in_2023_0088.

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Reliable measurements and further evaluation of noise environment in the field, as well as refinement of an airfield noise zone are directly impacted by the completeness and accuracy of registered individual noise events created by aircrafts flying near monitoring locations. Also, monitoring stations are often located in densely-populated areas that feature other noise sources. Detecting aircraft flight events becomes even more complicated when there is no location data for aircrafts that lack ADS-B transponders. The Moscow region, where most aircraft noise monitoring projects are run, is uniq

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Tang, Hong, Guo Guang Chen, and Hui Zhu He. "Optimization Design and Numerical Simulation for Aerodynamics Shape of an Aircraft." Applied Mechanics and Materials 215-216 (November 2012): 275–78. http://dx.doi.org/10.4028/www.scientific.net/amm.215-216.275.

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Considering safety and reliability of interface between aircraft and artillery, aircraft need of increasing space of shell bands, but its range decreased by flight experimental results. It is enough to numerically simulate and calculate to aerodynamics of two projects (namely aircraft increased spacing bands vs. archetype aircraft) model in this paper. The simulation results show that big space of shell bands affect aircraft body’s coefficient of drag, and keep to flight experimental results. In keeping to big spacing bands at the same time, it is put forward optimization scheme that aircraft

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Reddy, D. Ramana, M. V. Aditya Nag, and M. S. N. Gupta. "Stress and Deformation Analysis of Aircraft's Fuel Tank under Different Inertia Load Cases in Addition to a Static Test Pressure Using FEA." Advanced Materials Research 1115 (July 2015): 527–30. http://dx.doi.org/10.4028/www.scientific.net/amr.1115.527.

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In the modern era the aerospace technology plays a very significant role in the development of the mankind. The evolution of the light weight aircraft has a special focus in the present industrial trends. Several research organizations are in the process of developing Light Weight Aircraft, which is ideally suited for civil transport, aerial survey, training etc. This Light Weight Aircrafts are to be designed accordance to Federal Aviation Regulations part 23 (FAR-23). This paper deals with the analysis of the Aircraft's Fuel Tank under variable conditions. The analysis of aircraft fuel tank i

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Cui, Xingda, Yonggang Yu, Shuai Ma, Zhongyun Xiao, Lu Zhang, and Fang Liu. "Numerical investigation of the aerodynamic interference in 2-aircraft formation flight." Journal of Physics: Conference Series 2280, no. 1 (2022): 012017. http://dx.doi.org/10.1088/1742-6596/2280/1/012017.

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Abstract Due to obvious reduction in drag, formation flight attracts wide attention of major powers in the world. Based on wild geese flying in a ‘V’ formation, a formation composed of two flying-wing aircrafts is designed. The aerodynamic interference in 2-aircraft formation flight is studied by CFD. Results show that 2-aircraft formation flight has little impact on leading aircraft, but has an evident impact on following aircraft. At the same AoA, the effect of increment in lift and reduction in drag of following aircraft is large. As considering the balance of gravity and lift, the reductio

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Cui, Xingda, Yonggang Yu, Shuai Ma, Zhongyun Xiao, Lu Zhang, and Fang Liu. "Numerical investigation of the aerodynamic interference in 2-aircraft formation flight." Journal of Physics: Conference Series 2280, no. 1 (2022): 012017. http://dx.doi.org/10.1088/1742-6596/2280/1/012017.

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Abstract Due to obvious reduction in drag, formation flight attracts wide attention of major powers in the world. Based on wild geese flying in a ‘V’ formation, a formation composed of two flying-wing aircrafts is designed. The aerodynamic interference in 2-aircraft formation flight is studied by CFD. Results show that 2-aircraft formation flight has little impact on leading aircraft, but has an evident impact on following aircraft. At the same AoA, the effect of increment in lift and reduction in drag of following aircraft is large. As considering the balance of gravity and lift, the reductio

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Wang, X., H. Yu, and D. Feng. "Pose estimation in runway end safety area using geometry structure features." Aeronautical Journal 120, no. 1226 (2016): 675–91. http://dx.doi.org/10.1017/aer.2016.16.

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ABSTRACTA novel image-based method is presented in this paper to estimate the poses of commercial aircrafts in a runway end safety area. Based on the fact that similar poses of an aircraft will have similar geometry structures, this method first extracts features to describe the structure of an aircraft's fuselage and aerofoil by RANdom Sample Consensus algorithm (RANSAC), and then uses the central moments to obtain the aircrafts’ pose information. Based on the proposed pose information, a two-step feature matching strategy is further designed to identify an aircraft's particular pose. In orde

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Chenguang, Yang, Liu Hu, and Gao Yuan. "Load Planning of Transport Aircraft Based on Hybrid Genetic Algorithm." MATEC Web of Conferences 179 (2018): 01007. http://dx.doi.org/10.1051/matecconf/201817901007.

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Loading of transport aircraft attracts much attention as the airlift is developing rapidly. It refers to the process that various cargoes are loaded, in an appropriate manner, into kinds of transport aircrafts with constraints of volume, weight and gravity center. Based on two-dimensional bin packing with genetic algorithm (GA), a new hybrid algorithm is proposed to solve the multi-constraint loading problem of transport aircraft for seeking the minimum of fuel consumption. Heuristic algorithm is applied to optimize single-aircraft loading in GA decoding, and the procedure of hybrid GA is summ

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BOIKO, Sergey, Alona HEBDA, Yurii STUSHCHANSKY, Serhiy GOLOVANOV, and Myhailo RUZHUK. "APPROACH TO THE IMPROVEMENT OF THE CONTROL SYSTEM OF THE ELECTRIC POWER PLANT OF THE AIRCRAFT." Herald of Khmelnytskyi National University. Technical sciences 315, no. 6 (2022): 20–24. http://dx.doi.org/10.31891/2307-5732-2022-315-6(2)-20-24.

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The paper proposes an approach to improving the adaptive system of aircraft with an electric propulsion system. Modern aircraft are inextricably linked with electronics that ensure the functioning of the entire air transport system. Modern aircraft avionics is a complex of hardware and software that is part of the automatic control system of the aircraft and functionally combines the glider with the drive of the executive body. One of the main functions of modern avionics is the automation of aircraft control processes, which aims to ensure the proper execution of a safe flight with the smalle

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Zhang, X., B. Xiong, and G. Kuang. "AIRCRAFT SEGMENTATION IN SAR IMAGES BASED ON IMPROVED ACTIVE SHAPE MODEL." ISPRS - International Archives of the Photogrammetry, Remote Sensing and Spatial Information Sciences XLII-3 (April 30, 2018): 2331–35. http://dx.doi.org/10.5194/isprs-archives-xlii-3-2331-2018.

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In SAR image interpretation, aircrafts are the important targets arousing much attention. However, it is far from easy to segment an aircraft from the background completely and precisely in SAR images. Because of the complex structure, different kinds of electromagnetic scattering take place on the aircraft surfaces. As a result, aircraft targets usually appear to be inhomogeneous and disconnected. It is a good idea to extract an aircraft target by the active shape model (ASM), since combination of the geometric information controls variations of the shape during the contour evolution. However

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Kalinowski, Miłosz. "Aero-Structural Optimization of Joined-Wing Aircraft." Transactions on Aerospace Research 2017, no. 4 (2017): 48–63. http://dx.doi.org/10.2478/tar-2017-0028.

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Abstract Joined-wing aircraft due to its energy characteristics is a suitable configuration for electric aircraft when designed properly. However, because of the specific for this aircraft phenomenons (e.g. static indeterminacy of structure, aerodynamic interference of lifting surfaces) it demands more complicated methods to model its behavior than a traditional aircraft configurations. For these reasons the aero-structural optimization process is proposed for joined-wing aircrafts that is suitable for preliminary design. The process is a global search, modular algorithm based on automatic geo

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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 turn

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Song, Shuang. "Study on development of aircraft design theory." Theoretical and Natural Science 13, no. 1 (2023): 45–50. http://dx.doi.org/10.54254/2753-8818/13/20240772.

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Nowadays, the aircraft has become a very important part of human life. The invention of the aircraft is a shining point in human civilization. During the development of aircraft, there have been significant changes in aircrafts appearance, power systems, design theories, and applications. In order to provide a clearer understanding of the development process of aircraft and lay the groundwork for future development of the aircraft, this article reviews the three important stages in the development of aircraft and elaborates on the development of aircraft from the perspectives of structural cha

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A., Armaan, and Srinivas G. "In Tune with Times: Recent Developments in Theoretical, Experimental and Numerical techniques of Aircraft Engines." International Journal of Engineering & Technology 7, no. 2 (2018): 805. http://dx.doi.org/10.14419/ijet.v7i2.10910.

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Today the aircraft engine designing and development work is increasing drastically. Especially aircraft engines play a vital role in order to decide the aircrafts speed and its performance. Broadly turbojet, turboprop, turbo shaft and turbofan engines comes under the category of air breathing engines. Every engine has its own purpose and application. But modern aircrafts require much more advancements. Designing a new aircraft engine has been a really challenging task to the researchers. But giving a complete holistic view of aircraft engines and research gap would definitely help a lot to the

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YANG, Jie, Jun ZHAN, Zhixiang CHEN, Xianyi LIU, Zhiqing ZHOU, and Zhi LI. "Optimization method of ballistic blast fragmentation warhead striking aircraft in aircraft shelter." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 41, no. 1 (2023): 115–24. http://dx.doi.org/10.1051/jnwpu/20234110115.

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For evaluating the economy and feasibility about blast fragmentation warhead striking aircraft in aircraft shelter, taking a typical aircraft and single/double aircraft shelter as study objects, based on the thought of simple/quadratic surface fitting, the 3D surface models of aircraft and shelter are built. According to the velocity and position model of fragment, combined with the transformation relationship of coordinate system, the missile-target encounter algorithm is given. The ruin tree model of aircraft is constructed to calculate the ruin probability algorithm of aircraft. For reducin

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Zhang, Yongjie, Kang Cao, Ke Liang, and Yongqi Zeng. "Study on the evaluation model of serialized civil aircraft commonality index based on fuzzy set theory." Journal of Intelligent & Fuzzy Systems 40, no. 6 (2021): 11539–58. http://dx.doi.org/10.3233/jifs-202749.

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Commonality, a typical commercial feature of serialized civil aircraft study and development, refers to a series of methods of reusing and sharing assets, which were developed based on broad similarity. The common design of serialized civil aircraft is capable of maximally saving R&D, production, operation, and disposal. To maximize the total benefits of manufacturers and operators, the common design of serialized civil aircrafts primarily exploits the commercial experience of serialized products in other fields (e.g., automobiles and mobile phones), whereas a scientific index system and q

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Fu, Yueshuai, and Huimin Fu. "A Novel Individual Aircraft Life Monitoring Method Based on Reliable Life Consumption Assessment." Machines 11, no. 11 (2023): 1016. http://dx.doi.org/10.3390/machines11111016.

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Individual life monitoring is crucial for ensuring aircraft flight safety. Conventional life-consumption-based monitoring methods ignore reliability, thus disjoining them from the aircraft’s reliable life determination and extension, where high confidence and reliability are required. Therefore, this paper proposes a reliable life consumption and individual life monitoring method for aircraft structure fatigue. In the paper, the P-S-N curve, i.e., the relationship between the aircraft structure’s life (N) and fatigue load (S) under a certain probability (P), is established, by which the lower

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Wu, Jiang, Feng Gao, Shengwen Li, and Fengtian Yang. "Conceptual Design and Optimization of Distributed Electric Propulsion General Aviation Aircraft." Aerospace 10, no. 5 (2023): 387. http://dx.doi.org/10.3390/aerospace10050387.

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The interaction between the slipstream of the propellers and the wing of an aircraft with distributed electric propulsion (DEP) could benefit aerodynamics. A conceptual design and optimization are carried out in order to increase the range of an electric general aviation aircraft without affecting its takeoff and landing velocity in the same fuselage condition. Propellers are modelled using the actuator disk (AD) theory, and the aircraft is modelled using the vortex lattice method (VLM) to obtain DEP aircraft’s aerodynamics in conceptual design. The DIRECT method is used for global optimizatio

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Lin, Fusheng, and Guang Meng. "Study on the Dynamics of a Rotor in a Maneuvering Aircraft." Journal of Vibration and Acoustics 125, no. 3 (2003): 324–27. http://dx.doi.org/10.1115/1.1576422.

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This paper shows how the dynamics of a rotor in a maneuvering aircraft changes according to the operation of the aircraft. The mathematical model of an unbalanced rotor system located in the maneuvering aircraft is derived. The dynamic characteristics of the rotor running at a constant angular speed or a constant acceleration are studied under the assumptions that the aircraft maneuvers only in a vertical plane and that the pitching angle and the flight path inclination of the aircraft are equal. The effects of gravity and unbalance parameter are considered. The results show that the unbalance

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Haryono, Aloysius Sigit, and Hadi Sutanto. "Aircraft Age Limitation versus Three Indonesian Fatal Air Accidents in HFCAS Perspective." Jurnal Praktik Keinsinyuran 1, no. 1 (2024): 1–10. http://dx.doi.org/10.25170/jpk.v1i1.5859.

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An aircraft deemed to be airworthy, not limited by aircraft age but by well maintenance and by the operation of the aircraft. The investigation by KNKT between 2014 -2021 found no statement related of aircraft aging like material fatique or other phrases. The latent errors started with repetitive failures which were not solved as early as possible. Three fatal accidents involved aircrafts with age of 27, 6 and 1 year old, all below the Minister Regulation No. 160 (2015) which stated maximum age was 30 years. The cancelation of Minister Regulation No. 027 (2020) is the correct decision from Ind

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Nezenko, Andriy, and Sergiy Kozlov. "METHOD FOR DETERMINING GEOMETRICAL PARAMETERS OF THE AIRCRAFT LANDING GEAR WHEELS POSITION." APPLIED GEOMETRY AND ENGINEERING GRAPHICS, no. 105 (February 2, 2024): 123–33. https://doi.org/10.32347/0131-579x.2023.105.123-133.

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The article addresses the issue of the actual geometric parameters’ compliance monitoring of a manufactured aircraft chassis wheel position with the parameters assumed at the product design stages. Typically, when investigating the actual geometric parameters of the aircraft, primary attention is given to airframe parameters, which determine the flight characteristics of the product. Nevertheless, chassis parameters receive considerably less attention, although deviations of the manufactured product's chassis geometric parameters from the design ones can significantly affect the controllabilit

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Huang, Wei, Wen Jun Wang, Fu Li Bai, and Xiang Hui Zhang. "Study on Optimization of Multi-Type Aircraft Scheduling Robust Model." Applied Mechanics and Materials 40-41 (November 2010): 347–53. http://dx.doi.org/10.4028/www.scientific.net/amm.40-41.347.

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Phased implementation approach, namely three models: aircraft type distribution model, aircraft scheduling model, robustness model is used to achieve the optimization of aircraft scheduling robustness. Aircraft type distribution model is established to obtain the best model of each leg; then fleet scheduling model is established to determine specified type in the implementation of the specific aircrafts for each flight, flight strings, which meet the constraints, are obtained by solving; finally, the flight robustness model is established, that is, flight string with minimal impact is selected

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Luo, Sai. "Discussion on Continuous Airworthiness and Maintenance of Civil Aircraft." Journal of Electronic Research and Application 6, no. 1 (2022): 1–4. http://dx.doi.org/10.26689/jera.v6i1.2804.

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With China’s rapid economic development, the civil aviation market’s development area has expanded. On this basis, the state has proposed more extensive and stringent civil aviation rules. Many factors can affect the civil aircraft during the real operation process, and this can have an impact on the aircraft’s regular functioning to some level. To ensure that civil aircraft remain airworthy, appropriate maintenance work must be performed on a regular basis to prevent compromising the aircraft’s safety performance. For the purpose of reference, this paper discusses the continual airworthiness

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