Different Phases Of Flight Research Articles

Investigating the role of flight phase and task difficulty on low-time pilot performance, gaze dynamics and subjective situation awareness during simulated flight.

Gaze behaviour has been used as a proxy for information processing capabilities that underlie complex skill performance in real-world domains such as aviation. These processes are highly influenced by task requirements, expertise and can provide insight into situation awareness (SA). Little research has been done to examine the extent to which gaze behaviour, task performance and SA are impacted by various task manipulations within the confines of early-stage skill development. Accordingly, the current study aimed to understand the impact of task difficulty on landing performance, gaze behaviour and SA across different phases of flight. Twenty-four low-time (<300 hours) pilots completed simulated landing scenarios under visual flight rules conditions. Traditional gaze metrics, entropybased metrics, and blink rate provided meaningful insight about the extent to which information processing is modulated by flight phase and task difficulty. The results also suggested that gaze behavior changes compensated for increased task demands and minimized the impact on task performance. Dynamic gaze analyses were shown to be a robust measure of task difficulty and pilot flight hours. Recommendations for the effective implementation of gaze behaviour metrics and their utility in examining information processing changes are discussed.

Evaluating The Impact of Mindfulness Service on Air Travel Experience and Satisfaction: A Mediation and Moderation Model

The concept of mindfulness is enhanced now a days over the world. It’s significant positive effects on person’s health not only valuable solution for people facing problems, like depression and anxiety but also makes a desire for society to enhance individual’s quality in many phases of life. To fulfilment of the objective of this study convenient sampling techniques is used to collected the data from the concerned respondents. To access and measurement of the model convergent validity, and discriminant validity is used and to measure the hypothesis path analysis is used. The results of it create positive travel experience which lead to higher customer satisfaction. Moreover, due to significant effects on travel anxiety and higher satisfaction with the service, customer more attract and loyal to airline. In order to take the large range of passengers the study was conducted as a survey which was taken at the international departure gate of Allama Iqbal International Airport Lahore. Data was collected and compiled from passengers who were frequent flyers in different airlines. The study also focusses on the relationship between mindfulness and travel experience with airlines of their choice. The Service quality acting as a moderator between mindfulness mediation and its effects on travel experience to improve customer satisfaction. Mindfulness has a limited attention in business perspective but this study investigates mindfulness as a business model. Mindfulness service create a positive effect to satisfied airline passengers during different phases of flight to enhance positive travel experience. There for, the possible impact of flight anxiety is investigated for better understanding of mindfulness meditation effect with the help of airline service quality.

A Review on Strategies to Reduce Fuel Consumption in Different Phases of Flight

Abstract: Fuel consumption is a critical aspect of aviation that directly impacts the cost, safety, and environmental impact of air travel. Aircraft require significant amounts of fuel to power their engines and maintain their altitude and speed during flight. Therefore, optimizing fuel consumption is a key priority for airlines, pilots, and aviation engineers. By understanding the factors that affect fuel consumption airlines can develop fuel-efficient flight plans and operational procedures that reduce costs and minimize the environmental impact of air travel. Research on ways to reduce fuel consumption are ongoing and lots of investment and research is required to improve the efficiency and sustainability of air transportation. In this review paper we will be discussing the ways airlines can reduce overall fuel burn in different phases of flight by using certain methods and procedures.

An Unmanned Helicopter Energy Consumption Analysis

The number of operations incorporating E-VTOL aircrafts is increasing each year, and the optimization of the energy consumption of such vehicles is a major problem. In this paper, a small-scale ARCHER helicopter’s energy consumption is analyzed, wherein different flight conditions, main rotor revolutions, and flight control system settings are considered. The helicopter dynamic model was developed in the FLIGHTLAB environment and was then validated based on flight test data. The model used for the calculation of energy consumption was developed using the electric and dynamic characteristics of the main rotor, electric motor, and transmission system. The main part of this work concerns the analysis of electric energy consumption during the vehicle’s flight via the use of an automatic flight control system (AFCS) that ensures repeatable flight conditions. The AFCS was designed such that it includes both path and attitude control to provide hover and cruise control modes. The helicopter’s energy consumption was analyzed during different phases of flight, when executing maneuvers, and using different main rotor angular velocities to perform - a given task. The results show that the level of energy consumption significantly depends on the helicopter’s main rotor revolutions, flight speed, and the maneuvers performed. The proposed methodology can be used in prospective energy-efficient mission planning and UAV helicopter design.

MODELING OF AERODYNAMIC INTERFERENCE IN THE DEVELOPMENT OF PERSPECTIVE AIRCRAFTS

There are presented the results of the main approaches analysis to modeling aerodynamic interference in the development of perspective aircrafts.&#x0D; The use of the methodological approaches proposed in the article will make it possible to determine the optimal aircraft layout in the formulation of the “wing-fuselage-engine” on the results of the achieved total aerodynamic characteristics.&#x0D; Analysis of modern armed conflicts shows that in most cases the use of aviation has a decisive influence on the outcome. Taking this into account, the main direction for the development of state aviation of Ukraine in the long term, with regard to the renewal of military transport aircraft fleet, is the designing and production of domestic planes. Nowadays, the world’s leading aircraft manufacturing companies (Airbus, Boeing and others) are working on the creation of competitive aircraft which are based on conceptually new schemes. This is because optimizing the shape of an aircraft can improve performance by only fraction of a percent while changes in the aircraft layout can lead to more significant positive results. Aerodynamic interference between the components of designed aircraft layout is relatively large and even minor changes in the geometry of one of the parts can significantly affect the overall aerodynamic characteristics of the aircraft. It is especially important to investigate the interference of working engines and airframe at different phases of flight at the stage of aircraft design.&#x0D; The purpose of the article is to present the results of the main approaches and methods analysis that can be used in modeling aerodynamic interference which is important in determining the total aerodynamic characteristics of advanced aircraft at the designing stage. This article uses the following research methods and methodologies:&#x0D; &#x0D; proven computational methods for optimizing the shape of an aircraft at the initial designing stage;&#x0D; boundary element methods, which are used to calculate potential flows, are also called methods of hydrodynamic singularities;&#x0D; numerical methods for studying the process of flow around bodies are used to study aero hydrodynamics based on various combinations of distributed and discrete hydrodynamic singularities;&#x0D; the numerical-analytical method and the panel method are used to calculate the carrier and moment characteristics of the airfoil in the framework of an ideal fluid;&#x0D; calculations based on the Navier-Stokes equations with a set of turbulence models are used for more complete and reliable information for calculating the carrier and moment characteristics of the airfoil;&#x0D; the discrete vortex method is used when the engine and the airframe are not considered separately from each other, but together;&#x0D; an iterative combination of the panel method with subsequent solution of the boundary layer equations for calculating the inviscid flow is used to take into account the effect of viscosity on the aerodynamic characteristics of the&#x0D; &#x0D; Conclusion: For solving problems of aerodynamic interference, the most suitable methods of the ideal fluid are the numerical-analytical and panel ones. More complete and reliable information on the calculation of the carrier and moment characteristics of the airfoil can be obtained by solving the full Navier-Stokes equations with a set of turbulence models. For those cases when it is necessary to obtain the aerodynamic characteristics of an aircraft that is designed with high accuracy.It is advisable to experimentally determine the corrections that are associated with the influence of operating engines.

Experiment verification test of the Artemis I ‘Deep Space Radiation Genomics’ experiment

When the Artemis missions launch, NASA's Orion spacecraft (and crew as of the Artemis II mission) will be exposed to the deep space radiation environment beyond the protection of Earth's magnetosphere. Hence, it is essential to characterize the effects of space radiation, microgravity, and the combination thereof on cells and organisms, i.e., to quantify any correlations between the deep space radiation environment, genetic variation, and induced genetic changes in cells. To address this, the Artemis I mission will include the Peristaltic Laboratory for Automated Science with Multigenerations (PLASM) hardware containing the Deep Space Radiation Genomics (DSRG) experiment. The scientific aims of DSRG are (i) to identify the metabolic and genomic pathways in yeast affected by microgravity, space radiation, and their combination, and (ii) to differentiate between gravity and radiation exposure on single-gene deletion/overexpressing strains' ability to thrive in the spaceflight environment. Yeast is used as a model system because 70% of its essential genes have a human homolog, and over half of these homologs can functionally replace their human counterpart. As part of the experiment preparation towards spaceflight, an Experiment Verification Test (EVT) was performed at the Kennedy Space Center to verify that the experiment design, hardware, and approach to automated operations will enable achieving the scientific aims. For the EVT, fluidic systems were assembled, sterilized, loaded, and acceptance-tested, and subsequently integrated with the engineering parts to produce a flight-like PLASM unit. Each fluidic system consisted of (i) a Media Bag, (ii) four Culture Bags loaded with Saccharomyces cerevisiae (two with deletion series and the remaining two with overexpression series), and (iii) tubing and check valves. The EVT PLASM unit was put under a temperature profile replicating the anticipated different phases of flight, including handover to launch, spaceflight, and splashdown to handover back to the science team, for a 58-day period. At EVT completion, the rate of activation, cellular growth, RNA integrity, and sample contamination were interrogated. All of the experiment's success criteria were satisfied, encouraging our efforts to perform this investigation on Artemis I. This manuscript thus describes the process of spaceflight experiment design maturation with a focus on the EVT, its results, DSRG's preparation for its planned launch on Artemis I in 2022, and how the PLASM hardware can enable other scientific goals on future Artemis missions and/or the Lunar Orbital Platform – Gateway.

Peculiarities of Interaction Between Trampoline and Trampolinist – as a Complex Biomechanical System in the Aspect of Physical Forces and Biomechanics of the Athlete

Aims. The purpose of this work is a detailed and detailed consideration of forces acting in the system «trampoline- trampolinist» from the point of view of the laws of classical physics. Concretely – the movement of the body of the athlete in space, mechanics of «work» of trampoline and system «trampoline trampolinist», as well as some aspects of the biomechanics of movements of the trampolinist when leaving the bed of the trampoline, coming to it and being out of contact with it. Study design. This work is an independent scientific research review with an analysis of question- naire data on the problematic issue. Methodology: the study was based on the application of a number of theoretical and empirical methods. The study uses theoretical analysis, systematization, and generalization of scientific literature, documentary sources, and guidelines in the field of physical education, biomechanics of movements of the trampolinist, a compilation of literature sources to identify the essence of the problem forces and interaction of the athlete with the trampoline and identify ways to solve. Results. In the article theoretical aspects of processes occurring in the interaction of trampoline as a mechanical system and trampolinist as a biomechanical system are considered. In connection with the increased requirements for the performance of athletes on trampolines since 2017 and the new rules of evaluation of performance in trampolining, the basic forces acting in the system «trampoline – trampolinist» are considered in detail. By calculation according to anthropometric and physical data of trampolinists and data of the analysis of their movements in the process of jumping by means of the special computer program «Kinovea» quantitative characteristics of forces acting in the «trampoline-trampolinist» system at different stages of their interaction in the process of their training or competitive programs were determined. A clear correlation of essential increase of these forces in proportion to the age of the sportsman, growth of his sports skill, and mass of his body is shown. The program allowed tracking the dynamics of athletes’ in-flight movements in slow motion and determining the angles of their body parts’ positions. A theoretical analysis of the main reasons that lead to violations in the combined operation of the trampoline as a mechanical system and the trampolinist as a biomechanical object was carried out. The consequences of these violations are shown and the ways of correcting these phenomena to increase the level of sportsmanship of trampolinists and increase their performance grades are proposed. Conclusion. When teaching trampoline athletes in the early stages and especially at the stage of specialized basic training, the authors point out that it is important to explain them and achieve a proper understanding of the physical forces and their real values acting on athletes in different phases of flight.

Capacity Fade and Aging Effect on Lithium Battery Cells: A Real Case Vibration Test With UAV

This article presents an analysis of the capacity and the state of health (SoH) of 3-Ah lithium battery cells operating in a real case vibration stress scenario based on drones. An unmanned aerial vehicle (quad-copter) is adopted to acquire real vibration profiles during different phases of flight. First, the possible capacity fade and aging effect on lithium cells are investigated by considering vibrations applied to the radial and longitudinal battery axes with both short-term and long-term (aging) tests. Then, the cruise-flight vibration profiles are applied and characterized. A comparison with standard (no vibrations) cycling aging is also presented and discussed. The experimental results show that no significant effect on capacity fade can be observed between standard and real case vibrating operating conditions.

Evaluation of CO2 Emission at Airports from Aircraft Operations within the Landing and Take-Off Cycle

The importance of airport emission inventory is more specific in the local context as it directly affects the local air quality. The specific gap addressed by this research is evaluating the CO2 emission from aircrafts within the landing and take-off (LTO) cycle. Using currently available methodologies for assessing emission within the LTO cycle in the Sri Lankan context has significant limitations, such as unavailability of relevant operational data and the International Civil Aviation Organization (ICAO)-specified “time-in-mode”(TIM) (e.g., take-off, climb-out, idle, and approach) estimates at different phases of the LTO cycle being inconsistent with local conditions. Such industry-wide standards have been found to over or underestimate actual volumes specific to local conditions. In this research, data collected from online flight-tracking services and daily aircraft movement record (DAMR) data maintained by the local air traffic service provider were used to estimate TIM values according to site-specific conditions. Existing literature to some extent addresses the assessment of CO2 emission levels under different phases of flight separately. In this research, a methodology was developed with available data sources to estimate CO2 emission levels under different phases of flight separately within the LTO cycle. The methodology was applied to Bandaranaike International Airport, Sri Lanka. This approach can be applied to similar scenarios in which operational data limitations exist as elaborated in the study.

Evaluation of CO₂ Emission from Flight Delays at Taxiing Phase in Bandaranaike International Airport (BIA)

On-time performance is one of the most important Key Performance Indicators for airport operations since flight delays carry a huge economic cost in the industry. Many types of research were conducted to measure aviation delay and its economic cost as consequences (Kuhn, 2013) while environmental impact due to the flight delays was sparsely addressed. Flight delays result in excess fuel consumption and more emission. Existing literature addressed the aggregate emission of the aviation industry(IPCC, 2015). However, assessment of emission levels separately under different phases of flight has not received sufficient attention. Evaluating each phase of flight separately allows initiating more precise emission reduction strategies. In this research, a methodology was developed with available technologies to evaluate the flight delays and CO2 emission at the taxing phase for both arrivals and departures. Bandaranaike International Airport (BIA) was taken as a case for developing the methodology.

An Investigation into the Factors that Affect Miscommunication between Pilots and Air Traffic Controllers in Commercial Aviation

ABSTRACTObjective: The present research sought to investigate the communication performance of both native English sounding pilots and accented commercial pilots in two different phases of flight, the approach and departure phase of flight.Background: English language proficiency requirements, standardized phraseology, and readbacks are some of the proactive measures which the aviation industry employs to ensure effective communication. However, despite these efforts, errors in communication still occur, and anecdotal evidence suggests that factors such as language background and phase of flight increase the likelihood of communication errors.Method: Eighteen hours of air-ground communications at Kingsford Smith International Airport, Sydney, Australia, were analyzed.Results: The results revealed that accented pilots committed more communication errors than native English sounding pilots and more specifically that these errors were mistakes rather than omissions, and involved words rather than numbers. Communication performance was similar in the approach and departure phases of flight regardless of language background.Conclusion: These results provide detailed information about the type of communication errors which occur in commercial aviation, their prevalence and the context in which they occur, which helps guide where resources should be directed to further improve safety.

Active Vibration Control of Launch Vehicle on Satellite Using Piezoelectric Stack Actuator

Satellites are subject to various severe vibration during different phases of flight. The concept of satellite smart adapter is proposed in this study to achieve active vibration control of launch vehicle on satellite. The satellite smart adapter has 18 active struts in which the middle section of each strut is made of piezoelectric stack actuator. Comprehensive conceptual design of the satellite smart adapter is presented to indicate the design parameters, requirements and philosophy applied which are based on the reliability and durability criterions to ensure successful functionality of the proposed system, also fabrication process of the proposed piezoelectric stack actuator is discussed in detail. The coupled electromechanical virtual work equation for the piezoelectric stack actuator in each active strut is derived by applying D'Alembert's principle to calculate the consistent mass matrix, the stiffness matrix and the load vector using finite element approximation. Modal analysis is performed to characterize the inherent properties of the smart adapter and extraction of a mathematical model of the system. Active vibration control analysis was conducted using fuzzy logic control with triangular membership functions and acceleration feedback. The control results conclude that the proposed satellite smart adapter configuration which benefits from piezoelectric stack actuator as elements of its 18 active struts has high strength and shows excellent robustness and effectiveness in vibration suppression of launch vehicle on satellite.

Need of different flapping styles for different flight phases of a flapping wing vehicle: A preliminary analysis

Flapping wing vehicles ranging from a large bird sized model to a tiny insect-sized model were made successfully. Still, there is a lot of scope for further research, since their natural counterparts outperform them in most of the flight aspects. The fact that the natural flyers change their flapping style for different flight phases is taken for investigation. Aerodynamic forces at a wing section are analyzed using the general blade-element approach. Using vector mechanics, contributions of the sectional lift and drag forces to the thrust, lift and side force of the vehicle are derived and non-dimensionalized. All the three were in terms of four non-dimensional parameters - the sectional lift to drag ratio, advance ratio, stroke plane orientation and instantaneous flapping angle. The variations of the three force components with the four non-dimensional parameters were plotted. Flapping style with minimized side force and maximized the thrust and lift production is considered as that of efficient flying. The results demand that the stroke plane orientation, speed and amplitude of flapping should be varied for different phases of flight for efficient flying.

Assessment of noise in the airplane cabin environment.

To measure sound levels in the aircraft cabin during different phases of flight. Sound level was measured on 200 flights, representing six aircraft groups using continuous monitors. A linear mixed-effects model with random intercept was used to test for significant differences in mean sound level by aircraft model and across each flight phase as well as by flight phase, airplane type, measurement location and proximity to engine noise. Mean sound levels across all flight phases and aircraft groups ranged from 37.6 to >110 dB(A) with a median of 83.5 dB(A). Significant differences in noise levels were also observed based on proximity to the engines and between aircraft with fuselage- and wing mounted engines. Nine flights (4.5%) exceeded the recommended 8-h TWA exposure limit of 85 dB(A) by the NIOSH and ACGIH approach, three flights (1.5%) exceeded the 8-h TWA action level of 85 dB(A) by the OSHA approach, and none of the flights exceeded the 8-h TWA action level of 90 dB(A) by the OSHA PEL approach. Additional characterization studies, including personal noise dosimetry, are necessary to document accurate occupational exposures in the aircraft cabin environment and identify appropriate response actions. FAA should consider applying the more health-protective NIOSH/ACGIH occupational noise recommendations to the aircraft cabin environment.

Influence of meteorological phenomena on worldwide aircraft accidents, 1967–2010

ABSTRACTBased on the information available in databases from relevant national and international organizations from 1967 to 2010, an Aviation Weather Accidents Database (AWAD) was built. According to the AWAD, the weather is the primary cause in a growing percentage of annual aircraft accidents: from about 40% in 1967 to almost 50% in 2010. While the absolute number of fatalities and injured people due to aircraft accidents has decreased significantly, the percentage of fatalities and injured people in accidents attributed to the weather shows a slight increase in the studied period. The influence of turbulence, clear air turbulence, wind shear, low visibility, rain, icing, snow and storms on aircraft accidents was analysed, considering the different phases of flight, the meteorological seasons of the year and the spatial distribution over four zones of the Earth. These zones were defined following meteorological and climatological criteria, instead of using the typical political criteria. A major part of the accidents and accidents attributed to the weather occur in latitudes between 12° and 38° in both hemispheres. It is concluded that actions aimed at reducing the risk associated with low visibility, rain and turbulence, in this order, should have priority to achieve the most significant improvements in air transport safety.

On the characteristics of titanium alloys for the aircraft applications

Complex aerodynamic design, high mechanical and thermal loads, extreme environmental and other service conditions produces high magnitude of dynamic stresses in various components of airframe. The magnitude and nature of these stresses further varies during different phases of flight. This governs the need to develop special materials having ability to withstand these variable stresses. Further high fuel costs, scarcity of raw material sources, need of efficiency improvements, growing demand of new aircrafts (both military and civil) and raised environmental standards (less CO2 emission, less noise pollution, recyclability of materials, etc.) are the few factors which forced the engineers to make stronger but ‘as-light-as-possible’ engine, frame and other parts of aircrafts. These factors open the door for ‘stronger-but-lighter’ metals like titanium and its alloys for aerospace application segment. Titanium and its alloys offers a unique set of physical, mechanical, metallurgical and composite compatibility characteristics which helps the aerospace sector to meet economy, fuel efficiency and other global standards in a wide range of temperatures and other service conditions. Starting from its first application in 1950s to till date, this wonder-metal not only increases its share of presence but becomes the first choice of aircraft fabricators. This paper presents an overview of inherent mechanical and metallurgical characteristics of titanium and its alloys which makes it an ideal for the aircraft applications. A brief summary of induced stresses in aircraft critical components with advantages of titanium and its alloy to manufacture these components is also discussed.

Модель оцінки ймовірності авіаційної події в околиці аеропорту

В статті описані результати обробки та статичного аналізу даних про АП ЦА України і ЦА держав-учасників Угоди. Встановлена тенденція виникнення авіаційних подій за етапами польоту ПС ЦА України і ЦА держав-учасників Угоди. Виконано аналіз існуючих моделей оцінки ймовірності авіаційної події в околиці аеропорту. Виконано аналіз існуючих моделей оцінки ймовірності авіаційної події в околиці аеропорту. Запропоновано подальший розвиток моделі оцінки ймовірності авіаційної події, яка дозволяє для запропонованих категорій важких і легких повітряних суден визначати ймовірності катастрофи в околиці аеропорту на різних етапах польоту. Представлено результати дослідження локального ризику виникнення катастрофи повітряного судна в околиці аеропорту ДП МА «Бориспіль».

Assessing Pilot Workload in Single-Pilot Operations with Advanced Autonomy

The proposed transition to single-pilot operations (SPO) in commercial and military aircraft has motivated the development of advanced autonomy systems. However, a detailed analysis of the impact of advanced autonomy on pilot workload through various phases of flight and contingency scenarios has not been conducted. To this end, this paper presents the development of the Pilot-Autonomy Workload Simulation (PAWS), a discrete event simulation model that allows the investigation of pilot workload under a variety of advanced autonomy capabilities and scenarios. Initial utilization results from PAWS of nominal and off-nominal point-to-point missions demonstrate that the workload for a single pilot assisted by advanced autonomy varies considerably over different phases of flight and various contingencies. These results suggest that advanced autonomy to offset pilot workload is not needed for low-workload phases, but could be critical during periods of high workload.

EEG Correlates of the Functional State of Pilots during Simulated Flights

Analysis of variance and discriminant analysis were used to study EEG spectral characteristics recorded using 15 leads from two professional pilots with more than 15 years of experience, in the frequency band 0.1–70 Hz, during flights on a TU-154 simulator, including takeoff, landing (including in difficult conditions), and horizontal flight. The results showed that the spectral characteristics of the EEG were highly informative measures of the ongoing functional state of the pilots at different phases of flight. The high significance of the differences seen in the individual features showed them to be nonrandom and demonstrated the potential for using EEG parameters to construct a system for monitoring the pilot’s state at all stages of flight.

Propuesta para disminuir la temperatura en la cabina del avión T-90 Calima

La temperatura es un factor importante en el momento de realizar una labor; sí la sensación térmica no es agradable, un trabajo sencillo puede transformase en un trabajo complicado, donde se puede exponer la integridad de la persona. En las aeronaves de entrenamiento los pilotos no son ajenos a los inconvenientes de la exposición a una temperatura elevada generada por radiación solar, equipos, entre otros. Al incluir un sistema de refrigeración a la cabina de entrenamiento de la aeronave ésta se ve afectada en características como equilibrio, mayor consumo de combustible, disminución de la eficiencia debido al aumento de peso. En este artículo, se proponen tres formas de disminuir la temperatura en la cabina del avión T-90, en las diferentes fases de vuelo, que consisten en implementar tomas y salidas de aire, utilizar una película térmica para la cabina y desarrollar un dispositivo que permita la circulación de aire en la fase previa al despegue.