Air Craft Research Articles

LSTM-Based Approach for Remaining Useful Life Prediction of Air Craft Engines

Working machinery has a limited lifespan and occasionally breaks down due to obsolete functioning. A maintenance strategy must be used on the scheduled machinery system in order to prevent the worst scenario (failure) and learn more about the machine’s condition. The ideal maintenance technique is predictive maintenance. Predictive maintenance, whose major goal is to forecast hardware component failures by continually monitoring their status, emphasizes the importance of this requirement so that maintenance operations can be planned far in advance. These observations, which span the lifecycle of the corresponding components, are produced by monitoring systems and often take the form of time series and event logs. The fundamental difficulty of data-driven predictive maintenance is analysing this history of observations in order to create prediction models. Machine learning has become widely used in this direction as a result of its ability to extract knowledge from a range of data sources with the least amount of human involvement. This work aims to investigate and deal with difficult issues in aviation connected to foreseeing component breakdowns on board. Scalability is a crucial component of every suggested strategy due to the vast volume of data related to the operation of airplanes.

Out of breath in pandemic - Is pressure swing adsorption (PSA) technology a solution for saving lives?

In these unprecedented times of COVID-19 pandemic, globally there has been a shortage of medical supplies, hospital beds, health care workers, etc. This was accentuated in India with a shortage of oxygen in the second wave of pandemic. The reasons for shortage were mainly imbalance between demand-supply and these also led to implementation of ingenious solutions in the form of oxygen generators based on PSA technology. The technology was an off shot from OBOGS developed by DRDO and DEBEL for light combat military air crafts. This review discusses the scientific technology behind medical oxygen plants based on PSA, its applications and its advantages to combat the dearth of oxygen.

Model-based microburst identification using a hybridized extended Kalman filter with genetic algorithm

Microburst (MB) wind shear is one of the most important meteorological dangers threatening the aircraft (AC) safety and the life of passengers. Though there are some ground-based 3D Lidar systems to detect low-level MB wind shears to alert the pilots, there have been fewer scientific attempts to identify model-based MB parameters via AC onboard air and position data. The latter refers to the development and identification of an acceptable MB model upon which an automatic flight control (AFC) system can be designed to control the AC through wind shear microburst. In essence, accurate knowledge of MB model is an essential prerequisite for design and analysis of AFC systems that can safely fly the AC against microbursts, especially in crucial phases of flight such as takeoff and landing. The present study focuses on online estimation of MB parameters whose results pave the way for effective MB autopilot designs for safe flights through MB. The proposed task is accomplished via a model-based approach using the AC six degrees of freedom (6 DoF) equations of motion (EOM) integrated with the latest verified model of the MB utilizing the extended Kalman filter (EKF). In addition to a sensitivity analysis to determine the key MB model parameters, the performance of the estimation process is enhanced via a hybridization of the genetic algorithm (GA) with the EKF. The results are promising and indicate that the proposed scheme can identify the MB model parameters with sufficient accuracy needed for online applications with AFC design.

Reducing Hydrogen Boil-Off Losses during Fuelling by Pre-Cooling Cryogenic Tank

Boil-off losses occur when gaseous hydrogen has to be released from a cryogenic tank due to liquid hydrogen evaporating. These are a substantial drawback for all areas in which liquid hydrogen is discussed as a potential fuel to limit the climate impact. Especially boil-off losses during fuelling are one of the most significant source of losses along the liquid hydrogen pathway. To analyse and minimize such losses, simulations of the filling process are performed with the simulation tool “EcoSimPro”. The simulations are validated with an analytical solution. The results show that boil-off losses can be significantly reduced by pre-cooling the cryogenic tank with liquid nitrogen. This method is most effective for relatively small tanks that could be used e.g., in small air crafts or air taxis.

Effect of Urban Expansion Indices Change by (R.S.) on Height of Convective Radix Layer around Baghdad Airport (Iraq)

Change in structure of land surface can affect atmospheric boundary layer and formation of internal boundary layer. This will change shear stresses and turbulent boundary layer. Change in low level wind shear and turbulent can affect air craft performance and has potentially adverse effects on flight safety during landing and taking-off stages. In this study, change in land area around Baghdad Airport and its effects on structure of boundary layer and radix layer through summer season (July from years 1985 and 2014) is examined. The examination is done through atmospheric data of radiosonde (at altitude more than 1500 m) and remote sensing by Landsat 5 and 8 images (circular region around airport has radius 3.250 km and the airport is considered the center of this circle). From analysis of hourly wind speed and temperature profile with height observed by radiosonde, change in convective radix layer can be determined at this period resulted from change structure of boundary layer depending on characteristic of landcover used in supervised classification. Building area increases from 18% in 1985 to 41% in 2014. These results enforced by positive values of built up index BI, that showed a decreases in 2014. All these elements changed convective radix layer from less than 500 m in summer 1985 to more than 700 m. There is a large fluctuation in radix layer height depended on convective and friction velocity at 2014 data. Thus indirect change in structure of convective layer will affect navigation movement of Baghdad International Airport.

Heat transfer enhancement for Marangoni Darcy-Forchheimer convective flow of hybrid nanofluid with magnetic force and dissipation features

Following enhanced thermal applications of hybrid nanofluids compared to traditional nanomaterials, scientists have focused attention on the improvement in thermal resources and energy systems. This research presents the Darcy-Forchheimer flow of hybrid nanofluid consisting of copper and silver nanoparticles with dust particles. The thermal model is further supported by the thermal radiation Marangoni convective phenomenon. The novel dynamic of viscous dissipation and magnetic impact are uniformly entertained. The stretched surface with a porous medium induced the flow. The spherical types of dust particles are used to assess the flow pattern. The expressions occupy the properties of the dust phase, and the fluid phase is used to formulate the model. The suitable transformations make the problem non-dimensional. Later on, a numerical framework is worked out to perform the simulations. The comparative task is used to ensure validity. All the essential thermal mechanism of hybrid nanofluid is evaluated and presented in a tabular form. The velocity profile increases for silver and copper particles with water suspension. The presence of porous space declined the phase fluid and dust particles velocities effectively. Moreover, the temperature profile of dust particles and hybrid nanofluid enhanced with an increment of interaction parameters. The obtained results convey novel significance in thermal systems, cooling of devices, engine coolants, air crafts, decrement of drugs, electronics and engineering devices, welding phenomenon glazing windows, etc.

Prediction of Kerf Width and Surface Roughness of Al6351 Based Composite in Wire-Cut Electric Discharge Machining Using Mathematical Modelling.

The machining of composite materials has been an area of intense research for the past couple of decades due to its wide range of applications, from automobiles to air crafts or from boats to nuclear systems. Non-conventional machining, especially electric discharge machining (EDM), is found to be a good machining option for meeting the required outputs. To overcome the challenges of machining complex shapes, wire electric discharge machining (WEDM) was developed. Al6351 composites was observed to be extensively used in nuclear applications. Therefore, identifying the kerf width and surface roughness are important criteria for the dimensional accuracy of the final product. The present work aims at predicting the behavior of the two major machining parameters which are kerf width and surface roughness of Al6351 composites in wire EDM by creating a mathematical model using ANOVA for different combinations of the reinforcements and comparing the variations in the coefficients for different combinations of reinforcements. The developed model has been validated by conducting similar set of experiments in Al6351-5% SiC-1% B4C hybrid composite. From the work, it was identified that pulse on time and current are the major contributing factor for kerf width and wire feed rate was observed to be contributing to the surface roughness. The validation results show an average variation of 8.17% for kerf width and 11.27% for surface roughness. The work can be successfully utilized for prediction of the kerf width and surface roughness of the composites manufactured with Al6351 as the base matrix material.

On the methodology for the probability evaluation of an aircraft crash on a nuclear power plant site and its nuclear power units

A mathematically correct new approach to the probability evaluation of an aircraft (AC) crash on a nuclear power plant (NPP) site and its nuclear power units is developed. The approach is based on two key assumptions: the AC completed its flight in airspace in the area of the nuclear power plant and its nuclear power units are located; during the flight, the aircraft is not affected by external forces. The new approach provides a guaranteed, adequate and cautious (conservative) estimate of the total annual probability of an aircraft crash on a site/object, the probability evaluation of an aircraft crash on an NPP site, since it is believed that in the event of a catastrophic situation on board, the aircraft trajectory does not change the heading angle directed strictly on the site/object. Keywords nuclear power plant, aircraft, fall probability, Gaussian distribution, DE distribution

Investigation on mechanical, microstructural and thermal properties of coconut peduncle fibre epoxy resin

Now days the natural composite materials are used in various applications like automobile interior decorations, Air craft applications, Industrial duct production etc… The Coconut peduncle leaf stack fiber (CPLSF) and Multi-Walled Carbon Nano Tubes (MWCNT) are different percentage used such as 0 %, 1 %, 1.5 % and 2 % are used to treat the extracted fiber to explore the influence of MWCNT over the properties of fiber. This research work is focused towards determining the static and dynamic mechanical properties and morphological analysis. This coconut peduncle leaf stalk fiber treated with the distilled water and alkaline sodium hydroxide. The length of each specimen’s fiber is slized into 3 mm, 7 mm and 10 mm. The flexural, impact and tensile test are conducted to reveal the mechanical properties of the component. Then the further investigation on thermogravimetric analysis (TGA) to confirm the thermal stable to confirm and finalize the presence of impurities over the surface of raw fiber.

Theoretical Study of Combustion Processes in Aero Gas Turbines for Air Craft Engines

Combustion process involves various physical and chemical processes which govern and control flames initiation in aero gas turbine engines. During certain flying conditions, at full load, unexpected critical situation may take place in such engines called blow off conditions, which leads to flames diminishing in the combustion chamber of such engines. Gas motion, flow velocity and turbulence kinetic energy are the most important parameters in ensuring flame stabilities. These parameters play a tremendous role and effects on this phenomenon. In gas turbines, the flame exists within a high velocity, non-uniform and intensely turbulent flow field, therefore careful temperature control is vital. Another important factor which must be considered to avoid blow off conditions, is mixture strength. Nearly, all modern gas turbines, due to emissions restrictions, operate on lean mixture conditions which are hard to ignite and lower flame temperatures and thus more risk to reach blow off conditions which leads to a complete flame extinction. These conditions may exist in an air craft engines due to sharp changes in loading parameters, (θL): pressure (Pu), temperature (Tu), mass flow rate (), and cross sectional area (Au). At present there is no detailed theory of gas turbine combustion. Therefore, we must resort to simple models and experimental correlations. This paper investigates the blow-off phenomena in aero gas turbine engines, its causes and estimation of required energy to ensure recovery (re-ignition) again inside the combustion chamber. Identifying the conditions at which blow-off takes place and associated loading parameters (θL) which are a function of (A, T, P, and ). The paper also, quantify the recovery conditions (required energy to re-ignition, change in loading parameter (Δq) Power, Required VHRR: (Volumetric Heat Release Rate) and changes in other loading variables (ρ: density, T: Temperature, P: Pressure, and : mass flow rate) tarts with discussing causes of blow off along with effecting operating conditions.

Performance and Scalability Make Advanced Carbon Materials Optimal for Air and Space Crafts

Know the importance on the Journal of Air and Space Crafts and Open Access Journals In USA - Scholars.Direct. Performance and Scalability Make Advanced Carbon Materials Optimal for Air and Space Crafts.

Development of a Computer Based Gas Turbine Instruments Test system

Due to the significant importance of gas turbine engines as it is the core of the aircr aft, the engine health status should be tested periodically. Testing methodologies are needed to conduct the engine tests required as a part of airworthiness certification. In this project, a Data Acquisition System (DAQ) was developed as a turboshaft engi ne (GTD 350) testing system. This system was developed to monitor the engine parameters for determining its condition. A PIC 16F877A microcontroller was used as the heart of the DAQ. Internal Analog to Digital Converters (ADC) acquired data from analog sig nals. The analog signals gathered from temperature, tacho generator, throttle, and pressure sensors were transformed into digital format, and then the corresponding data was sent serially to Personal Computer (PC) through a microcontroller serial port. The visual basic program was designed to convert, scale, and display these data. Furthermore, the system was designed to analyze, compare the displayed data with standard stored data, and provides automatically a troubleshooting list whenever upnormal data oc curred. The developed test system had been applied successfully and the results are accurate, reliable, and acceptable.

Effect of plasma nitriding on M50 NiL steel – A review

Chemical Diffusion Process like Nitriding has important role in modern surface hardening. Plasma nitriding is one of the best method to improve surface hardness, wear and corrosion resistance of material, and also plasma nitriding improves surface properties. M50 NiL Steel is a low carbon high alloy steel with good strength, hardness, and wear and corrosion resistance at elevated temperatures. It is frequently utilised in the aerospace sector due to its unique features. To determine the corrosion and wear resistance of double element alternate implanted M50 NiL steel, detection methods such as scanning electron microscopy (SEM), X-Ray diffraction method (XRD), transmission electron microscopy (TEM), and potentio dynamic polarisation were utilised. The purpose of this paper is to identify the effects of plasma nitriding on M50 NiL Steel and to know the progress of surface hardening properties like micro hardness and wear for M50 NiL steel after plasma nitriding. The bearing made out of this steel is operated under heavy loads and high speeds in air craft engine. Effects of nitriding temperature on microstructure, micro hardness, and wear resistance of nitride layers with only a diffusion layer and no standard compound layer. and surface hardness is improved at low nitriding temperatures, When the nitriding temperature exceeds 575 °C, the nitride layer thickness increases, while the core and surface micro hardness drops. Mechanical Properties of nitride surfaces are studied by using Vickers hardness test and polarization tests. M50 NiL Steel was Plasma nitro carburized at low temperature and rare earth (RE) atoms are diffused into the specimen surface for better surface hardness and increased corrosion resistance. Some times to achieve exceptional properties duplex hardening is preferred and this process can be useful to obtain good hardness and same can be done for both hardened and case hardened bearing steels, with relative increase in rolling contact fatigue resistant and better tribological properties.

A CFD study on the structural parameters of NACA 2412 airfoil based air-wing using different composite materials

Weight is one of the important factors in aerodynamics; we need to reduce the weight of any flying object in order to get the higher lift force. Wight reduction of wing helps us to get better air craft efficiency and high performance. Aluminum alloys are used to make aircraft wing as it is suitable but in this study, we have used few light weighted composite materials for making the aircraft wing and other alloys as well where aluminum is used as the base material and it is mixed with other materials with different proportions for testing the performance. In this study, NACA 2412 airfoil has been chosen and the wing has been designed in Design Modeler 19. The model has been imported to ANSYS Workbench; the static structural analysis has been carried out by putting the required parameters. The objective of the study is to find out which material will be suitable for making aircraft wing among Carbon Fibers, Alpha-Beta Titanium alloy and Al-Zn-Mg alloy.

Scientific basis for the trainer aircraft anti-g equipment requirements

The design process of a new aircraft (AC) is always associated with the issue of choosing its basic technical parameters, or, in other words, the formation of its conceptual design. In case of a civil aircraft, the choice of these parameters is defined by the requirements for operational safety, market conditions, norms that specify the tolerable harmful impact of the aircraft on the environment, etc. In case of a military aircraft, its outlay mostly depends on the concept of potential military threats, ways of using the military aircraft in military conflicts. Some of these requirements are formulated in regulatory documents – the Aviation Requirements for Civil Aircraft and the General Tactical and Technical Requirements of the Air Force for Military Aircraft. For example, Part 25 of the Aviation Requirements for Civil Aircraft defines the Airworthiness Standards for transport aircraft. It should be noted that the stated above requirements are often a tool of competition, for example, when tightening the aircraft noise abatement procedures provides advantages for particular manufacturers, not admitting other manufacturers to enter the market, whose aircraft do not conform to the new standards. Thus, complying with the requirements virtually involves additional costs both in the aircraft development and during its operation. In addition, the implementation of the requirements stated above can lead to the deterioration of the aircraft’s performance, and hence, to the decrease of its competiveness and combat effectiveness. Therefore, each requirement of the regulatory documents should have a profound scientific rationale. This article analyzes one of the regulatory documents requirements referring to the necessity of anti-g system on board aircraft. The authors propose the approach to specify the existing criterion to provide the scientific basis for the anti-g system on board aircraft by assessing the actual level of pilot load when maneuvering. The subject under study is of particular importance for the Yak-152 trainer aircraft. The actual level of loads during pilotage of the Yak-152 trainer aircraft does not require the use of the anti-g system but if to be based on a formal criterion, namely, in terms of the maximum operational overload value, the aircraft should be fitted out with such a system.

К вопросу об определении барометрической высоты механическим альтиметром и системой воздушных сигналов

Reliable information on the altitude and speed parameters of the aircraft (AC) is required for safety and increasing the efficiency of flight missions. In this regard, the task of studying the features and improving the characteristics of existing meters for these parameters is quite urgent. Purpose of the study. The features of determining the barometric altitude of an aircraft by a mechanical indicator and an air signal system (SHS) are considered. Materials and methods. The essence of the baro¬metric method for measuring the altitude of the aircraft is analyzed, it is found that to build a clear theory of the method, it is necessary to know the dependence of the temperature of the atmosphere on the altitude. Moreover, it is known that this temperature usually decreases with increasing altitude. However, the rate of decrease unpredictably changes both at different times of the year and day, and at different points and at different heights. Moreover, in some cases, in a certain range of heights, the temperature may not decrease, but, on the contrary, increase. In this regard, there is some problem with the formalization of this dependence. When constructing a theory of the method for mechanical pointers, one proceeds in such a way that the dependence for the International Stan¬dard Atmosphere (ISA) is used, in which temperature and pressure are uniquely related. When developing algorithmic support for SHS, it is considered that the temperature decreases with height as well as in a standard atmosphere, but its actual value at the level of the reference plane can be anything that is not at all related to pressure and altitude in ISA. For this purpose, a temperature control unit is provided in the SHS at the level of the height reference plane. Results. A formula has been obtained that makes it possible to determine the difference between the readings of a mechanical altimeter and SHS. It was found that this difference is a function of pressure and temperature at the level of the plane of the altitude reference plane, as well as the actual pressure at the flight altitude. Numerical studies have been carried out to assess the discrepancy between the readings. It has been established that the relative difference in readings can reach the order of magnitude under ope¬rating conditions, and it practically does not depend on the aircraft altitude and is, in essence, a constant for the indicated initial values of pressure and temperature (at the level of the plane of the altitude reference). Conclusion. The developed algorithms can be used to improve the algorithmic support of the SHS.

Oil Exploration and Underdevelopment: A Study Of Niger Delta Region Of Nigeria

This study placed at the center of its focus oil exploration and underdevelopment in the Niger Delta region of Nigeria. In the study, three research questions were posed; what are the benefits of oil exploration in the Niger Delta region of Nigeria? What are the effects of oil exploration and underdevelopment to the host communities in the Niger Delta region of Nigeria? What are the remedies that can enhance oil exploration and development in the Niger Delta region of Nigeria? Also, three objectives were stated, which includes to identify the benefits of oil exploration to the Nigeria nation, to examine the effects of oil exploration to the host communities and to recommend remedies that can enhance oil exploration and development. Elite theory was adopted to theoretically analyze this work and descriptive research design method was employed. Secondary sources were used in gathering data and content analysis was adopted as data analysis technique. The study revealed the benefits of oil exploration such as economic growth, job creation, energy supply to power industries and homes, provide fuel for vehicles and air crafts etc. Also, the research work xrayed the effects of oil production activities and the neglect of the Niger Delta region by the Nigerian state and oil and gas industries such as environmental degradation, exploitation, unemployment, lack of social amenities, infrastructure, poverty among others. Furthermore, the study made some recommendations advising the federal government and oil companies to ensure effective consultation and partner proactively with host communities to better their operations, to reduce environmental degradation and its adverse effects and improve the living standard of people in the areas of oil exploration by providing infrastructures like roads, schools, electricity, hospital scholarships among others which will protect the environment and enhance the relationships between government, companies and the host communities in the Niger Delta region.

The Method of Operational Planning of Group Actions of Aircraft in the "Air Taxi" Mode

The article is devoted to the development of algorithms for operational planning of routes for a group of aircraft (AC). We consider group actions of small and unmanned aircraft in the "air taxi" mode, when there is no regular flight schedule between the points of destination, and requests are received "on call" for flights to points whose composition is unknown in advance and is of a random nature. The multicriteria task of planning a group flight in the "air taxi" mode is being solved. The solution to this problem is proposed using the apparatus of the queuing theory, according to which the system under consideration belongs to the class of multichannel queuing systems with waiting. A method for solving the problem of operational planning of aircraft actions is proposed. An algorithm for group target distribution of new claims between aircraft is developed on the basis of a modified minimax criterion for assigning the nearest aircraft for an object with a maximum service time. The developed algorithm is based on the following four main operations: in the first operation, priority unserved targets are selected according to the criterion of assigning a dynamic priority; in the second operation, the formed list is ranked according to another criterion, taking into account the importance and total distance of each ground object from the aircraft group, in three this operation selects the object with the maximum rank, and for it the task of assigning "own" aircraft is solved according to the third criterion of maximum proximity, in the fourth operation the conditions of non-intersection of the group flight routes are checked. A computer model of the system for servicing requests in the air taxi mode has been developed. The developed model makes it possible to analyze various scheduling algorithms, as well as to determine at each step the number of free claims and the number of free and busy aircraft. A comparison is made between the well-known in the theory of queuing and the proposed minimax approaches. It is shown that, in comparison with the known variants of scheduling in the queuing theory, on the basis of the proposed approach, the optimal number of used aircraft is achieved.

Establishment, simulation and verification of firepower safety control model

On a narrow warship platform, the coordinated use of shipborne weapon systems may cause firepower conflicts, which seriously endangers the ship safety. Meanwhile, with directed-energy weapons mounted on ships, firepower conflicts between weapons become a “high probability event”. Aiming at the problem of firepower safety control, based on the research about the collision probability model of air crafts and space targets and according to the cone of fire model of conventional weapons and directed-energy weapons, this paper solved the firepower conflict probabilities between conventional weapons as well as between conventional weapons and directed-energy weapons respectively using the methods of probability theory, and established the firepower safety control model. Then the calculation of firepower conflict probability was carried out using the dimensionality reduction method based on the equivalent conversion of polar coordinates and the power series method based on Laplace transform. The simulation results revealed that the proposed model and calculation methods are effective and reliable, which can provide theoretical basis and technical support for resolution of firepower conflicts between weapons.

Analysis of Air Side Needs at Mutiara SIS AL-JUFRI Airport Palu

The city of Palu is the capital of the province of central Sulawesi which has hajj waiting list 0f around 31,384 pilgrims with a qouta of 1986 pilgrims until 2034. Garuda indonesia has prepared four tipes of air craft that will serve these filghts including Boeing B777-300ER, B747-400, A330-300 and A330-200. In this study use the secondary data for the next 10 and 20 years forcasting uses the econometric method. The data needed includes climatology, passenger and air craft characteristic at Mutiara Al Jufri Airport. The standard refers to the ICAO. Based on the calculation result obtained that in the exixting condition, the length and width of the runway is 2,510 x 45 m and the width of taxiway is 23 m and the dimension of the apron are 373 x 311,2 m. In 2027, the length of the runway will be 3786 m with a width of 45m, and the width of taxiway 23 m. Apron dimension 541,5 x 195,5 m2. In 2037, the dimension of the runway and taxiway are still fixed, but the apron dimension changes to 714 x 195,5 m.
 Keywords: Mutiara Sis Al-Jufri Palu Airport, Runway, Taxiway, Apron