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Artykuły w czasopismach na temat „Aircraft”
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1
Yao, Xinchi. "Differences in large aircraft design between military and civil perspectives". Theoretical and Natural Science 14, nr 1 (30.11.2023): 112–16. http://dx.doi.org/10.54254/2753-8818/14/20240908.
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Military transport aircrafts and civil aircrafts are important parts of the aviation field. With the development of aviation technology and the specificity of aircraft functions, the design of military transport aircraft and civil aircraft gradually differs according to application scenarios. However, in the aircraft design, military transport aircrafts and civil aircrafts still have a lot of mutual references. Analyzing the differences between them and the reasons for the differences may contribute to the design and development of military transport aircraft and civil aircraft in the future, and provide reference suggestions for the design of civil aircraft in the context of the civil-military integration. In this article, the application scenarios and functions of military transport aircraft and civil aircraft are analyzed, as well as the special situation of civil aircraft research and development. This article may offer a reference for the future research and development of military transport aircraft and civil aircraft.
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Olugbeji, Jemitola P., Okafor E. Gabriel i Godwin Abbe. "Wing Thickness Optimization for Box Wing Aircraft". Recent Patents on Engineering 14, nr 2 (29.10.2020): 242–49. http://dx.doi.org/10.2174/1872212113666190206123755.
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Background: In the interest of improving aircraft performance, studies have highlighted the benefits of Box wing configurations over conventional cantilever aircraft configuration. Generally, the greater an aircraft's average thickness to chord ratio (τ), the lower the structural weight as well as volumetric capacity for fuel. On the other hand, the lower the ., the greater the drag reduction. A review of patents related to the Box-wing aircraft was carried out. While methodologies for optimizing wing thickness of conventional aircrafts have been studied extensively, limited research work exist on the methodology for optimizing the wing thickness to chord ratio of the Box wing aircraft configurations. Methods: To address this gap, in this work, a two stage optimization methodology based on gradient search algorithm and regression analysis was implemented for the optimization of Box wing aircrafts wing thickness to chord ratio. The first stage involved optimizing the All Up Mass (AUM), Direct Operating Cost (DOC) and Zero Lift Drag Coefficients (CDO), with respect to the aft and fore sweep angle for some selected τ values. At the second stage, a suitability function (γ) was optimized with respect to the aft and fore sweep angle for some selected τ values. A comparative study was further carried out using the proposed methodology on similar size cantilever wing aircraft. Results: From the result, an optimal τ value was reached. Also the τ value for the cantilever aircraft found based on the proposed methodology was similar to the true τ value of the adopted aircraft, thereby validating the methodology. Conclusion: Based on the optimal τ value reached from this work, the Box wing aircraft are suitable for thin airfoils.
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Yao, Dongdong, i Qunli Xia. "Finite-Time Convergence Guidance Law for Hypersonic Morphing Vehicle". Aerospace 11, nr 8 (18.08.2024): 680. http://dx.doi.org/10.3390/aerospace11080680.
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Aiming at the interception constraint posed by defensive aircrafts against hypersonic morphing vehicles (HMVs) during the terminal guidance phase, this paper designed a guidance law with the finite-time convergence theory and control allocation methods based on the event-triggered theory, achieving evasion of the defensive aircraft and targeting objectives for a morphing vehicle in the terminal guidance phase. Firstly, this paper established the aircraft motion model; the relative motion relationships between HMV, defensive aircraft, and target; and the control equations for the guidance system. Secondly, a guidance law with finite-time convergence was designed, establishing a controller with the angle between the aircraft–target–defense aircraft triplet as the state variable and lift as the control variable. By ensuring the angle was non-zero, the aircraft maintained a certain relative distance from the defense aircraft, achieving evasion of interception. The delay characteristic of the aircraft’s flight controller was considered, analyzing its delay stability and applying control compensation. Thirdly, a multi-model switching control allocation method based on an event-triggered mechanism was designed. Optimal attack and bank angles were determined based on acceleration control variables, considering different sweep angles. Finally, simulations were conducted to validate the effectiveness and robustness of the designed guidance laws.
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Hong, Wei Jiang, i Dong Li Ma. "Influence of Control Coupling Effect on Landing Performance of Flying Wing Aircraft". Applied Mechanics and Materials 829 (marzec 2016): 110–17. http://dx.doi.org/10.4028/www.scientific.net/amm.829.110.
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As flying wing aircraft has no tail and adopts blended-wing-body design, most of flying wing aircrafts are directional unstable. Pitching moment couples seriously with rolling and yawing moment when control surfaces are deflected, bringing insecurity to landing stage. Numerical simulation method and semi-empirical equation estimate method were combined to obtain a high aspect ratio flying wing aircraft’s aerodynamic coefficients. Modeling and simulation of landing stage were established by MATLAB/Simulink. The control coupling effect on lift and drag characteristics and anti-crosswind landing capability was studied. The calculation results show that when the high aspect ratio flying wing aircraft was falling into the deceleration phase, appropriate to increase the opening angle of split drag rudder can reduce the trimming pitching moment deflection of pitch flap, thereby reduce the loss of lift caused by the deflection of pitch flaps. Flying wing aircraft can be rounded out successfully by using the pitch flap gently and steady. Both side-slip method and crabbed method can be applied to the landing of high aspect ratio flying wing aircraft in crosswind, the flying wing aircraft’s anti-crosswind landing capability was weakened by the control coupling effect of split drag rudder and elevon. Sideslip method was recommended in the crosswind landing of flying wing aircraft after calculation and analysis.
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Fujita, Etsushi, Taichi Higashioka, Manabu Sugiura i Osamu Kohashi. "Evaluation method of military aircraft noise using AI analysis of aircraft images". INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, nr 6 (1.08.2021): 854–62. http://dx.doi.org/10.3397/in-2021-1668.
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In recent aircraft noise survey in Japan, noise data is associated with each aircraft by flight log or by radio information including transponder signals. Especially, above Tokyo metropolitan area, flight tracks are tangled extremely each other, therefore assessments from various perspectives such as departure / arrival airport, used runway, aircraft model, and operator have been demanded for determining noise policies. However, for military aircrafts, it is not easy to identify their information with the same way as commercial aircrafts, because their flight logs are not disclosed and many of them do not emit transponder signals like commercial aircrafts. Therefore, manned 24 hours survey around air bases have been necessary to obtain flight information of military aircrafts. In this paper, we propose an AI-based analysis using captured aircraft images for obtaining actual flight data of military aircrafts. In the past trials, we could determine the takeoff/landing time and the aircraft model by the above method. Associating these information and noise data measured at monitoring stations, details of noise characteristics around the air base can be clearly grasped. Advanced analysis of the causes of noise impact will lead effective and concrete countermeasures.
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Rogalski, Tomasz, i Boguslaw Dołęga. "THE METHOD OF EVALUATION OF THE AIRCRAFT CONTROL SYSTEM". Aviation 9, nr 2 (30.06.2005): 29–34. http://dx.doi.org/10.3846/16487788.2005.9635901.
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The dynamical development of general aviation demands compilation of new aircraft control methods. Those methods allow people without special airborne qualifications to pilot these aircrafts. The main goals of such a control system are to reduce a pilot's load, to improve control precision, and to protect an aircraft against dangerous situations. There are many criterions applied to grading and describing an aircraft's flying characteristics and the handling qualities of general aviation airplanes equipped with classical mechanical control systems. But a modern, small, transport aircraft should be equipped with fly‐by‐wire control systems, and there are no clear, straight, rules rate and describe the handling qualities of small airplanes with fly‐by‐wire control systems. This paper presents a methodology created by the authors that classifies and compares the handling qualities of general aviation aircraft equipped with fly‐by‐wire control systems. It takes into consideration two parameters: pilot's effort during realization of ordered tasks and precision of his control.
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Xie, Naiming. "Estimating civil aircraft’s research and manufacture cost by using grey system model and neural network algorithm". Grey Systems: Theory and Application 5, nr 1 (2.02.2015): 89–104. http://dx.doi.org/10.1108/gs-12-2014-0054.
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Purpose – The purpose of this paper is to propose novel civil aircraft cost parameters’ selection method and novel cost estimation approach for civil aircraft so as to effectively simulate or forecast civil aircraft cost under poor information and small sample. Design/methodology/approach – Based on existent cost estimation indexes, this paper summarized civil aircraft research and manufacturing cost impact index system and adopted grey relational model to select most important impact factors. Consider civil aircrafts’ cost information could not be easily collected, the author must estimate their costs with limited sample and poor information. A combination model of GM (0, N) model and BP neural network algorithm is proposed. Both advantages of simulation of BP neural network algorithm and poor information generation of GM (0, N) were effectively combined. Then steps of combined model were given out. Finally, nine types of aircrafts were used to test the validity of proposed model. As comparing with the traditional multiple linear regression model and simple GM (0, N) model, results indicated that proposed model can do the work better. Findings – Grey relational model can be applied for parameters’ selection and combined GM (0, N) model and BP neural network algorithm can estimate aircraft’s cost as well. Results show that novel combined model could get high forecasting accuracy. Practical implications – Cost estimation is key problem in production management of civil aircraft. Effective cost management could promote competitiveness of aircraft manufacturing company. Proposed combined model can be applied for civil aircraft cost estimation. Similarly, it could be applied for other complex equipment cost estimation. Originality/value – The paper succeeds in proposing grey relational model for cost parameters’ selection and constructing a combination model of GM (0, N) model and BP neural network algorithm. Algorithm of the proposed model was discussed and steps were given out.
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Sharma, Vaibhav. "Fanwing Aircraft- Scope as an Agricultural Aircraft". International Journal for Research in Applied Science and Engineering Technology 9, nr VIII (15.08.2021): 603–7. http://dx.doi.org/10.22214/ijraset.2021.37436.
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The objective of this paper is to apply the concept of fan wing to agricultural aircrafts which are conventionally fixed wings aircrafts or multi-rotor drones. Fan wing is capable of producing good amount of lift at a sufficiently low speed without stalling, thus is apt for agricultural processes of irrigation, spraying pesticides, etc. Fan wing has a special ability that it doesn’t stalls (for the practical range of AOA), making this spraying method reliable. A fanwing aircraft is modelled using CATIA V5 and the flow visualizations for the same are performed on the ANSYS. This aircraft is then compared with three different existing agricultural aircrafts on different parameters, namely payload capacity, work efficiency and ease of operation. The comparison shows that such fanwing vehicle is a good substitute over the conventional fixed wings and multi-rotor drones.
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Wang, Hong Yong, Rui Ying Wen i Yi Fei Zhao. "Empirical Research on Topological Characteristics of Air Traffic Situation Network". Applied Mechanics and Materials 744-746 (marzec 2015): 1975–79. http://dx.doi.org/10.4028/www.scientific.net/amm.744-746.1975.
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A method for description of structural characteristics of air traffic situation based on the theory of complex network was proposed. This method characterizes the air traffic situation from three dimensions, including single aircraft, local sector, and overall sector. We selected the routinely-recorded flight data in an air traffic control sector within China's airspace in 2013. With the aircrafts in the sector regarded as nodes, and with the between-aircraft proximity relations as edges, we constructed an undirected and unweighted aircraft network. The results show that network node degree can distinguish the key aircraft in the sector; the network connection rate reflects the proximity of aircrafts; the clustering coefficient identifies the presence of high-density aircraft group.
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Zuo, Yu Yu. "Analysis of Gas Turbine Engines Auxiliary Power Units". Applied Mechanics and Materials 533 (luty 2014): 13–16. http://dx.doi.org/10.4028/www.scientific.net/amm.533.13.
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As aircraft became more complex a need was created for a power source to operate the aircraft systems on the ground without the necessity for operating the aircrafts main engines. This became the task of the Auxiliary Power Unit (APU). The use of an APU on an aircraft also meant that the aircraft was not dependant on ground support equipment at an airfield. It can provide the necessary power for operation of the aircrafts Electrical, Hydraulic and Pneumatic systems. It should come as no surprise that the power unit selected to do this task is a Gas Turbine Engine.
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Idres, Moumen. "Assessment of the Range of an Electric Aircraft". Journal of Advanced Research in Applied Sciences and Engineering Technology 50, nr 2 (25.08.2024): 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 simple flight mission that includes take-off, climb, cruise, descent and landing is considered. Electric propulsion components are modelled. The predicted range of the aircraft is 63 nm for a flight time of 43 minutes, which matches favourably with aircraft published data. The study showed that the Breguet range equation overestimates range, particularly at high altitudes. Hence, the proposed approach in this article is necessary for accurate prediction of range for short-range aircraft. Battery capacity-payload-range charts are developed for present and future battery technologies. Aircraft range can be extended to 150 nm if battery capacity is increased to 166 Ah and the payload is only the pilot. Doubling battery specific energy would extend the range to 193 nm with a flight time of 130 minutes.
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Yao, Man. "Water Impact Analysis for Aircraft over Sea". Applied Mechanics and Materials 341-342 (lipiec 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 addition, concerning with the limitation of the aircrafts overload, the water-contact condition is proposed to avert attitude overturning and structure broken of the aircraft.
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Zhaohui, Ming, Zhang Ming, Tang Xinmin i 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, nr 6 (1.12.2015): 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 variable, influencing the deceleration of the following aircraft can be analyzed. Simulation analysis is carried out for different combinations of aircraft types, initial speed, safe separation and deceleration. The follow aircraft deceleration was calculated under different conditions and the results coincided with reality. It is proved that the model can provide safe separation between the two aircrafts.
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Zhao, Chang Jun, Yue Bai, Xun Gong, Dong Fu Xu i Zhi Jun Xu. "Control System Design of a Hex-Rotor Aircraft Based on the Neural Network Sliding Mode Method". Advanced Materials Research 971-973 (czerwiec 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 system is able to guarantee the aircrafts tracking flight of the aircraft.
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Yadav, Bharosh Kumar, Ramhit Yadav i 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, nr 1 (31.12.2023): 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 computed loads into account. This study uses structural finite element analysis (FEA) to analyze the nose gear's stress behavior and displacement during landing, as well as to assess the effect of the runway gradient. Utilizing a comprehensive numerical simulation, the landing gear of a real material Twin-Otter STOL aircraft has been demonstrated to be subjected to a dynamic force of 3653.26N, a pneumatic pressure of 1.59MPa, a bead pressure of 7.97MPa, and a vertical force of 1672.31lbs on level runways, or runways with no gradient. These findings will increase the level of confidence of aircraft manufacturers to make necessary appropriate design of STOL aircraft’s landing gear. It may can decrease the aircraft accidents and increase human life safety ultimately saving valuable time and resources too.
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Shao, Haoyuan, Daochun Li, Zi Kan, Shiwei Zhao, Jinwu Xiang i Chunsheng Wang. "Analysis of Catapult-Assisted Takeoff of Carrier-Based Aircraft Based on Finite Element Method and Multibody Dynamics Coupling Method". Aerospace 10, nr 12 (29.11.2023): 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 enhanced plasticity algorithm that includes transverse shear effects was employed to simulate the tensioning and release processes of the holdback system. Additionally, the forces applied by the launch bar and holdback bar, nonlinear aerodynamics loads, shock absorbers, and tires were introduced. Finally, a comparative analysis was conducted to assess the influence of different launch bar angles and holdback bar fracture stain on the aircraft’s attitude and landing gear dynamics during the catapult process. The proposed rigid–flexible coupling dynamics model enables an effective analysis of the dynamic behavior throughout the entire catapult process, including both the holdback bar tensioning and release, takeoff taxing, and extension of the nose landing gear phases. The results show that higher launch bar angle increase the load and extension of the nose landing gear and cause pronounced fluctuations in the aircraft’s pitch attitude. Additionally, the holdback bar fracture strain has a significant impact on the pitch angle during the first second of the aircraft catapult process, with greater holdback bar fracture strain resulting in larger pitch angle variations.
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Zhang, Yuhang, Hao Sun, Jiawei Zuo, Hongqi Wang, Guangluan Xu i Xian Sun. "Aircraft Type Recognition in Remote Sensing Images Based on Feature Learning with Conditional Generative Adversarial Networks". Remote Sensing 10, nr 7 (16.07.2018): 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 aircrafts. Second, a conditional GAN with a region of interest (ROI)-weighted loss function is trained on unlabeled aircraft images and their corresponding masks. Third, an ROI feature extraction method is carefully designed to extract multi-scale features from the GAN in the regions of aircrafts. After that, a linear support vector machine (SVM) classifier is adopted to classify each sample using their features. Benefiting from the GAN, we can learn features which are strong enough to represent aircrafts based on a large unlabeled dataset. Additionally, the ROI-weighted loss function and the ROI feature extraction method make the features more related to the aircrafts rather than the background, which improves the quality of features and increases the recognition accuracy significantly. Thorough experiments were conducted on a challenging dataset, and the results prove the effectiveness of the proposed aircraft type recognition framework.
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Li, Jun, Wei Yang i Yang Pei. "Vulnerability Assessment for Fire and Explosion Suppression Measures of Aircraft Fuel System". Advanced Materials Research 510 (kwiecień 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 before and after adopting fire/explosion suppression measures are analyzed. The results show that fire/explosion suppression measures can effectively decrease the aircrafts vulnerable area and kill probability.
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Qin, Derek Xiao. "Vertical takeoff and landing aircraft: Categories, applications, and technology". Theoretical and Natural Science 13, nr 1 (30.11.2023): 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 Vehicles, and electric VTOL aircraft. These categories of VTOL aircraft are compared. Famous VTOL aircrafts like Osprey and Harrier are introduced. The technology behind VTOL aircraft is explained, and the ways in which VTOL aircraft can be made useful are reviewed. In addition, the prospect of VTOL aircraft has been made. This paper may offer a reference for the future works about VTOL.
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Sun, Ji Ku, Zong Jie Cao, De Jian Sun i Yi Chen. "Characteristic of Corrosive Damages about Aircraft Structures in Service". Applied Mechanics and Materials 543-547 (marzec 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 of aircraft structures is studied. The law of corrosion developed at aircraft structural parts or materials is summarized. This research contributes to improving professionals capacity of corrosion prevention and control. It also provides technical support for aircraft maintainers.
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Fang, Jie, i Hong Shan Xia. "Aircraft Dynamic Scheduling Algorithm Research Based on Heuristic Column Generation Algorithm". Applied Mechanics and Materials 411-414 (wrzesień 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 practical solution for airlines in the effective time.
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Kwiek, Agnieszka. "Conceptual design of an aircraft for Mars mission". Aircraft Engineering and Aerospace Technology 91, nr 6 (10.06.2019): 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 stability was computed by MATLAB code, and the derivatives computed by the SDSA software were used as the input data. Different aircraft configurations have been studied, including different wing’s aerofoils and configurations of the side plate. Findings This paper presents results of aerodynamic characteristics computations and longitudinal dynamic stability analysis. This paper shows that tailless aircraft configuration has potential to be used as Martian aircraft. Moreover, the study of the impact of side plates’ configurations on the longitudinal dynamic stability is presented. This investigation reveals that the most effective method to improve the short period damping ratio is to change the height of the bottom plate. Practical implications The presented result might be useful in case of further design of the aircrafts for the Mars mission and designing the aircrafts in a tailless configuration. Social implications It is considered by the human expedition that Mars is the most probable planet to explore. This paper presents the conceptual study of aircraft which can be used to take the high-resolution pictures of the surface of Mars, which can be crucial to find the right place to establish a potential Martian base. Originality/value Most of aircrafts proposed for the Mars mission are designed in a configuration with a classic tail; this paper shows a preliminary calculation of the tailless Martian aircraft. Moreover, this paper shows the results of a dynamic stability analysis, where similar papers about aircrafts for the Mars mission do not show such outcomes, especially in the case of the tailless configuration. Moreover, this paper presents the results of the dynamic stability analysis of tailless aircraft with different configurations of the side plates.
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Shi, Qiongyan, i Jianghua Zhang. "Mechanical Structure Design of the Aircraft ASD Control Isolation Control". Journal of Applied Mathematics 2022 (16.11.2022): 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 transmission ratio distribution and calculation of the aircraft control isolation system are given, and finally, the mechanism design of the aircraft ASD control isolation system is realized.
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Reddy, D. Ramana, M. V. Aditya Nag i 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 (lipiec 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 is carried out for different inertia load cases in addition to a test pressure of 3.5psi (24KPa), to validate whether the structure is safe or not. The size of the fuel tank has been taken as per the FAR-23 guidelines. The Finite Element Analysis is carried out to arrive at stresses and displacements in critical components using the Ansys software. The maximum shear stresses included are observed to be much less than the Yield strength of materials.
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Wang, Zhipeng, Zhiqin Qian, Ziye Song, Hongzhou Liu, Wenjun Zhang i Zhuming Bi. "Instrumentation and self-repairing control for resilient multi-rotor aircrafts". Industrial Robot: An International Journal 45, nr 5 (20.08.2018): 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, resilience and fault tolerance. All of these four aspects are taken into consideration to improve overall reliability of aircrafts. When a rotor malfunction occurs, the control algorithm is cable of adjusting the operation conditions of the rest of rotors to achieve system stability. Findings In this paper, the authors first present a research topic on the development of a resilient multi-robot aircraft. A multi-rotor aircraft usually possesses more actuated motions than the required degrees of freedom. Originality/value The authors proposed to equip the multi-rotor aircraft with malfunction detecting sensors, and they developed the self-repairing algorithm to re-stabilize the aircraft when a malfunction of a rotor occurs. The design concept and methods were implemented on an eight-rotor aircraft, and the performance of the proposed instrumentation and self-repairing algorithm have been verified and validated.
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Wang, X., H. Yu i D. Feng. "Pose estimation in runway end safety area using geometry structure features". Aeronautical Journal 120, nr 1226 (kwiecień 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 order to validate the accuracy of the pose estimation and the effectiveness of the proposed algorithm, we construct a pose database of two common aircrafts in Asia. The experiments show that the designed low-dimension features can accurately capture the aircraft's pose information and the proposed algorithm can achieve satisfied matching accuracy.
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Kim, Min-Seong, Byung Hyuk Kwon i Tae-Young Goo. "Comparisons between Mean and Turbulent Parameters of Aircraft-Based and Ship-Based Measurements in the Marine Atmospheric Boundary Layer". Atmosphere 12, nr 9 (24.08.2021): 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 flux from the surface. With the exception of temperature, the mean parameters measured by the two aircrafts were in good agreement with each other. The sensible heat flux was more dispersed than the latent heat flux according to the comparisons between aircraft and aircraft, and aircraft and ship. This study demonstrates the feasibility of using two aircraft to describe the MABL and surface flux with confidence.
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Liu, Ruiwei, Siqi Hao, Yaping Zhang, Chonghang Xu, Wenjing Li i Yunrui Mo. "A Novel Strategic Aircraft Track Planning Method Considering Conflict Probability". Aerospace 9, nr 12 (19.12.2022): 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 method for aircraft conflict probability is introduced. Then, taking conflict probability minimization as the objective, the classical ant colony algorithm (ACA) algorithm is improved to solve the model. Finally, an experimental study is conducted to illustrate the proposed method. Results show that the proposed method is able to provide a scientific and effective track planning approach considering the potential conflict probability of aircrafts, which is able to provide fundamental to the safety of entire air transport system.
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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, nr 8 (30.11.2023): 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 unique in that there are 8 closely located airfields used both for regular passenger flights and flights of experimental aircrafts not equipped with transponders. Each of the 50 noise monitoring stations can simultaneously register noise events that correspond to flight of aircrafts at different airfields. Aircraft flyover events were detected on the noise time line using an artificial neural network (ANN) that allows to identify aircraft audibility periods at the monitoring location using the 1/3 octave band of noise registered in real time for all measurement locations. This article describes the development of an ANN architecture based on the YOLO v4 convolutional neural network, as well as requirements and mechanisms for normalizing data fed to the ANN that filters data provided by the Ecoflight Monitoring aircraft noise monitoring system.
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Tang, Hong, Guo Guang Chen i Hui Zhu He. "Optimization Design and Numerical Simulation for Aerodynamics Shape of an Aircraft". Applied Mechanics and Materials 215-216 (listopad 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 can reach to design range by adjusted tails shrink angle. When the tails shrink angle reached to six degrees, the big spacing bands aircraft’s coefficient of drag decreased obviously and pressure coefficient little increased to avail of improving aircraft’s range by a large of numerical simulations.
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Cui, Xingda, Yonggang Yu, Shuai Ma, Zhongyun Xiao, Lu Zhang i Fang Liu. "Numerical investigation of the aerodynamic interference in 2-aircraft formation flight". Journal of Physics: Conference Series 2280, nr 1 (1.06.2022): 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 reduction in drag of following aircraft is much larger, that is up to 25.1%. Under the aerodynamic interference effect, the following aircraft has a nosedown pitching moment increment, and becomes lateral static instability, which is opposite to the characteristic of solo flying-wing aircraft. The aerodynamic interference mainly comes from upwash flow induced by wingtip vortex of leading aircraft, which reduces the actual AoA and induced drag of following aircraft, and changes the lift distribution of both sides of following aircraft.
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Cui, Xingda, Yonggang Yu, Shuai Ma, Zhongyun Xiao, Lu Zhang i Fang Liu. "Numerical investigation of the aerodynamic interference in 2-aircraft formation flight". Journal of Physics: Conference Series 2280, nr 1 (1.06.2022): 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 reduction in drag of following aircraft is much larger, that is up to 25.1%. Under the aerodynamic interference effect, the following aircraft has a nosedown pitching moment increment, and becomes lateral static instability, which is opposite to the characteristic of solo flying-wing aircraft. The aerodynamic interference mainly comes from upwash flow induced by wingtip vortex of leading aircraft, which reduces the actual AoA and induced drag of following aircraft, and changes the lift distribution of both sides of following aircraft.
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Chenguang, Yang, Liu Hu i 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 summarized for the multi-aircraft loading issues. In the case study, eight kinds of cargos are distributed in three different aircrafts. The optimal result indicates that this algorithm can rapidly generate the best plan for the loading problem regarding lower transport costs.
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BOIKO, Sergey, Alona HEBDA, Yurii STUSHCHANSKY, Serhiy GOLOVANOV i 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, nr 6 (29.12.2022): 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 smallest number of crew members. this fact encourages the continuous improvement of the existing on-board avionics complexes of aircraft. Among other things, the adaptive control system should determine the dynamic characteristics of the controlled aircraft during the flight, the assessment of the state of the functional systems of the aircraft and the formation of control signals. An approach to the construction of an aircraft control system is proposed, which involves a double determination of the characteristics of the object under study. The structure of the control system of an aircraft with an electric power plant is proposed. Its construction was influenced by the operating features of the aircraft’s electric power plant, the approach to the dual determination of the aircraft’s characteristics, and the principle of dual control of the aircraft’s flight parameters. The paper proposes an approach to improving the adaptive system of aircraft with an electric propulsion system. There are the following factors: 1) height, accuracy and reliability of sensors of all parameters, regardless of operating conditions; 2) a simple and at the same time reliable and functional interface; 3) timely detection of deviations in the operation of aircraft systems during its operation and transmission of relevant information to the crew and the control system; 4) operational determination of the dynamic characteristics of the aircraft during flight and adaptive optimization of controlled signals taking into account the purpose of control and the specified optimization criteria.
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Zhang, X., B. Xiong i 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 (30.04.2018): 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, linear dimensionality reduction, used in classic ACM, makes the model rigid. It brings much trouble to segment different types of aircrafts. Aiming at this problem, an improved ACM based on ISOMAP is proposed in this paper. ISOMAP algorithm is used to extract the shape information of the training set and make the model flexible enough to deal with different aircrafts. The experiments based on real SAR data shows that the proposed method achieves obvious improvement in accuracy.
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Filippov, R. N., i 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, nr 10 (739) (październik 2021): 65–73. http://dx.doi.org/10.18698/0536-1044-2021-10-65-73.
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The wake vortex consists mainly of two vortices, which are formed when the stream flows around the wings of an aircraft. A semi-empirical model of a stable vortex wake is proposed and analyzed. The model allows describing the velocity field in a vortex, depending on the characteristics of the aircraft generator, as well as assessing the effect of the vortex on the subsequent aircraft. Statistical modeling was carried out to determine the safe interval between the aircrafts for the characteristic sections of the trajectory. When moving over the sea, a straight-line route, a trajectory with turns and an ascent to an altitude for flying around the island were chosen; on the land section of the movement, a flight over the relief was simulated. A significant influence of the ruggedness of the relief on the probability of an aircraft falling when it enters a wake vortex is shown. The effect of the displacement of the aircraft trajectories in the vertical and horizontal planes and the increase in the average flight speed on the safe interval between the aircrafts is investigated.
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Kalinowski, Miłosz. "Aero-Structural Optimization of Joined-Wing Aircraft". Transactions on Aerospace Research 2017, nr 4 (1.12.2017): 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 geometry generator, FEM solver and aerodynamic panel method. The range of aircraft was assumed as an objective function. The algorithm was successfully tested on UAV aircraft. The improvement of 19% of total aircraft range is achieved in comparison to baseline aircraft. Time of evaluation of this global search algorithm is similar to the time characteristic for local optimization methods. It allows to reduce the time and costs of preliminary design of joined-wing.
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A., Armaan, i Srinivas G. "In Tune with Times: Recent Developments in Theoretical, Experimental and Numerical techniques of Aircraft Engines". International Journal of Engineering & Technology 7, nr 2 (23.05.2018): 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 new designers. Once identified the drawbacks of engine performance can be corrected in the future. For any new design of aircraft engine researchers are suggested to take Theoretical, Experimental and Numerical approaches. Therefore present paper makes an effort to review complete recent Theoretical, Experimental and Numerical approaches which are followed till date. Under all the three approaches all the air breathing engines have been clearly explained and solicited. The effort is to identify the gaps between different approaches which are hampering the process of engine development. The paper also gives the research gaps that need to be incorporated for effective performance enhancement of the aircraft engines for aeromechanical features.
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Song, Shuang. "Study on development of aircraft design theory". Theoretical and Natural Science 13, nr 1 (30.11.2023): 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 changes, theoretical updates, and applications. While introducing the development process, this article emphasizes the difficulties at each stage and the measures to solve them. In a hundred years of development, human beings have evolved from relying solely on the experience and imitation of birds in the early stages to developing and applying aerodynamics and then combining theory and practice to design.
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Zhang, Yongjie, Kang Cao, Ke Liang i Yongqi Zeng. "Study on the evaluation model of serialized civil aircraft commonality index based on fuzzy set theory". Journal of Intelligent & Fuzzy Systems 40, nr 6 (21.06.2021): 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 quantitative evaluation model has not been formed. Accordingly, this study proposes a new civil aircraft commonality index evaluation model in accordance with fuzzy set theory and methods. The model follows two branches, i.e., attribute commonality and structural commonality, to develop a multi-level civil aircraft commonality index system. The proposed model can split the commonality into six commonality sub-intervals and build the corresponding standard fuzzy set with the characteristic attribute parameters of the civil aircraft as the elements. Next, based on considerable civil aircraft sample data, a fuzzy test is designed to yield the membership function of the fuzzy set. Thus, a model of evaluating civil aircraft commonality is constructed, taking the characteristic parameters of the civil aircraft to be evaluated as input, and selecting the degree of commonality of each level as output. Lastly, this study employs the evaluation model to evaluate the commonality of Boeing 757-200 with other civil aircrafts. Furthermore, the evaluated results well explain the actual situation, which verifies the effectiveness and practicability of the proposed model.
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YANG, Jie, Jun ZHAN, Zhixiang CHEN, Xianyi LIU, Zhiqing ZHOU i Zhi LI. "Optimization method of ballistic blast fragmentation warhead striking aircraft in aircraft shelter". Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 41, nr 1 (luty 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 reducing the computation of missile-target encounter, a mean ruin probability algorithm of aircraft based on integration method is proposed, which slices target area to grids and takes grids as alternative aim point. Taking maximum to entire ruin effect of all aircrafts as target, the optimizing algorithm to strike scheme about minimum missile consumption and find best aim point based on advanced PSO algorithm are proposed. The striking scheme optimizing about fragmentation warhead striking aircraft in single/double aircraft shelter is simulated. The result shows that, low blast height, small CEP, combination strike strategy with multiply aim points can reduce the minimum missile consumption effectively.
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Fu, Yueshuai, i Huimin Fu. "A Novel Individual Aircraft Life Monitoring Method Based on Reliable Life Consumption Assessment". Machines 11, nr 11 (8.11.2023): 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 confidence limit of the aircraft structure’s reliable life can be evaluated under any fatigue loads. Based on that and the aircraft’s monitored fatigue loads, the indexes of reliable life consumption and remaining reliable life percentages are proposed and assessed in real time for individual aircraft life monitoring and online life management. Case studies indicate that the proposed method can guarantee high confidence and reliability requirements in individual life monitoring, consistent with the aircraft’s life determination and extension, which are widely accepted nowadays in engineering practice.
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Wu, Jiang, Feng Gao, Shengwen Li i Fengtian Yang. "Conceptual Design and Optimization of Distributed Electric Propulsion General Aviation Aircraft". Aerospace 10, nr 5 (22.04.2023): 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 optimization. To concentrate on the layout of the propellers and wing, a propeller with the same chord distribution, twist distribution, and number of blades is selected. The design and optimization of DEP aircraft’s range is carried out with the objective of achieving the maximum product of the lift–drag ratio with propeller efficiency under force balance constrains. Additionally, to decrease the takeoff and landing distance, the DEP aircraft’s takeoff and landing performance are optimized with the objective of the smallest velocity at an angle near the tail down angle under the constrains of acceleration bigger than 0 and a Mach number at the tip of blades smaller than 0.7. The CFD simulation was used to confirm the DEP aircraft’s pretty accurate aerodynamics. Compared to the reference aircraft, the improved DEP aircraft with 10 high-lift propellers on the leading edge of the wing and 2 wing-tip propellers may boost cruise performance by 6% while maintaining takeoff and landing velocity. Furthermore, it has been shown that the stall speed of DEP aircraft with smaller wings would rise proportionally when compared to conventional design aircraft, and the power need of DEP aircraft will be increased as a result of the operation of high-lift propellers. The conceptual design and optimal approach suggested in this work has some reference value for the design and research of the fixed-wing DEP general aviation aircraft.
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Lin, Fusheng, i Guang Meng. "Study on the Dynamics of a Rotor in a Maneuvering Aircraft". Journal of Vibration and Acoustics 125, nr 3 (18.06.2003): 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 unbalanced response of a rotor in an aircraft is obviously influenced by the aircraft’s flying status.
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Durgam, Shankar, Sweety Rajesh Deshmukh i Preetam Selmokar. "Selection of aircraft materials and aircraft air conditioning technologies: A review". IOP Conference Series: Materials Science and Engineering 1258, nr 1 (1.10.2022): 012036. http://dx.doi.org/10.1088/1757-899x/1258/1/012036.
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This article reviews the demands of innovative material and the best refrigeration cycle to dissipate heat in airplane cabin. The suitable materials of excellent mechanical properties are used for aircraft applications that makes the aircraft to live longer, stay safe, reliable, and durable. Airplane is a special type of aircraft. The helicopter, and hot air balloon are aircrafts, but airplane is special type of aircraft which is weighing its body and it can be controlled and powered. Refrigeration in airplane, does not so far involve the use of any techniques which have not already established and used in other fields but of prime importance for comfort of occupants. The analysis for aircraft materials is briefly described with its significance. The material production is going to be innovated in various countries across the globe and among all the countries Russia is on top level for better using materials for aircraft production. The material used for aircraft production must be light, and efficient. It should not be affected by any impurities. This paper also gives the merits and demerits of such material and their sustainability. The motive of this review is to describe, briefly properties of materials for aircraft, and air conditioning technologies that best suited system for aircraft to dissipate heat.
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Huang, Wei, Wen Jun Wang, Fu Li Bai i Xiang Hui Zhang. "Study on Optimization of Multi-Type Aircraft Scheduling Robust Model". Applied Mechanics and Materials 40-41 (listopad 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 from above flight strings to obtain high robustness of multi-type flight scheduling combination. The phased multi-type aircraft scheduling robust model has been successfully applied in the domestic airline scheduling, it has been achieved a better effect of robust optimization.
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Xiao, Xian Bo, Xiang Jun Kong, Ya Jie Shi i Si Yuan Yao. "Jet Blast Resistance Experiment of Engineered Material Arresting System". Advanced Materials Research 750-752 (sierpień 2013): 2244–47. http://dx.doi.org/10.4028/www.scientific.net/amr.750-752.2244.
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Engineered materials could arrest aircrafts rushing out of runway, but its fragile and can be easily damaged by jet blast exhausted by taking off aircraft nearby. Engineered material unit coating and encapsulation were described in this paper, and a jet blast resistance experiment is designed to quantitatively measure the units resistant capability. In this experiment, a test bed built by units will receive a taking-off Boeing 737-300 aircrafts jet blast for over 60 seconds. The test order decreased distance from aircraft tail to the test bed. And the predicted air velocity and temperature was calculated through aircrafts characteristics contour. All the design made the experiment high reliable and economical. Experimental result indicated that the nearest distance from the test bed to aircraft tail could be 15 meters, and this experiment result has already been used for design of the arresting system in a Chinese civil airport.
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Luo, Sai. "Discussion on Continuous Airworthiness and Maintenance of Civil Aircraft". Journal of Electronic Research and Application 6, nr 1 (18.01.2022): 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 and maintenance of civil aircraft.
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Amelyushkin, I. A., M. A. Kudrov i P. S. Kuleshov. "Peculiarities of icing in a flow with supercooled droplets and ice crystals". Journal of Physics: Conference Series 2817, nr 1 (1.08.2024): 012025. http://dx.doi.org/10.1088/1742-6596/2817/1/012025.
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Abstract New results of aircraft icing are obtained. New mathematical models of physical phenomena are formulated. Original construction of adaptive wing was invented, developed and prototypes were built. New algorithm of aircrafts’ surface with nanorelief are developed. Parametric studies of aircraft icing peculiarities were carried out.
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T, Gurumekala, Indira Gandhi S i Senthil Sivakumar M. "122 Published By: Blue Eyes Intelligence Engineering and Sciences Publication (BEIESP) © Copyright: All rights reserved. Retrieval Number: A10301291S52019/2019©BEIESP DOI:10.35940/ijeat.A1030.1291S519 Journal Website: www.ijeat.org Routing Protocols for AANET". International Journal of Engineering and Advanced Technology 9, nr 1s5 (30.12.2019): 122–26. http://dx.doi.org/10.35940/ijeat.a1030.1291s519.
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Ad hoc network is an infrastructure less, self-configuring and dynamic network where the nodes are able to forward the information to other nodes based on connectivity and routing algorithm they follow. Recently, the concept of this ad hoc networking has been introduced among aircrafts for providing in-flight communication and to manage increased flow of data produced by civil aviation. The aircraft communication can be established either by satellites or cellular based systems. Utilizing satellites for the communication is very expensive and prone to high propagation delay. The cellular based systems provide direct link to aircraft with minimum cost and less delay. As the line-of-sight range of cellular systems is limited, the aircraft over the oceanic regions is unable to communicate with ground stations. Aiming at overcoming the demerits associated with aforementioned technologies for aircraft communication, the Aeronautical Ad hoc networks has been developed, which creates a ad hoc network among aircrafts where each aircraft is self-aware nodes and communicates with ground stations and other aircrafts irrespective of their flight region. AANET shares has some similarities with existing wireless ad hoc networks whilst having unique challenges in supporting greater mobility, size of network, node density and bandwidth limitations. Because of this unique challenges, routing in this AANET is a difficult task. In this paper, various routing algorithms for AANET with its merits and demerits has been thoroughly studied. Finally, the unsolved problems and research issues of routing in AANET are identified.