Статті в журналах з теми "Aircraft's safety"
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1
Wang, X., H. Yu, and D. Feng. "Pose estimation in runway end safety area using geometry structure features." Aeronautical Journal 120, no. 1226 (April 2016): 675–91. http://dx.doi.org/10.1017/aer.2016.16.
Анотація:
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.
2
Feng, Zihan. "Flutter Phenomenon and Safety Implications in Transonic Flow." Highlights in Science, Engineering and Technology 76 (December 31, 2023): 198–204. http://dx.doi.org/10.54097/br1qsb29.
Анотація:
As advancements in aircraft manufacturing technology persistently elevate the boundaries of flight speed, challenges emerge when aircraft velocities verge on sonic speeds. Notably, empirical observations have highlighted instances of pronounced vibrations and, in extreme cases, structural failures, casting shadows over flight stability and safety. This research endeavors to dissect the ramifications of shock waves and flutter phenomena, precipitated by fluid discontinuities during supersonic flight, on the overarching safety of aircraft. Methodologically, the study delineates a series of simulation protocols, commencing with the derivation of simplified functions representing the aircraft's 2D contour, followed by error function computations, and finally, using the finite difference method in conjunction with the successive over-relaxation (SOR) iterative technique to model the aircraft's velocity distribution. Preliminary findings indicate that for β values spanning 0.1, 0.15, and 0.175, the surrounding airflow retains its continuity and stability, with the Mach number's rate of change exhibiting a decelerating trend. Conversely, at a β threshold of 0.2, the airflow descends into turbulence, manifesting in erratic Mach number fluctuations. Such fluidic discontinuities underscore potential threats to the aircraft's flight safety, necessitating further exploration and mitigation strategies.
3
Michalak, Sławomir, and Tomasz Tokarski. "The effect of the operation time of the aircraft power system on power quality in transient states." Journal of Konbin 54, no. 1 (March 29, 2024): 47–64. http://dx.doi.org/10.5604/01.3001.0054.4462.
Анотація:
The paper presents the importance of electricity parameters in transient states for assessing the ability of an aircraft's power grid to self-regulate. It has been shown that the quality of electrical energy of an aircraft's power system is influenced by its operating time. Aging changes resulting from long-term operation of the power system cause deterioration of electrical energy parameters, which directly affects airworthiness and flying safety. Maintaining standard energy parameters in transient states is very important to ensure proper operation of the aircraft. The article describes the method of measuring the quality of electricity in transient states, and using the example of the DC power system of the Su 22 aircraft, the essence of its network diagnostics in transient states is presented. Also presented are sample results of research conducted by the authors regarding changes in electrical energy parameters in transient states of the Su 22 aircraft, obtained during its many years of operation.
4
Feng, Jiaqi. "Analysis of aerodynamic characteristics of aircraft during take-off and landing." Applied and Computational Engineering 28, no. 1 (December 6, 2023): 92–98. http://dx.doi.org/10.54254/2755-2721/28/20230133.
Анотація:
Take-off and landing are the most critical phases of flight, as they require the pilot's utmost attention and skill. Through force analysis, we can determine the main factors that affect aircraft take-off and landing performance. By understanding these factors, we can improve the safety and efficiency of air travel. During take-off and landing, lift, weight, thrust, and drag work together to give rise to the aircraft's resultant motion and angle of attack. By analysing these forces, we can determine the aircraft's speed and altitude during these critical phases. Ground friction is a factor that is often neglected in theoretical analysis but has a significant effect on aircraft performance in reality. Friction between the wheels and the runway affects the braking of the aircraft after it begins to decelerate on the runway, making it essential for a secure landing. Accurately measuring the friction coefficient can help prevent accidents, particularly in severe weather conditions. Investigating these factors can aid in improving aircraft performance, achieving better energy efficiency, and meeting modern society's needs for safe and efficient air travel. By considering these factors, we can enhance the safety and efficiency of aircraft take-off and landing, ensuring a more reliable and enjoyable travel experience for all.
5
Kim, Hyeonsoo, Minsu Kim, Byungjoon Shin, and Younghee Jo. "A Study on the Flight Safety Analysis of Military Aircraft External Stores." Journal of the Korea Institute of Military Science and Technology 26, no. 1 (February 5, 2023): 83–90. http://dx.doi.org/10.9766/kimst.2023.26.1.083.
Анотація:
The external store fitted to the aircraft may affect the flight characteristics and flight safety of the aircraft, which requires the analyses and testing on it. The purpose of this study is to identify and analyze types of failures that can affect the flight safety of aircraft due to the installation of external stores, and to check the flight safety of aircraft through dropping tests of the external stores. After identifying the types of failures that could affect the flight safety of the aircraft, the criticality was calculated to analyze the effect on the flight safety of the aircraft. Four types of failures were selected: unintentional dropping, failure of dropping, unintentional main wing deployment, and release of tail wing restraint of the external store, which are considered to affect the flight safety of the aircraft due to the operation of the external store. As a result of the aircraft's flight safety analysis on the failure types, the criticality requirements were met. Based on this, after obtaining the airworthiness certification, the drop test was successfully performed to confirm the flight safety of the aircraft by mounting an external store on the aircraft. However, in addition to the four hazards carried out in this study, the real external stores of the military aircraft may have various factors affecting the flight safety of the aircraft, so further research will be needed.
6
Kim, Hyeonsoo, Minsu Kim, Byungjoon Shin, and Younghee Jo. "A Study on the Flight Safety Analysis of Military Aircraft External Stores." Journal of the Korea Institute of Military Science and Technology 26, no. 1 (February 5, 2023): 83–90. http://dx.doi.org/10.9766/kimst.2023.26.1.83.
Анотація:
The external store fitted to the aircraft may affect the flight characteristics and flight safety of the aircraft, which requires the analyses and testing on it. The purpose of this study is to identify and analyze types of failures that can affect the flight safety of aircraft due to the installation of external stores, and to check the flight safety of aircraft through dropping tests of the external stores. After identifying the types of failures that could affect the flight safety of the aircraft, the criticality was calculated to analyze the effect on the flight safety of the aircraft. Four types of failures were selected: unintentional dropping, failure of dropping, unintentional main wing deployment, and release of tail wing restraint of the external store, which are considered to affect the flight safety of the aircraft due to the operation of the external store. As a result of the aircraft's flight safety analysis on the failure types, the criticality requirements were met. Based on this, after obtaining the airworthiness certification, the drop test was successfully performed to confirm the flight safety of the aircraft by mounting an external store on the aircraft. However, in addition to the four hazards carried out in this study, the real external stores of the military aircraft may have various factors affecting the flight safety of the aircraft, so further research will be needed.
7
Yang, Qin Yu, Jin Bo Yao, Yue Ming Yang, and Xue Wei Liu. "In the Wind Tunnel Simulation Defroster Control Study." Applied Mechanics and Materials 380-384 (August 2013): 191–94. http://dx.doi.org/10.4028/www.scientific.net/amm.380-384.191.
Анотація:
Aircraft in flight, such as supercooled water droplets encountered icing conditions suitable for the external environment, the relevant parts of the body will freeze, making the aircraft's aerodynamic performance deterioration, severe endanger flight safety, in addition, the aircraft parked in the open winter months , there will be icing, you need to clean up before takeoff. We should grasp the mechanism of aircraft icing, environmental factors and easy to freeze parts of the body. This paper presents a simulation using the wind tunnel icing device icing wind tunnel simulations can reproduce the real situation of aircraft icing, for guiding practice and got good results.
8
Yao, Jin Bo, Yue Ming Yang, Qin Yu Yang, Xiu Juan Liu, and Dun Jin. "Application of LED Light Source in the Flow Imaging." Applied Mechanics and Materials 380-384 (August 2013): 219–22. http://dx.doi.org/10.4028/www.scientific.net/amm.380-384.219.
Анотація:
Aircraft in flight, such as supercooled water droplets encountered icing conditions suitable for the external environment, the relevant parts of the body will freeze, making the aircraft's aerodynamic performance deterioration, severe endanger flight safety, in addition, the aircraft parked in the open winter months , there will be icing, you need to clean up before takeoff. We should grasp the mechanism of aircraft icing, environmental factors and easy to freeze parts of the body. This paper presents a simulation using the wind tunnel icing device icing wind tunnel simulations can reproduce the real situation of aircraft icing, for guiding practice and got good results.
9
Kiselev, M. A., Y. S. Kalyuzhny, A. V. Karpov, and S. F. Borodkin. "Methodology for plotting the flight planned route change of the aircraft in flight." Civil Aviation High Technologies 26, no. 6 (December 25, 2023): 33–46. http://dx.doi.org/10.26467/2079-0619-2023-26-6-33-46.
Анотація:
A significant number of aviation incidents is related to loss of control in flight and controlled flight into terrain (LOC-I, CFIT, LALT categories). Investigation of these aviation incidents has revealed that these incidents often occur due to the need for rapid changes in flight routes as a result of detecting obstacles, such as thunderstorms, along the aircraft's path. During the determination of alternative routes to circumvent the encountered obstacle, as well as during the implementation process of the chosen rerouted route, the flight crew makes errors due to increased psycho-physiological workload and time constraints. This article presents an approach to the automatic rerouting of the aircraft's flight route to avoid obstacles detected during flight. The algorithm proposed by the authors allows for evaluating the safety of the original route, calculating alternative route options to bypass the obstacles encountered during flight, verifying their feasibility considering the aircraft's flight technical characteristics and control parameter limitations, and selecting the optimal rerouted route based on specific criteria, such as minimizing the increase in the flight route length, reducing additional fuel consumption, time required for implementing the new flight route, etc. Examples of rerouting the flight route of a hypothetical aircraft with detected obstacles along the flight path are provided in the article to demonstrate the algorithm's functionality. It is shown, in particular, that in the considered example, the shortest route for obstacle avoidance is not optimal in terms of time. It is also demonstrated that the safety of flying along the identified alternative rerouted routes depends, among other factors, on the selected flight speed. Therefore, for each calculated rerouted route, the algorithm determines a range of speeds within which the implementation of the obtained rerouted route is possible. This highlights the complexity and non-triviality of the pilot's task of autonomously finding a safe obstacle avoidance route on board the aircraft.
10
LESZCZYŃSKI, Tadeusz, Daniel JANUSZEWSKI (januszewski.d@wp.pl), and Adam BUDZYŃSKI (adam.artur.budzynski@gmail.com). "Summary of Failure Conditions Recorded in Selected Helicopters Operated by Army Air Corps." Problems of Mechatronics Armament Aviation Safety Engineering 15, no. 1 (March 31, 2024): 99–114. http://dx.doi.org/10.5604/01.3001.0054.4491.
Анотація:
This paper has been drawn up for the Air Operations Group and the Technical Maintenance Group of the 56th Air Force Base in Inowrocław (Poland). Its primary purpose is to compare the frequency of failure conditions and their impact on the safety of flights performed on Mi-24 and W-3PL helicopters. Special attention has been paid to the values of flight parameters recorded and any anomalies identified. The data were analyzed using the "Objective Record Analysis" software, with two aspects taken into consideration. The first aspect – failure conditions which do not affect flight safety, i.e. when the crew exceeded the permissible flight parameters for a given exercise, an interference took place, a calculation error occurred in the system or the equipment became uncalibrated. A total of 534 failure states were singled out, with 18% of them caused by the human factor. The remaining 82% occurred due to interference and errors in the recording system or due to an incorrect flight parameter recording process (with this factor remaining beyond the control of the flight crew or maintenance personnel). The second aspect focused on failure conditions having an impact on flight safety, i.e. when the crew exceeded the aircraft's operating envelope or damage to the aircraft's systems and components occurred. 1,075 states have been recorded, with safety violations caused by exceeding the aircraft’s operating limits accounting for 5% of them. Damage to aircraft systems and components was the root cause of the 95% of the failures (with emergency landings required in 6 cases). It was shown that 80% of the failure conditions studied occurred on the Mi-24, with the number of missions performed on this particular type being nearly twice as high as on the W-3PL. Analysis of the years to which the available data was related (2012-2016) has led to the conclusion that the number of flights performed and the number of failure conditions was on an increase. However, the share of failure conditions in the total number of flights decreased. Authors 1 and 2 serve in the 56th Air Force Base and were granted permission to access and publish the data presented in this paper.
11
Cai, Wenchao, and Yadong Zhou. "Preventing aircraft from wildlife strikes using trajectory planning based on the enhanced artificial potential field approach." Metascience in Aerospace 1, no. 2 (2024): 219–45. http://dx.doi.org/10.3934/mina.2024010.
Анотація:
<abstract> <p>Wildlife strikes refer to collisions between animals and aircraft during flight or taxiing. While such collisions can occur at any phase of a flight, the majority occur during takeoff and landing, particularly at lower altitudes. Given that most reported collisions involve birds, our focus was primarily on bird strikes, in line with statistical data. In the aviation industry, aircraft safety takes precedence, and attention must also be paid to optimizing route distances to minimize operational costs, posing a multi-objective optimization challenge. However, wildlife strikes can occur suddenly, even when aircraft strictly adhere to their trajectories. The aircraft may then need to deviate from their planned paths to avoid these collisions, necessitating the adoption of alternative routes. In this article, we proposed a method that combines artificial potential energy (APE) and morphological smoothing to not only reduce the risk of collisions but also maintain the aircraft's trajectory as closely as possible. The concept of APE was applied to flight trajectory planning (TP), where the aircraft's surroundings were conceptualized as an abstract artificial gravitational field. This field exerts a "gravitational force" towards the destination, while bird obstacles exert a "repulsive force" on the aircraft. Through simulation studies, our proposed method helps smooth the trajectory and enhance its security.</p> </abstract>
12
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 (December 31, 2023): 1–20. http://dx.doi.org/10.3126/oas.v2i1.65618.
Анотація:
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.
13
Liu, Xinchao, Zeqing Chen, and Ronghao Guo. "Design of Dual-tiltable Ducted-Fan Aircraft Based on Cross-coupling Network Control." Academic Journal of Science and Technology 7, no. 3 (October 29, 2023): 274–79. http://dx.doi.org/10.54097/ajst.v7i3.13413.
Анотація:
In recent years, with the rapid development of drone technology, unmanned aerial systems have been widely applied in various fields. Although the flight control and airframe structure of traditional multirotor aircraft are fairly mature, they still face challenges such as low aerodynamic efficiency, low safety, and complex structure. In order to solve these issues, a dual-tiltable-ducted-fan aircraft system is designed. The system is equipped with an STM32F407 processor as the main controller, which receives motion control information from the remote control module. By employing cross-coupling network control methods, it coordinates the output values and tilt angles of the two channeling fans to achieve stable control of the aircraft's flight attitude.
14
Loroch, Leszek, and Andrzej Żyluk. "New Technologies for Air Traffic Security." Journal of Konbin 7, no. 4 (January 1, 2008): 95–112. http://dx.doi.org/10.2478/v10040-008-0081-z.
Анотація:
New Technologies for Air Traffic Security Security of increasing intensity of air traffic requires significant technological support. In Europe, the dynamics of this phenomenon will be additionally stimulated by implementation of unmanned aerial vehicles (UAVs) into the air traffic. For effective operation of aircraft fleet it is necessary to employ new on-board diagnostic devices and flight recorders in order to evaluate technical condition of aircraft's instrumentation. Reducing the pilots' workload requires the development of new integrated digital avionics. On the other hand, in order to make the air traffic more secure, it is necessary to develop "sense and avoid" systems not only for UAVs, but for piloted aircraft, as well. On-ground support requires the effective airport/airfield protection and keeping airfield pavements well-maintained and safe.
15
Ruan, Qikang. "Analysis of the types of aircraft icing and the solutions." Applied and Computational Engineering 9, no. 1 (September 25, 2023): 177–81. http://dx.doi.org/10.54254/2755-2721/9/20230082.
Анотація:
Aircraft ice accumulation has a negative impact on flight safety, the smooth flow field on the aircraft surface, flight drag, flight control accuracy, and lift. It interferes with the smooth flow field of the aircraft's surface, increases flight drag, lessens the accuracy of the flight controls, diminishes the lift of the aircraft, and affects the stability and operation of the aircraft. The primary scientific challenge is to catalog the several forms of icing that exist, along with their sources and aerodynamic configuration-related impacts. This paper primarily examines the most efficient de-icing techniques in light of various ice kinds. The paper is divided into two parts: the classification of each anti-icing technique and the comparative analysis that follows. The most practical anti-icing techniques are now available, it is determined. This paper can greatly reduce the anti-icing resources and design space required by the aircraft in winter.
16
SOLTANMOHMMAD, BAHRAM, and RUXANDRA MIHAELA BOTEZ. "Control moment coefficient methodology validation for eVTOL sizing." Romanian Journal of Technical Sciences - Applied Mechanics 68, no. 2-3 (December 14, 2023): 161–81. http://dx.doi.org/10.59277/rjts-am.2023.2-3.05.
Анотація:
This paper presents a novel approach for the preliminary design of electric Vertical Takeoff and Landing (eVTOL) aircraft that utilizes the new Control Moment Coefficient (CMC) to size electric motors and to determine the rotor location and incidence angle. The CMC is determined for both thrust and arm length in eVTOL aircraft design, and is used to measure the moment produced by the rotors in the roll, pitch, and yaw axes. Analyzing its dimensionless value thus allows insights into an eVTOL aircraft's controllability. To test our methodology, two eVTOL aircraft were used in flight tests, one of which had up to 126% higher CMC values than the other. The results of the flight tests showed that a higher CMC value yielded many benefits, including an increased margin of safety between the rotors and the saturation level, reduced tracking error, and reduced control effort (or energy consumption).Furthermore, the 126% increase in the dimensionless CMC related to the pitch resulted in a 30% increase in the Pulse-Width Modulation - PWM margin of safety of the rotors at the saturated level while still maintaining a reasonable tracking error and a 97% decrease in the pitch control effort. Our research suggests that incorporating higher CMCs into the preliminary design of an eVTOL aircraft can significantly improve its safety and controllability. We hope that our findings will encourage further exploration of this promising approach in future.
17
Psyllou, Elena, Arnab Majumdar, and Washington Ochieng. "A Review of Navigation Involving General Aviation Pilots Flying under Visual Flight Rules." Journal of Navigation 71, no. 5 (May 21, 2018): 1130–42. http://dx.doi.org/10.1017/s0373463318000279.
Анотація:
General Aviation (GA) pilots need, more than ever, to be constantly aware of their aircraft's position especially when they navigate in areas surrounded by controlled airspace. With pilots being taught to navigate using visual landmarks and radio, the increasing use of space-based navigation aids might degrade the pilot's performance. Given limited literature resources on navigation by GA pilots, the following three navigation methods are outlined: visual, radio-based and space-based navigation. 27 GA pilots were interviewed in three European nations to determine the navigation methods currently used and their impact on the pilots’ performance. The selection of the participants based on aircraft type (fixed-wing, ultralight and glider), in three European nations highlights profound differences in navigation between the three most popular aircraft designs. Furthermore, space-based navigation aids, in particular portable computers, have changed both planning and navigation implying that changes in the training of pilots are urgently needed to enhance the pilot's performance, and subsequently, to promote aviation safety.
18
Birbraer, Adolf N., and George D. Kostrov. "Probability of a High-Speed Military Aircraft Falling at a Nuclear Power Plant and Setting of Design Loads on Building Structures." Earthquake Engineering. Construction Safety, no. 6 (December 25, 2020): 10–26. http://dx.doi.org/10.37153/2618-9283-2020-6-10-26.
Анотація:
The article is devoted to issues related to the probabilistic justification of the safety of nuclear power plants (NPP) when a high-speed military aircraft falls. The random parameters are the recurrence of falls and the direction of the aircraft's trajectory. The conservative value of the recurrence of falls, given in the IAEA documents, was used, which ensures a high degree of NPP safety. The aircraft approach is assumed to be equally probable from either side. The trajectory slope is specified taking into account the IAEA documents and statistics of aviation accidents.
The aircraft impact load is applied to one of the structures, therefore the impact probability must be determined independently for each of them. It is proportional to the equivalent area of the building structure, depending on its size, shape, position in space and in relation to other structures. Expressions are given for the equivalent areas of structures of various shapes, typical for NPP. It is shown that if the aircraft crash is unintentional (accident), then with the usual dimensions of structures, the probability of an impact in them is less than the value, starting from which, according to Russian standards, it must be taken into account in the design basis of the NPP, i.e. it can be ignored. Dependencies are given for calculating the probability of an aircraft strike in the case of a deliberately organized accident (terrorist attack), in which the aircraft will surely fall on the territory of “Nuclear Island” of the NPP.
The procedure for setting the design loads on the building structures of a NPP in the case of a deliberate aircraft fall based on the allowed probability of their realization is described. It is shown that this method of setting the loads makes it possible to substantiate their significant reduction, which leads to a reduction in the cost of the NPP while guaranteeing its safety. A probabilistic assessment of structures safety of existing NPP in the event of an aircraft impact is discussed.
19
Elfitra Desifatma. "Electrical Wing Prototype Anti Icing pada Pesawat Komersil." Jurnal Jaring SainTek 2, no. 2 (October 29, 2020): 34–41. http://dx.doi.org/10.31599/jaring-saintek.v2i2.331.
Анотація:
The accumulation of ice on the aircraft's wings can cause a decrease in the aerodynamic properties of the aircraft, increase in weight, and it is difficult to control the aircraft so that it affects aircraft safety. Icing handling on aircraft is growing. One of the newest systems being developed is electrical anti-icing. Therefore, the researcher designed a prototype of an anti-icing electrical wing on a commercial aircraft with advantages in terms of maintenance and lighter components. The purpose of making this prototype is to design an anti-icing electrical wing in the form of a prototype and can be used as an anti-icing. The prototype consists of three parts, namely input, control unit, and heating element. The heating element working system is by attaching the heating element to the surface of the wing, so when the tool is active through the controls, the heating element will work with an indication of the LED on. After testing the Prototype electrical anti-icing function that has been made, it can be used as a de-icing that removes icing that has already frozen on the leading edge.
20
Andriawan, Antonius Angga, Nanang Ruhyat, and Michael Kirkland Ngala. "Analysis of Changes in ACM Performance in PK-XXX Aircraft with Modification of Cleaning Method to Get a Comfortable Temperature." Journal of Integrated and Advanced Engineering (JIAE) 2, no. 1 (March 20, 2022): 45–54. http://dx.doi.org/10.51662/jiae.v2i1.38.
Анотація:
Airplanes are a mode of transportation that people are interested in because they have a relatively short travel time and long distances. Therefore, aircraft is a means of transportation with a high level of safety. One level of safety comes from the aircraft's Air Conditioning (AC) system, which functions as a temperature controller for the aircraft during flight and as a pressure protector during flight. Various components make up an aircraft AC system, one of which is the Air Cycle Machine (ACM). Where the ACM changes the temperature to extremes from hot to cold, the ACM becomes fouling, thereby reducing the performance of the ACM itself and causing an increase in the cabin temperature of the aircraft. This problem was solved by a different cleaning method, first using Aluminum Solution and second without using Aluminum Solution. The difference in cleaning methods aims to determine the right cleaning method to overcome the existing problems. The results showed that power without using aluminum solution gave 49.802 kJ/s in 5 minutes and 54.771 kJ/s in 10 minutes, while power using aluminum solution showed 40.1705 kJ/s in 5 minutes and 61.4155 kJ/s in 10 minutes. This indicates that the use of Aluminum solution requires greater power after the ACM rotates for 10 minutes, affecting the efficiency of the ACM itself. The results prove that the cleaning method without aluminum solution gives results of 140.6% at 5 minutes and 90.34% at 10 minutes compared to before.
21
Li, Xu, Xiaoping Zhu, Zhou Zhou, and Xiaoping Xu. "The Numerical Simulation of UAV's Landing in Ship Airwake." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 37, no. 1 (February 2019): 186–94. http://dx.doi.org/10.1051/jnwpu/20193710186.
Анотація:
In order to investigate the influence of ship airwake on aerodynamic characteristics of the carrier-based aircraft, UAV's landings in different winds over deck were simulated by Overset Mesh method. Firstly, mesh factors, steady and unsteady methods were compared based on single aircraft carrier. The results showed that the boundary layer mesh around ship didn't show obvious influence for our simulation, and the calculation results between the steady and unsteady time average showed a similar trend. Then, aircraft carrier's flow fields in three wind directions were analyzed, and ship airwake variations with different direction winds over deck were concluded as well. Next, the reliability of Overset Mesh was verified though single UAV's landing simulation. Finally, the coupled flow fields of UAV/ship were studied. The calculation results indicated that aircraft was always in a low dynamic pressure condition, the lift and pitching moment of UAV had apparent changes in landing. Meanwhile, the aerodynamic fluctuations of UAV also revealed differences in different wind directions. The simulation results can be regarded as a reference for the safety assessment of carrier-based aircraft's landing and its control in the future.
22
Saraygord Afshari, Sajad, Bhargava Jonnadula, Xiangyang Xu, Xihui Liang, and Zhaohui Yang. "Jet Engine Optimal Preventive Maintenance Scheduling Using Golden Section Search and Genetic Algorithm." Journal of Prognostics and Health Management 2, no. 1 (July 13, 2022): 45–71. http://dx.doi.org/10.22215/jphm.v2i1.3321.
Анотація:
Jet engines are critical assets in aircraft, and their availability is crucial in the modern aircraft industry. Therefore, their maintenance scheduling is one of the major tasks an airline has to make during an engine’s lifetime. A proper engine maintenance schedule can significantly reduce maintenance costs without compromising the aircraft's reliability and safety. Different maintenance scheduling approaches have been used for jet engines, such as corrective, preventive, and predictive maintenance strategies. Regarding the safety demands in aircraft industries, preventive maintenance is a frequent maintenance method for jet engines. However, preventive maintenance schedules are often use fixed maintenance intervals, which is usually suboptimal. This paper focuses on minimizing a jet engine's overall maintenance cost by optimizing its preventive maintenance schedule based on an engine’s comprehensive reliability model. A hierarchical optimization framework including the golden section search and genetic algorithms is applied to find the optimal set of preventive maintenance number and their times and the components to be replaced at those times during the jet engine's overall lifetime. The Monte Carlo simulation is used to estimate the engine’s failure times using their lifetime distributions from the reliability model. The estimated failure times are then used to determine the engine's overall corrective and preventive maintenance costs during its lifetime. Finally, an optimal preventive maintenance schedule is proposed for an RB 211 jet engine using the presented method. In the end, comparing the proposed method's overall maintenance cost with two other maintenance methods demonstrates the proposed schedule's effectiveness. The method presented in this paper is generic, and it can be used for other similar engineering systems.
23
Ochi, Y. "Flight Control System Design for Propulsion-Controlled Aircraft." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 219, no. 4 (April 1, 2005): 329–40. http://dx.doi.org/10.1243/095441005x30289.
Анотація:
The loss of an aircraft's primary flight controls can lead to a fatal accident. However, if the engine thrust is available, controllability and safety can be retained. This article describes flight control using engine thrust only when an aircraft has lost all primary flight controls. This is a kind of flight control reconfiguration. For safe return, the aircraft must first descend to a landing area, decelerate to a landing speed, and then be capable of precise flight control for approach and landing. For these purposes, two kinds of controllers are required: a controller for descent and deceleration and a controller for approach and landing. The former controller is designed for longitudinal motion using a model-following control method, based on a linear quadratic regulator. The latter is designed by an H∞ state-feedback control method for both longitudinal and lateral-directional motions. Computer simulation is conducted using linear models of the Boeing 747. The results indicate that flight path control, including approach and landing, is possible using thrust only; however, speed control proves more difficult. However, if the horizontal stabilizer is available, the airspeed can be reduced to a safe landing speed.
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Mourad, Nahia. "Assessment of Structural Cracks in Aircraft Using a Decision-Making Approach Based on Enhanced Entropy and Single-Valued Neutrosophic Sets." International Journal of Neutrosophic Science 19, no. 04 (2022): 49–57. http://dx.doi.org/10.54216/ijns.190404.
Анотація:
Structural health monitoring (SHM) tries to determine the status of substances, elements, and the life expectancy of any aircraft building. It also serves as a vital tool for ensuring the structural integrity and safety of the aircraft. This research used a neutrosophic-Entropy model to assess the structural cracks in the reinforced concrete aircraft to evaluate its structural performance. For example, Entropy may be used in the civil engineering profession to pick subcontractors, manage traffic, and monitor the structural integrity of a structure, among other things. SHM in reinforced concrete aircraft buildings is examined in this research using the suggested technology. Expert groups were consulted to help determine the level of significance among the parameters used to monitor the aircraft's structural integrity. To further understand the structures' actual improvement, the Entropy approach given here would be quite beneficial. Also, we presented some neutrosophic multiplications. Neutrosophic multiplication module (NMM) (a.k.a. ) (commulative group (A))has produced some surprising new findings, which we explore in this article. As a bonus, we'll shed some light on a few related topics to the NMM itself. Since the Neutrosophic Jacobson radical of the A multiplication modules is a Neutrosophic small submodule of , then must be a Neutrosophic cyclic module, as we demonstrate. Last but not least, we prove that E (Universal) is a NMM only if and only when it's Neutrosophic divided modules more than a Neutrosophic integral domain.
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Zhang, Yuhang, Chang Liu, Tingting Xu, Yan Huang, and Liangyan Tao. "Impact analysis and classification of aircraft functional failures using improved FHA based on grey evaluation." Grey Systems: Theory and Application 10, no. 2 (April 6, 2020): 159–71. http://dx.doi.org/10.1108/gs-07-2019-0027.
Анотація:
PurposeThe technical level of aircraft failure analysis plays a special role in ensuring the safety of civil aviation flight. Using appropriate methods for functional failures analysis can provide a reliable reference for aircraft safety. The purpose of this paper is to provide a new and comprehensive measure based on conventional functional hazard analysis (FHA) and grey system theory to analysis and evaluate the class that each failure belongs to.Design/methodology/approachThis paper integrates multiple methods including the FHA, the fixed weight cluster, the Delphi method and the analytic hierarchy process (AHP). To begin with, use FHA method to sort out the corresponding failure states of a certain system from the perspective of function and determine the evaluation index. And then using group decision and AHP, determine the expert weight and index weight in the fixed weight cluster. The fixed weight cluster function is used to determine the grey class to which a certain functional failure belongs in the complex system.FindingsIn the past, the risk assessment of aircraft was mostly dominated by the subjective judgment of the experts, but it was not possible to give an objective observation score for each failure state. This paper addresses the problem efficiently as well as the feature of “little data, poor information.” The risk degree of each failure state can ultimately be replaced by a quantitative value.Research limitations/implicationsThis paper uses the idea of clustering in grey system theory to evaluate the risk of landing gear system. In the expert evaluation stage, different experts evaluated the impact degree of the aircraft's failure caused by its functions, so the final risk classification is subjective to some extent.Practical implicationsThis study analyzed the different conditions of the landing gear, including the front wheel steering, front wheel damping, front wheel steering system, brake system fault information and so on. It can effectively divide the different failure states and their effects, which is helpful to improve the safety of aircraft landing gear system and provide some useful methods and ideas for studying the safety of aircraft systems.Social implicationsBased on the FHA analysis process and the grey system theory, this paper determines various potential risks and their consequences of various functions according to the hierarchy, so as to carry out further detailed analysis on the risks that may occur under various functional conditions and take certain measures to prevent them. It is helpful to improve the risk management and control ability of aircraft in the actual flight process and to guarantee the safety of people's lives and property.Originality/valueThis paper is a pioneer in integrating the FHA method and the grey system theory, which exactly can be used to address the problem with the character of “little data, poor information.” The model established in this paper for the defects of FHA can effectively improve the accuracy of FHA, which is of great significance for the study of safety. In this paper, a case about landing gear system is given to illustrate the effectiveness of the model.
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Polyakov, Nikolai, Anna Solovyeva, and Vladimir Tselischev. "CONCEPT OF POWER TRANSFER UNITS DEVELOPMENT IN CIVIL AIRCRAFT HYDRAULIC SYSTEM." Perm National Research Polytechnic University Aerospace Engineering Bulletin, no. 67 (2021): 5–15. http://dx.doi.org/10.15593/2224-9982/2021.67.01.
Анотація:
There is a need to ensure a high level of safety of the aircraft's flight, in particular with regard to the redundancy of the hydraulic system. However, the introduction of additional hydraulic circuits entails, in addition to the advantages and many disadvantages, such as increasing the complexity and weight of the hydraulic system. One of the compromises in this situation was the installation of a power transfer unit. In this article, schematic solutions and peculiarities of operation of power transfer units, cases of their use are considered. An analysis of the current problems and possibilities of improving such aggregates is presented. Possible directions of further development of power transmission units have been identified. In particular, the directions for increasing pressure, reducing the gas content of the liquid, using pump power regulators, reducing gaps, reducing noise and temperatures, and introducing an intelligent component are highlighted. Possibilities for installation of power regulators, their various circuit solutions and operating principles are described. The characteristics of regulators , the operation of which is based on the principle of load sensitivity, the possibility of using these regulators to optimize the operation of the power transfer unit, and, therefore, increase the accuracy, stability, controllability of the entire hydraulic system of the aircraft are presented.
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Фомичов, Петро Олександрович, Тетяна Сергіївна Бойко та Олександр Олександрович Севостьянов. "Метод расчета усталостного повреждения регулярных зон крыла самолета при случайном нагружении на этапах типового полета". Aerospace technic and technology, № 3 (27 травня 2021): 13–23. http://dx.doi.org/10.32620/aktt.2021.3.02.
Анотація:
In accordance with the airworthiness standards, the aircraft structure must be operationally survivable, it means that structure must be able to remain efficiency in the presence of admissible damage. But, accumulating above than a certain level, damages cause fatigue failure of the structure, in the form of micro- and submicrocracks, thus reducing its strength characteristics. Currently, several approaches have been formed to ensure the safety of an aircraft structures in terms of strength. One of them is ensuring a safe resource (safe durability). This principle implies that during the specified service life of the product, no damage will occur in it, reducing the strength below the permissible level. The aircraft resource is limited “from above” by the durability of the regular zones of airframe. Therefore, predicting the durability of an aircraft wing structure at the design stage is a fundamental engineering problem to ensure its safety and economic efficiency. At the same time, the first step in dealing with aircraft fatigue damage at the design stage is the collection and assessment of the operational loads of the analog aircraft. However, at the design stage of a new aircraft model, obtaining such data is not always possible. Therefore, the purpose of this article is to develop a method for calculating fatigue damage at the stage of cracking and assessing the durability of regular zones of a transport aircraft wing, taking into account the conditions of its operation. The tasks to be solved are: to isolate the factors that determine the durability of the aircraft at flying in turbulent air; to take into account the asymmetry of loads and accumulated damage that occurs at each stage during the entire flight of the aircraft; to determine the aircraft's resource depending on the profile of a typical flight. The method is based on a standardized atmospheric turbulence model, typical flight profiles, fatigue characteristics of materials, the hypothesis of linear summation of damages and calculation based on nominal stresses. As result, comparison between the calculated integral repeatability of overloads and equivalent bending moments with the results of processing flight test data showed good agreements. Conclusions. The scientific novelty of the work lies in the fact that a method for calculating the fatigue damage of the regular wing zones, taking into account the expected flight profile of the aircraft was developed. This means that the proposed method makes it possible to carry out a preliminary assessment of the resource when designing an airplane without using data on the operational loads of an analogue airplane, and also estimate the residual resource of the airplane during its operation.
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Lamb, Richard, and Amanda Kavner. "Peripheral Eye Tracking for Measurement of Military Pilot Performance." International Journal of Psychology and Neuroscience 9, no. 2 (August 31, 2023): 110–15. http://dx.doi.org/10.56769/ijpn092010.
Анотація:
Abstract Flying plays a crucial role in establishing both tactical and strategic superiority through direct engagement, facilitating logistics movement, and providing other essential supports. However, a concerning trend has been observed regarding pilot flight time, which has decreased from approximately 300 hours per year to 230 hours per year. This decline could potentially impact flight safety and training, particularly in situations requiring rapid decision-making. One of the critical factors affecting rapid decision-making is a pilot's ability to closely monitor the aircraft's systems and flight path. The objective of this paper is to review and synthesize a series of studies that investigated the impact of peripheral gaze behavior on flying performance. Pilots can process peripheral eye gaze information more quickly and effectively, and peripheral eye movements could be used to activate controls faster than typical motor reflexes. Mathematical models of visual attention related to peripheral eye tracking have proven to be valuable predictive tools for human-machine interfaces and can lay the groundwork for improved training of pilots. Understanding gaze behavior offers valuable insights into the human-machine interface in modern cockpits. Keywords: Peripheral eye tracking, Pilot decision making, Human-machine teaming.
29
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 (November 29, 2023): 1005. http://dx.doi.org/10.3390/aerospace10121005.
Анотація:
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.
30
Kushwaha, Dinesh Kumar, Mark Volner, Shih‐Yih (Ryan) Young, and Sebin K. Kottackal. "Neural Network‐based Method to Compute Recommended Cruise Level and Optimal Climb Location." INCOSE International Symposium 33, S1 (December 2023): 120–34. http://dx.doi.org/10.1002/iis2.13119.
Анотація:
AbstractSystem engineering towards utilizing machine learning solutions in the aviation domain is a fast‐progressing discipline. This paper tries to bring out the system engineering and implementation aspects of ML solution as an improvement in a sub‐system of an existing aviation system. The flight management systems (FMSs) compute the recommended cruise level (RCL) considering the aircraft's gross weight, its speed schedule, and the forecast wind. The RCL increases with distance in the no wind conditions as the fuel get consumed, reducing the gross aircraft weight. The RCL profile may have frequent climbs and descents in the presence of winds, which is not desired for flight operations.The document proposes a neural network‐based method for computing an operationally acceptable cruise profile considering the wind and temperature weather forecast. The method recommends step climbs and step descents (optimal level and optimal step location) in such a way that they are separated by a large enough cruise phase. From system engineering point of view two guiding documents for such an implementation to look forward are “EASA Concept Paper: First usable guidance for Level 1 machine learning applications” [12] and “Process Standard for Development and Certification/Approval of Aeronautical Safety‐Related Products Implementing AI” [13].Two neural networks have been created to estimate wind compensated ECON cruise speeds and required time‐fuel to cover the next 500NM distance. The RCL profiles are generated for various test wind scenarios for Airbus A220 aircraft. It has been recorded the proposed neural network‐based method is better at recommending a cruise altitude and it is 9X faster than the existing method to calculate the RCL and optimal climb location. The neural network‐based design also helped in reducing the memory footprint by more than 100 times as there is no requirement of storing the performance database files required by the existing system. Only the parameters of the trained neural networks are required to be stored. Most importantly, the RCL computed by the proposed neural network‐based method yields a smaller operational cost than that determined by the existing method. The proposed method is designed to replace the existing traditional subsystem to give an overall improved performance while the functionalities of other subsystems remain unaffected.
31
Šlihta, Mareks, Vladimirs Šestakovs, and Ramachandran Karunanidhi. "Aircraft Automatic Control System Failure and Flight Safety." Transport and Aerospace Engineering 3, no. 1 (December 1, 2016): 15–23. http://dx.doi.org/10.1515/tae-2016-0002.
Анотація:
Abstract This article presents a mathematical model estimating the probability of successful completion of the aircraft’s flight in case of aviation equipment failure in flight. This paper shows the relationship between the aircraft’s automatic control system and flight safety. The calculations of probability are made for the successful completion of the flight on Boeing 737 aircraft when the automatic control system has failed.
32
Chu, Tang, Li Zhongyang, and Wang Libo. "Research on safety issues and safety analysis of new energy aircraft." Journal of Physics: Conference Series 2633, no. 1 (November 1, 2023): 012006. http://dx.doi.org/10.1088/1742-6596/2633/1/012006.
Анотація:
Abstract As the global aviation industry faces increasing pressure on the environment, the International Civil Aviation Organization (ICAO) has implemented increasingly strict requirements for aircraft carbon emissions. The adoption of innovative energy technologies, such as electric power, hydrogen fuel, and sustainable biofuels in the aviation sector, will enable us to achieve zero carbon emission targets and mitigate environmental pollution associated with air transportation. Drawing on statistical data of aviation accidents, this paper analyses the primary causes of flight mishaps and summarizes several safety issues faced by new energy aircraft. Based on these, the new energy aircraft is divided into several subsystems, including power system, energy system, flight control system and so on. Then, safety analysis tools and methods are then used to conduct an analysis of the aircraft’s safety, with the aim of improving overall safety.
33
Kashirskiy, Dmitriy Yurievich, and Aleksandr Vladimirovich Sukhomlinov. "Law Enforcement Agencies' Repression of the Unlawful Use of Unmanned Aircrafts." Полицейская деятельность, no. 2 (February 2022): 20–29. http://dx.doi.org/10.7256/2454-0692.2022.2.37789.
Анотація:
The subject of the study is the peculiarities of legal regulation of piloting (operation) of unmanned aircrafts. As example of such legal regulation author studied the legislation of the Russian Federation as well as the legislation of other countries. The object of the study is the conditions under which the piloting of such aircrafts is permitted from the point of view of flight safety. The authors consider in detail such aspects of the topic as possible undesirable consequences of the use of unmanned aircraft. Particular attention is paid to the consequences that may occur in the case of malicious use of this aircrafts for criminal purposes, namely during the transportation of drugs, interception of valuable cargo, interception of traffic information flows, intentional or accidental injury to people. The study presents the main problematic issues that need to be addressed by legislation. The main contribution of this study is detection of the problematic issues that need to be addressed by Russian legislation as well as by the norms of international law in terms of ensuring flight safety in all its manifestations. A special contribution of the authors of the research is a practical overview of the main safety threats caused by the use of the unmanned aircrafts. The novelty of the research lies in the systematization of these threats (especially personnel training for remotely piloted aircraft flaws). This scientific work can be considered as a set of measures to improve safety during the operation of unmanned aircraft.
34
Luo, Sai. "Discussion on Continuous Airworthiness and Maintenance of Civil Aircraft." Journal of Electronic Research and Application 6, no. 1 (January 18, 2022): 1–4. http://dx.doi.org/10.26689/jera.v6i1.2804.
Анотація:
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.
35
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.
Анотація:
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.
36
Liu, En Yu, Xiang Min Guan, Xue Jun Zhang, and Jie Zeng. "Conflict Resolution Based on Cooperative Coevolutionary with Dynamic Grouping Strategy for Multi-Aircraft." Applied Mechanics and Materials 333-335 (July 2013): 1251–55. http://dx.doi.org/10.4028/www.scientific.net/amm.333-335.1251.
Анотація:
Conflict resolution problem (CRP) plays a crucial role in the guarantee of safety. This paper formulates CRP as a multi-agent path planning problem which aims to find optimal paths for aircrafts. An algorithm named CCDG is proposed to tackle it based on cooperative coevolutionary (CC) with a dynamic grouping strategy for aircraft. CCDG makes aircraft divided into several equal sub-groups according to the dynamic grouping strategy. Each sub-group can adopt an evolutionary algorithm (EA) to optimize the aircrafts paths fully distributed and in parallel. Optimal solution is obtained through cooperation and coordination with all sub-populations. Empirical studies using extremely scenario adopted by previous research show that CCDG outperformed the existing approach (the fast GA), and the popular path planner that each aircraft uses an EA. Moreover, CCDG succeed to improve the airspace safety and reduce cost for CR.
37
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.
Анотація:
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.
38
Kulik, A. A. "Development of a Method for Computation of Aircraft Safety Control Signal." Mekhatronika, Avtomatizatsiya, Upravlenie 21, no. 11 (November 4, 2020): 656–62. http://dx.doi.org/10.17587/mau.21.656-662.
Анотація:
The optimal flight safety management of an aircraft is considered, on the basis of which the signal for parrying the threat of an aviation accident is calculated. In the process of analyzing the factors affecting the flight safety of the aircraft, the psychophysical state of the crew, the serviceability of the aircraft’s onboard equipment and the flight weather conditions are separated into separate groups. Based on the performed analysis, a target function of aircraft flight safety management is proposed in the form of a maximum, which is provided by the output signal of the aircraft flight safety management system. The calculation of the control signal is based on a count state of the flight conditions of the aircraft, which allows us to estimate the causal relationship of the factors of threat of the accident, and to determine the control signal with the safety of the vessel. In the course of this work, an algorithm for calculating the aircraft safety control signal has been developed. The results obtained during the work can be used for software and hardware implementation of aircraft flight safety management systems, as well as for the design of systems and complexes of its onboard equipment.
39
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.
Анотація:
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.
40
Luo, Lin Yin, Yan Bin He, Xuan Liu, and Xiao Hu Yao. "Dynamic Behavior on Emergency Landing of Light Aircraft with Occupant Restraint System." Advanced Materials Research 591-593 (November 2012): 2513–17. http://dx.doi.org/10.4028/www.scientific.net/amr.591-593.2513.
Анотація:
In the case of aircraft emergency landing, occupants’ safety analysis and research is one of the indispensable links in the verification of airworthiness safety. However, traditional experimental methods is time-consuming, complex and costly, seriously affect the development of new models to market. This paper established a finite element model of the full-size aircraft cockpit according to a certain type of amphibious light aircraft, and adding the dummy and safety belt occupant restraint system finite element model on this basis. In accordance with the requirements of CCAR-23 test conditions, using large dynamic finite element analysis software LS-DYNA numerical simulation was processed to study this aircraft’s emergency landing procedure. This paper investigated the dynamic response of the dummy and head injury criterion (HIC) value etc. The results provide certain reference for aircraft emergency landing safety design.
41
Fu, Yueshuai, and Huimin Fu. "A Novel Individual Aircraft Life Monitoring Method Based on Reliable Life Consumption Assessment." Machines 11, no. 11 (November 8, 2023): 1016. http://dx.doi.org/10.3390/machines11111016.
Анотація:
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.
42
Vladimirov, Y. "PROGRESS BEYOND THE CLOUDS AND METAMORPHOSIS OF TIME." World of Transport and Transportation 16, no. 5 (October 28, 2018): 272–76. http://dx.doi.org/10.30932/1992-3252-2018-16-5-18.
Анотація:
For the English full text of the article please see the attached PDF-File (English version follows Russian version).Sobolev, Dmitry A. The history of development of passenger aircrafts (1910-1970s): To the 100th anniversary of civil aviation. Moscow, «Russkie Vityazi» Foundation, 2018, 264 p. ABSTRACT The book is devoted to the history of development of passenger aircrafts from the beginning of their appearance until the mid-1970s. The book tells how the first passenger aircrafts appeared and civil aviation became more and more in demand, which was intended to master the previously inaccessible long-distance routes, to turn into an independent powerful mode of transport, with its specific infrastructure, intercontinental transportation system, and the rapidly developing aircraft industry. The main stages and vectors of development of civil aircrafts are traced, evolution of their design, technical and economic characteristics is shown. The author focuses particularly on the growing level of comfort and safety of passenger aircrafts from the beginning of the commercial use of airlines. The work is intended for a wide range of people interested in the history of aviation. Keywords: history of civil aviation, passenger aircraft, stages of formation, transportation market, progress in aircraft construction, leading countries.
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Anna Polanecka. "Determination of Laser Attack Risk Zones Under Aircraft Flight Path." Journal of Electrical Systems 20, no. 5s (April 13, 2024): 828–36. http://dx.doi.org/10.52783/jes.2329.
Анотація:
This paper introduces a method of determination of zones around and beneath an aircraft’s flight path where it is reasonable to believe that a laser attack would be successful, i.e. from where a laser beam pointed towards an aircraft can reach the eye of the pilot and lead to a potential safety risk. The method is based on the determination of lines of sight led from the ideal pilot eye position as recommended by the aircraft’s manufacturer and a simplified model of aircraft windows derived from aircraft technical drawings published by the manufacturer. The paper demonstrates the change of the shape of these zones and the distance between the aircraft and the emitter as a function of the aircraft’s pitch, allowing the zones to be adjusted according to the targeted area to be protected such as the final approach path or the intermediate approach segment. The use of such a method is demonstrated on a sample application of determination of such zones at 2500 ft above terrain, a height representing the transition from the intermediate approach segment to the final approach descent.
44
Suprapto, Ready Kresna Nanda, and Lasinta Ari Nendra Wibawa. "Desain dan Analisis Tegangan Rangka Alat Simulasi Pergerakan Kendali Terbang Menggunakan Metode Elemen Hingga." Jurnal Teknik Mesin ITI 5, no. 1 (March 12, 2021): 19. http://dx.doi.org/10.31543/jtm.v5i1.559.
Анотація:
Alat simulasi pergerakan kendali terbang merupakan alat peraga untuk menunjukkan mekanisme kerja dari sayap dan ekor pesawat terbang yang mendekati kenyataan. Alat ini bertujuan sebagai metode pembelajaran bagi calon pilot sebelum mengendarai sebuah pesawat terbang. Penelitian ini bertujuan untuk merancang dan menganalisis rangka alat simulasi pergerakan kendali terbang menggunakan metode elemen hingga. Analisis statik dilakukan menggunakan perangkat lunak SolidWorks 2017. Material rangka yang digunakan yaitu baja ASTM A36 dan ASTM A500 (square hollow section) dengan ukuran 50 x 50 x 1,2 mm dan 40 x 40 x 1 mm. Beban yang digunakan yaitu 375,25 kg yang merupakan beban sayap dan ekor pesawat. Hasil analisis menunjukkan rancangan rangka aman untuk menahan beban dinamis menggunakan baja ukuran 50 x 50 x 1,2 mm. Hal ini karena material ASTM A36 dan ASTM A500 untuk ukuran 50 x 50 x 1,2 mm memiliki faktor kemanan berturut-turut 2,162 dan 2,724. The flight control movement simulation tool is a visual aid to show the working mechanism of an airplane wing and tail close to reality. This tool aims as a learning method for aspiring pilots before driving an airplane. The study aims to design and analyze a flight control movement simulation frame using the finite element method. Static analysis was performed using SolidWorks 2017 software. The frame material used was ASTM A36 and ASTM 500 steel (square hollow section) with sizes of 50 x 50 x 1.2 mm and 40 x 40 x 1 mm. The load used is 375.25 kg, which is the weight of the aircraft's wing and tail. The analysis results show that a safe frame design to withstand dynamic loads uses 50 x 50 x 1.2 mm steel. The ASTM A36 and ASTM A500 materials for sizes 50 x 50 x 1.2 mm have a safety factor of 2.162 and 2.724, respectively.
45
Li, Hui Zhen, Yu Cai Dong, Jian Du, Bao Hong Lv, Lei Gong, and Ping Chen. "A Safety Evaluation Method of Military Aircraft Based on Projection Pursuit Method." Applied Mechanics and Materials 513-517 (February 2014): 4547–50. http://dx.doi.org/10.4028/www.scientific.net/amm.513-517.4547.
Анотація:
This paper focuses on the current development of military aircraft safety risk decision method is not enough application of projection pursuit method to calculate the weights of the evaluation indexes of a military aviation, comprehensive evaluation of different layout scheme. The available schemes were quickly ranked by their safety performance, the difficult problem with safety design of military aircrafts was primarily solved in the aeronautic project.
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Kim, Young-Cheol, Dong-Hyeop Kim, and Sang-Woo Kim. "Evaluation of the Multiaxial Fatigue Life of Electro-Mechanical Actuator for Aircraft Blade Pitch Control Based on Certification Standards." Aerospace 11, no. 1 (January 18, 2024): 91. http://dx.doi.org/10.3390/aerospace11010091.
Анотація:
To achieve the commercialization of electric vertical takeoff and landing (eVTOL) aircrafts, which have recently garnered attention as the next-generation means of transportation, objective certification based on rigorous procedures is essential. With the advancement of structural analysis technology, aircraft airworthiness standards recommend a combination of testing and analytical methods to demonstrate structural integrity. In this study, we propose analytical techniques for demonstrating the structural integrity of components for eVTOL aircrafts in accordance with airworthiness standards. We evaluated the static structural integrity and fatigue safety of an electro-mechanical actuator. Multibody dynamics analysis was performed to calculate the loads for application in finite element analysis. Subsequently, static analysis and fatigue analysis based on finite element analysis were conducted to calculate the safety margin and fatigue life of all key components. Therefore, we have confirmed the feasibility of utilizing analytical methods for the structural integrity assessment of aircraft components. We propose the utilization of the technique introduced in this study as one of the approaches for demonstrating compliance with airworthiness standards for eVTOL aircrafts through the application of analytical methods.
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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 (December 19, 2022): 848. http://dx.doi.org/10.3390/aerospace9120848.
Анотація:
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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Ni, Junfei, and Xiaoyan Qi. "Research on pipeline stress test method of civil aircraft hydraulic system." Journal of Physics: Conference Series 2691, no. 1 (January 1, 2024): 012040. http://dx.doi.org/10.1088/1742-6596/2691/1/012040.
Анотація:
Abstract The hydraulic system is an important component of the aircraft, whose performance status directly affects the aircraft’s flight safety, and aircraft hydraulic system piping is the main component of the hydraulic system. In the development process, civil aircraft must be tested and analyzed on the hydraulic system piping vibration and stress. This paper takes the hydraulic system pipeline of civil aircraft as the research object, carries out the research of pipeline stress test method, and provides the stress test method and reliable test data for verifying whether the design of the hydraulic system pipeline is reasonable.
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Xiao, Chuan, and Jun Hong Feng. "Analysis of Localizer Over-Bending at Coastal Airport." Applied Mechanics and Materials 568-570 (June 2014): 1865–68. http://dx.doi.org/10.4028/www.scientific.net/amm.568-570.1865.
Анотація:
Inaccurate alignment with the runway centerline caused by localizer over-bending, will make the aircraft’s approach unstable, and hinder the timely and correct establishment of landing configuration, even threat the safety of aircraft. Targeting at the problems above, and according to the actual operational circumstance of coastal airport ,this paper, based on the performance specification of instrument landing system and character analysis of localizer over-bending at coastal airport, presents the relationship between localizer bending extent and the distance from the runway centerline to the coastline. Meanwhile, corresponding mathematics model is built and related simulations have been done, which effectively enhance the crew’s situation awareness of localizer over-bending and improve the aircraft’s landing safety at coastal airport.
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Liao, Yong, and Na Zhai. "Research on Mechanical Operation with Sequencing Optimization of Arrival Aircraft in Terminal Area." Applied Mechanics and Materials 345 (August 2013): 404–7. http://dx.doi.org/10.4028/www.scientific.net/amm.345.404.
Анотація:
In order to ensure flight safety and efficiently sequence arrival aircrafts in terminal area, a sequencing model for scheduling the sequence of arrival aircrafts in the terminal area was discussed. Model's objective is minimizing the loss of delays due to meeting separation which is used to keep the safety of aircrafts before and afterwards. Then the model is transferred to pure integer nonlinear program model so that the model can be solved by some program software like Lingo. At last, a numerical example is used to illustrate the process of solving the model. The numerical example shows that the model proposed in this paper is extremely efficient in scheduling the sequence of arrival flights compared with the FCFS (first come first served) algorithm and model used for the aircraft sequencing in the terminal area is feasible.