Zeitschriftenartikel: „Aircraf“

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Suharyadi, Suharyadi, und Yudhistira Tri Nurteisa. „Teknologi Pesawat Tanpa Awak untuk Pemetaan Skala Detail Rencana Jaringan Pipa Sanitasi Komunal bagi Masyarakat Dusun Kepek 1, Kepek, Wonosari, Gunungkidul“. Jurnal Pengabdian kepada Masyarakat (Indonesian Journal of Community Engagement) 2, Nr. 1 (16.02.2017): 1–13. http://dx.doi.org/10.22146/jpkm.22081.

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Human settlements can not be separated from the emergence of waste generated by human activity. Waste will give a negative efect on health and the environment if not handled and managed properly. Hamlet Kepek 1, Kepek, Wonosari have realized the impact that arises when household waste is not managed properly. For that, some residents have initiated a communal waste management and manufacture of communal sanitation pipelines. Conventionally, communal sanitary pipe network planning and data requires a huge cost, for it takes breakthrough of utilization of appropriate technology to facilitate the planning process and reduce the cost incurred.Utilization of small format aerial photographs resulting from the unmanned aircraf vehicle (UAV) used as an alternative technology in the planning communal sanitation pipelines. Analytical methods to create a map of the communal sanitation pipelines through least cost path analysis. Utilization of UAV technology is expected to make the planning of communal sanitary pipelines with good results and at afordable costs. Te result of small format aerial photography from unmanned aircraf vehicle (UAV) can be used to produce the spatial data with high resolution. Small format aerial photographs produced is then processed to obtain the orthophoto image and the image of Digital Surface Model (DSM). Both kinds of remote sensing image are then used as the main data to create maps of the communal sanitation pipelines. Te result of processing in the form of a map of communal sanitation pipelines in t Kepek 1 at low cost and appropriate technology.

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Al Wardi, Yousuf, Sasirajan Jeevarathinam und Saleh Al Sabei. „A Cross-Cultural Anthropometric Analysis in Military Aviation“. Aerospace Medicine and Human Performance 91, Nr. 4 (01.04.2020): 358–62. http://dx.doi.org/10.3357/amhp.5530.2020.

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BACKGROUND: Aircrew-aircraft compatibility is important in military aviation for flight safety. Anthropometric aircrew selection standards in RAFO were embedded from the selection standards of western defense forces as the aircrafts were imported from there. Henceforth efforts were made to fit local native aviators into aircrafts not initially designed for them. In view of this, this study was carried out to obtain the anthropometric data of Oman aircrew recruits and compare these with published western and eastern data with a hope to understand and highlight the aircrew-aircraft mismatch issues, if any.METHODS: The anthropometric data of 2296 Omani recruits from 2003 to 2012 were collected and their statistical distribution of data was collated. Published data from the UK and Singapore were used to carry out the comparative distribution of five anthropometric dimensions.RESULTS: Minimal differences were noted between Oman and Singaporean recruits whereas differences were most pronounced between Oman and Western populations (UK). Aircrew cadets from Oman, Singapore, and UK differed significantly in standing height. The UK cadets (M = 177.4 cm) showed the highest standing height followed by Oman cadets (M = 171.9cm), and then Singapore cadets (M = 168.5 cm).DISCUSSION: This study has provided opportunities to recognize the discrepancies involved in selection of Middle Eastern aircrew for western cockpits. This adds impetus to the scope for application of military recruitment standards suitable to the native population in aiding the ideal man-machine interface. This approach shall consider national policy, the significant anthropometric trends of the general population, and the procured aircraft profile of the country.Al Wardi Y, Jeevarathinam S, Al Sabei S. A cross-cultural anthropometric analysis in military aviation. Aerosp Med Hum Perform. 2020; 91(4):358–362.

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Biswal, P., und YS Dahiya. „Principal component analysis: The path ahead for aircrew-aircraft compatibility at the Institute of Aerospace Medicine“. Indian Journal of Aerospace Medicine 63 (07.11.2019): 8–15. http://dx.doi.org/10.25259/ijasm_2019_3.

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Introduction: The Institute of Aerospace Medicine provides design consultancy on aircraft-aircrew compatibility on a number of fixed-wing as well as rotary-wing aircrafts during various stages of development. Till date, the cockpit compatibility of aircrew has been determined based on the percentile concept. Percentiles, though useful when dealing with a single parameter, pose major design and fitment problems when considering multiple parameters simultaneously as in aircraft cockpit design. The concept of multivariate analysis has been the solution which the aviation industry the world over has accepted in overcoming this problem. This paper presents the Institute of Aerospace Medicine initial foray into the field of multivariate analysis, specifically principal component analysis (PCA) to achieve desired aircrew fitment in the aircraft cockpit right from the design stage. Materials and Methods: The fighter aircraft of the near future is being designed using the anthropometric parameters available in the IAF aircrew anthropometry survey 2013. Of the 57 parameters available, six parameters critical to the design of the cockpit were subject to PCA to derive three principal components. About 96% confidence ellipse was drawn on the plot of the principal components. From this, along the different axes, 21 boundary individuals were identified defining the extreme individuals in various combinations of the six parameters. Discussion: The use of more than 2 parameters is not amenable to sequential use of percentiles. As the number of parameters considered increases, it leads to reduced fitment percentage. The use of PCA allows consideration of critical parameters together at one go. The design aim is changed from the 3rd to 97th percentile to an overall aim of fitting 96% of the target population in the cockpit. The boundary individual’s entire anthropometry data are used to create boundary manikins for use in computer-aided design models. The fitment of these boundary individuals ensures that if these individuals fit, all others would fit in the cockpit. This concept brings about a paradigm shift in the aircrew-aircraft compatibility in the aviation industry in India.

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Lewitowicz, Jerzy, und Stefan Rutkowski. „Research of the Reliability of an Air Combat Manoeuvere – Nosedive of a Jet Powered Aircraft / Badanie Niezawodności Lotniczego Manewru Bojowego – Lotu Nurkowego Samolotu Odrzutowego“. Journal of KONBiN 31, Nr. 1 (01.12.2014): 13–22. http://dx.doi.org/10.2478/jok-2014-0019.

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Abstract This paper considered a problem of: the reliability of performance of a nosedive of a jet powered aircraft in the context of the ability of pilots trained on a simulator to reliably accomplish a combat mission. For research purposes, the manoeuvre of attack of a target with the nosedive, which is most commonly used by the pilots performing flights on different types of modern aircrafts, and the basic manoeuvre during aircrew training, both basic and advanced were assumed. The research was conducted on a flight simulator.

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Fujita, Etsushi, Taichi Higashioka, Manabu Sugiura und 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 (01.08.2021): 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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Zhang, Yuhang, Hao Sun, Jiawei Zuo, Hongqi Wang, Guangluan Xu und 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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Zuo, Yu Yu. „Analysis of Gas Turbine Engines Auxiliary Power Units“. Applied Mechanics and Materials 533 (Februar 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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Wang, Hong Yong, Rui Ying Wen und Yi Fei Zhao. „Empirical Research on Topological Characteristics of Air Traffic Situation Network“. Applied Mechanics and Materials 744-746 (März 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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Yao, Man. „Water Impact Analysis for Aircraft over Sea“. Applied Mechanics and Materials 341-342 (Juli 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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Zhao, Chang Jun, Yue Bai, Xun Gong, Dong Fu Xu und Zhi Jun Xu. „Control System Design of a Hex-Rotor Aircraft Based on the Neural Network Sliding Mode Method“. Advanced Materials Research 971-973 (Juni 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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Zhaohui, Ming, Zhang Ming, Tang Xinmin und 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 (01.12.2015): 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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Li, Jun, Wei Yang und Yang Pei. „Vulnerability Assessment for Fire and Explosion Suppression Measures of Aircraft Fuel System“. Advanced Materials Research 510 (April 2012): 64–69. http://dx.doi.org/10.4028/www.scientific.net/amr.510.64.

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Fuel system is the most vulnerable system on fixed wing aircraft. When penetrated by threat propagators, it is liable to be damaged by combustion and explosion. Thus, fire/explosion suppression for fuel system are important measures to improve the aircrafts survivability. In this paper, the whole aircraft vulnerability model which consists of aircraft configuration, structure, and systems is constructed by CATIA software, the basic steps for vulnerability quantitative computation are descried, and the computing formulas of three kill modes are presented. The vulnerability of one aircraft 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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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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Zhang, X., B. Xiong und 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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Gao, Feng, Qizhi Xu und Bo Li. „Aircraft Detection from VHR Images Based on Circle-Frequency Filter and Multilevel Features“. Scientific World Journal 2013 (2013): 1–7. http://dx.doi.org/10.1155/2013/917928.

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Aircraft automatic detection from very high-resolution (VHR) images plays an important role in a wide variety of applications. This paper proposes a novel detector for aircraft detection from very high-resolution (VHR) remote sensing images. To accurately distinguish aircrafts from background, a circle-frequency filter (CF-filter) is used to extract the candidate locations of aircrafts from a large size image. A multi-level feature model is then employed to represent both local appearance and spatial layout of aircrafts by means of Robust Hue Descriptor and Histogram of Oriented Gradients. The experimental results demonstrate the superior performance of the proposed method.

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Chenguang, Yang, Liu Hu und 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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Sutiawan, Sutiawan, Dena Hendriana, Hanny J. Berchmans, Henry Nasution und Gembong Baskoro. „Design and Analysis of Warning System for Aircraft Wingtip Proximity to Hangar Column using Ultrasonic Sensor“. Proceedings of The Conference on Management and Engineering in Industry 2, Nr. 1 (23.11.2020): 7–10. http://dx.doi.org/10.33555/cmei.v2i1.33.

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Aircraft maintenance is using very large hangar as a place to work on the aircrafts and the hangar can fit several aircrafts at the same time. The aircrafts are moved using tow cars in and out of the hangar. The hangar is so big that it requires columns for its structure and these columns present risk to the aircrafts for having wingtip collitions during towing in and out of the hangar. In this study, warning system for aircraft wingtip proximity to the hangar columns is designed. This warning system is using ultrasonic sensors attached to the columns and controlled by Arduino micro processor and wirelessly connected as Internet of Things system to warn the driver of the tow car. The ultrasonic sensors are placed in the columns based on dimension and elevation of 2 different most common aircraft wingtips to get effective column warning system. The speed of tow car affects the driver time to response the warning and based on calculations and experiments, the tow car driver should have enough time to respond the warning system.

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Kim, Min-Seong, Byung Hyuk Kwon und 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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Xiao, Xian Bo, Xiang Jun Kong, Ya Jie Shi und Si Yuan Yao. „Jet Blast Resistance Experiment of Engineered Material Arresting System“. Advanced Materials Research 750-752 (August 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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Fang, Jie, und Hong Shan Xia. „Aircraft Dynamic Scheduling Algorithm Research Based on Heuristic Column Generation Algorithm“. Applied Mechanics and Materials 411-414 (September 2013): 2364–68. http://dx.doi.org/10.4028/www.scientific.net/amm.411-414.2364.

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

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Wang, Jie Ning, Bin Bin Wang und Yuan Di Zhao. „A Probabilistic Algorithm to Medium-Term Conflict Detection with Multi-Waypoints“. Applied Mechanics and Materials 411-414 (September 2013): 2763–69. http://dx.doi.org/10.4028/www.scientific.net/amm.411-414.2763.

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To predict the potential conflict during the flight routes, a conflict detection approach based on multi-waypoints is presented. Aimed at the encounter geometry of two aircrafts with multi-waypoints, in order to simply the computational process, the aircrafts routes are divided into several straight conflict paths. Model along track kinematics equation of the aircraft by referencing to a classical conclusion that the along track error of the aircraft is normal distributed, consider an encounter between two aircrafts at the same flight level , construct an ellipse conflict region, by establishing a rectangular coordinate system represented aircraft position appropriately . First, propose a probability estimation algorithm of medium term conflict detection for cross routes at the same level, then analyze the relationship between the conflict probability and several factors based on various graphs. MATLAB result shows that the proposed algorithm is advanced in its simple calculation method, fast calculation speed and precise detection calculations.

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Wang, Zhipeng, Zhiqin Qian, Ziye Song, Hongzhou Liu, Wenjun Zhang und 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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Sun, Ji Ku, Zong Jie Cao, De Jian Sun und Yi Chen. „Characteristic of Corrosive Damages about Aircraft Structures in Service“. Applied Mechanics and Materials 543-547 (März 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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Kolanjiappan, S. „Innovative Approach in Introducing Lean Manufacturing Tools in Maintenance of Aircraft“. Applied Mechanics and Materials 766-767 (Juni 2015): 1190–95. http://dx.doi.org/10.4028/www.scientific.net/amm.766-767.1190.

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Lean manufacturing was initially introduced successfully in Japan to enhance the production standard of cars in Toyota Company. These lean principles were initially known as Toyota Production system (TPS)[2]. Lean seeks to eliminate all forms of waste in the manufacturing process—including waste in the maintenance operation[1].This present study about lean principles if could be introduced in maintenance of aircraft the standard of maintenance process could be significantly improved. Hence study of experimental research was carried out on pre-matured failure of lifed hydraulic components of ten aircrafts. The failure rate of each component was studied in-depth to adopt remedial measures for improving its life and in turn to reduce the period of “Aircraft on Grounds”. Aircraft on ground mean unserviceable aircraft will be on ground and not suitable for flying. In addition, a deep study was made on each component to fix a Time Between Overhaul (TBO) by analyzing the failure trend of each component to determine a common and effective TBO for enhancing the serviceability rate of aircrafts. It also prevents sudden failure of components thus improving the serviceability status. In order to enhance the standard of serviceability a “Root Cause Analysis”was carried out on those defective components to suggest remedial measures to those maintenance personnel to modify the maintenance process and reduce the TBO for effective reduction in time of occurrence of the defects. These suggestive measures were implemented by the users of the ten aircrafts on trial basis. Occurrence of such defects was minimized showing significant improvement in the subsequent maintenance of aircrafts. Further, the remedial measures have a great impact on the development of a high degree of aircraft maintenance. The final results of this research study are prepared and suggested measures are forwarded for implementation to manufactures, overhaul agency and operators.

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Heiselberg, Peder, und Henning Heiselberg. „Aircraft Detection above Clouds by Sentinel-2 MSI Parallax“. Remote Sensing 13, Nr. 15 (01.08.2021): 3016. http://dx.doi.org/10.3390/rs13153016.

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Detection of aircrafts in satellite images is a challenging problem when the background is strongly reflective clouds with varying transparency. We develop a fast and effective detection algorithm that can find almost all aircrafts above and between clouds in Sentinel-2 multispectral images. It exploits the time delay of a few seconds between the recorded multispectral images such that a moving aircraft is observed at different positions due to parallax effects. The aircraft speed, heading and altitude are also calculated accurately. Analysing images over the English Channel during fall 2020, we obtain a detection accuracy of 80%, where the most of the remaining were covered by clouds. We also analyse images in the 1.38 μm water absorption band, where only 61% of the aircrafts are detected.

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A., Armaan, und 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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Sakaue, Hirotaka. „Special Issue: Deicing and Anti-Icing of Aircrafts“. Aerospace 8, Nr. 3 (10.03.2021): 72. http://dx.doi.org/10.3390/aerospace8030072.

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Zieja, Mariusz, und Mirosław Zieja. „An economic aspect of shaping reliability and safety of the ‘pilot-aircraft’ system/Ekonomiczny aspekt kształtowania niezawodności i bezpieczeństwa systemu „pilot – statek powietrzny”“. Journal of KONBiN 20, Nr. 1 (01.12.2011): 175–84. http://dx.doi.org/10.2478/v10040-012-0045-1.

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Abstract An economic factor is what should be given careful consideration throughout the aircraft service process. This is what significantly adds to the question of aircraft utility value. Any aircraft of even exceptionally good engineering properties may show rather poor utility value if it proves extremely expensive while in operation. If significance of economic issues throughout the process of operating military aircraft remains underestimated, it may straightforward lead to false if not disastrous solutions. Rational decisions on increasing expenditures on improvement in the operational use of military aircraft are expected to result in: substantial increase in operational readiness of aircraft, significant increase in aircraft reliability, increase in the ratio of effectiveness for the operational use of aircraft. Any increase in the above-mentioned fundamental rates of aircraft operation will provide some rise in the level of safety for the aircrew.

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Lü, Zhi, Zhan Gao und Yi Lü. „A Flight Simulator that Grouping Aircrafts Simultaneously Take off and Land in Open Grid Computing Environment“. Applied Mechanics and Materials 182-183 (Juni 2012): 1292–97. http://dx.doi.org/10.4028/www.scientific.net/amm.182-183.1292.

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The performance of airplane in commercial airline environment is determined by, and therefore an indicator of performance measure of, the thermodynamic properties of airplane. The aim of this study was to establish the use of simulators to determine aircraft accident for a flight of airplanes and evaluate the potential of new airspace structure and airport’s runway. This indicates that there is a possibility of obtaining airplane performance from analysis and verification simulating airplane. As compared with AIRBUS Full Flight Simulator, a multiple aircrafts flight simulator that grouping aircrafts simultaneously take off and land was presented, which is basis on a parallel distributed computing in Open Grid Computing Environment (OGCE), and service oriented architecture (SOA) of software in multiple aircraft simulator, the performance of collaborative flight of multiple aircrafts is evaluated.

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Liu, En Yu, Xiang Min Guan, Xue Jun Zhang und Jie Zeng. „Conflict Resolution Based on Cooperative Coevolutionary with Dynamic Grouping Strategy for Multi-Aircraft“. Applied Mechanics and Materials 333-335 (Juli 2013): 1251–55. http://dx.doi.org/10.4028/www.scientific.net/amm.333-335.1251.

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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.

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Zhang, Yongjie, Kang Cao, Ke Liang und 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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Xiong, Zhuang, Hua Wen Zhou und Jia Yue Ren. „The Design and Application of Aircraft Flight Stimulation and Visualization Based on HLA“. Applied Mechanics and Materials 543-547 (März 2014): 3472–75. http://dx.doi.org/10.4028/www.scientific.net/amm.543-547.3472.

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Aircraft training simulator has integrated combat training ability not only needs to simulate the aircraft flight and radar, inertial navigation and avionics equipment, but also to generate realistic battlefield environment and visual effects, and to simulate the interaction between the system and the complex interaction. In the realization of the simulator, using HLA/RTI as its architecture and the supporting platform, make the device emulator is to achieve interoperability, can improve the system's flexibility and scalability. [ The target and the electromagnetic reflection characteristics of ground data and radar detection model based on the dynamic radar image generation. The blackboard model is based on the virtual machine technology, which is easy to modify and evolution of CGF system. [Combat aircraft is the main weapon platform in modern war, and aircrew training level is an important factor which affects the combat effectiveness of an aircraft. Research on the domestic and abroad aircrew training methods and training methods with simulate system, develops advanced technology, which can achieve close to actual combat to training effect and save a lot of training funds.

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NORMAN, C. „B-1's Problems Stir Debate on Bomber's Role: A new report on the controversial aircraf may rekindle an old debate over the merits of building bombers designed to strike deep into the Soviet Union“. Science 241, Nr. 4871 (09.09.1988): 1282–83. http://dx.doi.org/10.1126/science.241.4871.1282.

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Lei, Zhang, und Jing Yachao. „Research on Comprehensive Evaluation of Military Aircrafts’ Overhaul Performance Based on Entropy Weight and Cloud Model“. E3S Web of Conferences 257 (2021): 02065. http://dx.doi.org/10.1051/e3sconf/202125702065.

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Due to the complex evaluation of the current military aircrafts’ overhaul performance with many influencing factors, an evaluation index system of military aircrafts’ overhaul performance was constructed. It was proposed that the entropy weight method (EWM) was used to calculate the performance results, and then the performance of the reliability and validity of the results was verified based on the cloud model. By collecting the performance index data of a certain type of military aircraft overhaul from 2015 to 2018, the value of the overhaul performance of this type of military aircraft was calculated, and the feasibility and effectiveness of the method were verified.

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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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Olugbeji, Jemitola P., Okafor E. Gabriel und 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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Read, C. A. „Injuries sustained by aircrew on ejecting from their aircraft“. Emergency Medicine Journal 17, Nr. 5 (01.09.2000): 371–73. http://dx.doi.org/10.1136/emj.17.5.371.

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Folds, Dennis J., und Roderick A. Beard. „Aircrew Recommendations for Voice Message Functions in Tactical Aircraft“. Proceedings of the Human Factors Society Annual Meeting 32, Nr. 2 (Oktober 1988): 63–67. http://dx.doi.org/10.1177/154193128803200212.

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Results are presented from a survey of 135 active tactical aircrews regarding use of synthetic voice messages in tactical aircraft. The sample was primarily composed of F-16, F-15, and F-4 pilots. The participants rated 69 existing, proposed, or suggested functions for voice messages in tactical aircraft. Over two-thirds of the participants rated the following functions favorably: Engine Fire, Fuel Low, Oil Pressure, Hydraulic Pressure, Brakes Malfunction, Landing Gear Malfunction, Gear/Flaps Configuration, Low Altitude, Missile Launch, Threat Display, Bingo Fuel, and Joker Fuel. Other functions, applicable to some but not all tactical aircraft, received strong support from the aircrews of the applicable aircraft. The participants' responses to open-ended questions, concerning use of voice messages for checklists and desirable control features for voice message systems, are also summarized.

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Kalinowski, Miłosz. „Aero-Structural Optimization of Joined-Wing Aircraft“. Transactions on Aerospace Research 2017, Nr. 4 (01.12.2017): 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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Guettler, Norbert, Dennis Bron, Olivier Manen, Gary Gray, Thomas Syburra, Rienk Rienks, Joanna d’Arcy, Eddie D. Davenport und Edward D. Nicol. „Management of cardiac conduction abnormalities and arrhythmia in aircrew“. Heart 105, Suppl 1 (13.11.2018): s38—s49. http://dx.doi.org/10.1136/heartjnl-2018-313057.

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Cardiovascular diseases i are the most common cause of loss of flying licence globally, and cardiac arrhythmia is the main disqualifier in a substantial proportion of aircrew. Aircrew ii often operate within a demanding physiological environment, that potentially includes exposure to sustained acceleration (usually resulting in a positive gravitational force, from head to feet (+Gz)) in high performance aircraft. Aeromedical assessment is complicated further when trying to discriminate between benign and potentially significant rhythm abnormalities in aircrew, many of whom are young and fit, have a resultant high vagal tone, and among whom underlying cardiac disease has a low prevalence. In cases where a significant underlying aetiology is plausible, extensive investigation is often required and where appropriate should include review by an electrophysiologist. The decision regarding restriction of flying activity will be dependent on several factors including the underlying arrhythmia, associated pathology, risk of incapacitation and/or distraction, the type of aircraft operated, and the specific flight or mission criticality of the role performed by the individual aircrew.

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

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Phased implementation approach, namely three models: aircraft type distribution model, aircraft scheduling model, robustness model is used to achieve the optimization of aircraft scheduling robustness. Aircraft type distribution model is established to obtain the best model of each leg; then fleet scheduling model is established to determine specified type in the implementation of the specific aircrafts for each flight, flight strings, which meet the constraints, are obtained by solving; finally, the flight robustness model is established, that is, flight string with minimal impact is selected 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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FUĆ, Paweł, Monika KARDACH und Marta MACIEJEWSKA. „Analysis of the availability of aircrafts with alternative propulsions“. Combustion Engines 179, Nr. 4 (01.10.2019): 220–25. http://dx.doi.org/10.19206/ce-2019-437.

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Global air traffic doubles every 15 years. Therefore, aviation emission grows as well. It is advisable to look for an alternative aircrafts’ propulsion for both commercial and general aviation (usually flying closer to the ground). There are many prototypes proposed by homemade projects, through companies wanting to extend their offer. There are also several more advanced constructions ready to self-set or serially produced. In the article the main topic are electric aircrafts as an example of possibility to reduce the toxic compounds emission. According to the analysis some of companies specializing in unmanned aircraft production, starting to expand their business with manned products. In the article, analyses of electric aircrafts different models, which are available on market and presented the comparisons characteristics based on e.g. cruise speed, range for every model or charging time were made and conclusions about alternative aircraft propulsions, were made.

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Alestra, Stephane, Cristophe Bordry, Cristophe Brand, Evgeny Burnaev, Pavel Erofeev, Artem Papanov und Cassiano Silveira-Freixo. „Application of Rare Event Anticipation Techniques to Aircraft Health Management“. Advanced Materials Research 1016 (August 2014): 413–17. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.413.

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Generally faults in complex technical systems (such as aircrafts) can be considered as rare events. In this paper we apply classification techniques to problem of rare events anticipation and demon-strate the approach to predictive maintenance of aircrafts through the real-world test cases from aircraft operations based on the data granted by AIRBUS.

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Rigogiannis, Nick, Dionisis Voglitsis, Tiago Jappe und Nick Papanikolaou. „Voltage Transients Mitigation in the DC Distribution Network of More/All Electric Aircrafts“. Energies 13, Nr. 16 (10.08.2020): 4123. http://dx.doi.org/10.3390/en13164123.

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The objective of this paper is to present a power conversion system, based on a bidirectional DC/DC converter, along with a supercapacitor bank, that mitigates the voltage transients that occur on the DC distribution network of More/All Electric Aircrafts. These transients, such as voltage sags and swells appear on the DC buses of on-board microgrids, mainly due to load variations and are classified according to the aircrafts electric power system standards. First, we shortly describe an aircraft distribution network, that is applicable to the most common actual aircraft architectures, then we present the proposed system, along with the bidirectional DC/DC converter design, the control technique and the supercapacitor bank sizing. Finally, we present simulation and experimental results that support the effectiveness of the proposed system to effectively compensate voltage transients, supporting the DC buses in dynamic conditions. Concluding, the proposed system provides high power quality and compliance with the respective power quality standards for aircraft microgrids.

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Kachel, Stanisław. „Control Curves Method of Airframe Geometry Modeling“. Solid State Phenomena 199 (März 2013): 279–84. http://dx.doi.org/10.4028/www.scientific.net/ssp.199.279.

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The paper presents the methodological approach to development of curves by selection of driving parameters with the application of the method to designing and reproduction of aircraft surfaces on the examples of both newly designed aircrafts and the ones that are already in service. The major assumptions are outlined that are necessary to develop the mathematical model of driving curves and surfaces, these assumptions served as the basis to draw up the relevant algorithms and to convert them to routines of the GRIP (Graphics Interactive Programming) language that is a part of the CAD/CAM/CAE Unigraphics system. These algorithms include the newly developed tool dedicated to design aircraft components and provided with inputs to the multi-criteria synthesis of the aerodynamic profiles of aircrafts. The study comprises also the assumptions to the newly developed algorithms dedicated to modelling of components incorporated into aircraft structures, these algorithms have been successfully implemented by the author.

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Hew, Patrick Chisan. „Distributed Cognition Sheds Light on Munitions Trajectories in Close Air Support“. Ergonomics in Design: The Quarterly of Human Factors Applications 25, Nr. 2 (07.02.2017): 12–14. http://dx.doi.org/10.1177/1064804616675243.

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Close air support is characterized by aircraft delivering munitions onto ground targets. I applied Hutchins’s theory of distributed cognition to understand how the trajectories of munitions were specified. In the baseline case, the aircrew specifies the munitions’ entire trajectory. With alternative options enabled by information and communications technologies, the joint terminal attack controller (JTAC) specifies the munitions’ impact point, time on target, and even the direction and angle of impact. The desire to affect the trajectories increases the amount and specialization of equipment and training placed onto the JTAC, aircraft, and aircrew. The analysis was important to the people who advance and sustain the capabilities of close air support by identifying the effects that are desired and developing new and better ways of providing those effects.

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Bukhtiyarov, I. V., M. F. Vilk, V. D. Glukhovskiy, N. N. Kurierov, V. A. Kaptsov, V. B. Pankova und L. V. Prokopenko. „Updating the assessment methodology of the acoustic load of flight crew members in the cabins of civil aviation aircraft“. Russian Journal of Occupational Health and Industrial Ecology, Nr. 2 (21.02.2020): 100–116. http://dx.doi.org/10.31089/1026-9428-2020-60-2-100-116.

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The article discusses the issues of adjustment, developed in 2007 and supplemented in 2009, of the methodology for evaluating the equivalent level of cabin noise of civil aviation aircraft in Russia. The relevance of the problem is due to high levels of professional hearing loss among the aircrew members of the air force, which is directly related to the lack of unified and competent approaches to assessing the acoustic load on the hearing organ of the aircrew members. The updated methodology contains full-fledged data on noise levels in modern domestic and foreign airliners, data on certification of acoustic efficiency of aircraft accessories, a direct algorithm and formulas for calculating the noise load for the selected periods of flight operation.

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Janeba-Bartoszewicz, Edyta, und Adam Rojewski. „Analysis of hazards occurring during the use of hydrazine“. WUT Journal of Transportation Engineering 125 (01.06.2019): 37–43. http://dx.doi.org/10.5604/01.3001.0013.6493.

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The article presents the safety issue bonded to the Polish Air Force F-16 multirole aircraft. The authors pointed out the issue of fuel used for emergency supply system of these aircrafts. The paper emphasized the fact that these aircrafts require special fuel with designation H-70, which is 70% aqueous solution of toxic hydrazine. For this reason, the rescue services of Polish Air Force bases where Polish F-16 are stationed had to be adjusted accordingly. Just as importantly authors noticed that in the event of an emergency landing of this aircraft at different airports can receive difficulties associated with the possible leakage of hydrazine, or its neutralization in the absence of specialized Hydrazine Response Team, which are part of the Airport Rescue Group.

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Zhou, Hong, Zhan Xue Wang und Xiao Bo Zhang. „Areo-Engine Cycle Parametric Analysis and Installed Performance Calculation Based on Aircraft Flight Mission“. Applied Mechanics and Materials 482 (Dezember 2013): 277–81. http://dx.doi.org/10.4028/www.scientific.net/amm.482.277.

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The aircraft/engine integration design numerical simulation model was established. The engine design performance specifications were obtained by calculating aircraft lift-drag characteristics, mission analysis, constraint analysis. Combining engine cycle parametric analysis with installation loss computing, the engine performance parameters can be found, which meet the aircraft flight envelope performance requirements. Taking double bypass variable cycle engine as an example to check the model, the results show that the variable cycle engine can meet aircrafts thrust and fuel consumption demands under different operating conditions, and achieve cruise thrust adjustment at the same inlet mass flow to reduce installation losses.

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Gonçalves, L. M., B. D. S. Barbosa, G. A. e. S. Ferraz, D. T. Maciel und H. F. D. Santos. „VARIABILIDADE ESPACIAL E TEMPORAL DO ÍNDICE VEGETAÇÃO MPRI APLICADO ÀS IMAGENS DE GRAMA SÃO CARLOS OBTIDAS POR AERONAVE REMOTAMENTE PILOTADA / SPACE AND TEMPORARY VARIABILITY OF THE INDEX VEGETATION APPLIED TO IMAGES OBTAINED BY A REMOTELY PILOTED AIRCRAF“. Revista Brasileira de Engenharia de Biossistemas 11, Nr. 4 (27.12.2017): 340. http://dx.doi.org/10.18011/bioeng2017v11n4p340-349.

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