Aeronautical Engineering

It is a precious knowledge of ancient india. this script was originally composed by mahrshi BHARADWAJA, the great indian sage around 5000 BC  ,it content english transtation of some of its sanskrit stotras and shlokas.before wright brothers first aircraft was made by dr Talpade was an Indian scholar who is said to have constructed and flown an unmanned airplane in 1895 with reference of this ancient hindu sanskrit manuscript .

Written for students of aeronautical engineering and based on a range of detailed aircraft design projects, this wide-ranging book draws together the elements of aircraft design and will support any aircraft design project. Written by experienced U.K. and U.S. based authors this is a unique resource that opens up the initial design process, explores the experience of others on similar projects, and clarifies the processes that are behind the equations and calculations used in aircraft design. Armed with this knowledge, readers will be freer to concentrate on the innovative and analytical aspects of their own project work. Key features include: demonstration of how the basic design process can be successfully applied to a wide range of aircraft; highly illustrated case studies that provide a valuable teaching and learning tool, examining how others have approached particular design challenges; and coverage of commercial, military, and concept aircraft design, plus award winning student projectsthat offer an insight into the conceptual design process from the student perspective.

The paper is about preliminary sizing and analysis of a trainer aircraft wing. The main objective is to fix an appropriate
structure within the given envelope and to estimate the Gross take-off weight, wing loading, Stress distribution, low
frequency vibrational modes, take-off distance and stall velocity. Sizing is done by using classical engineering theories and
FEA packages. Skin and web are considered as shell elements. Flange, spar and stringer are considered as beam elements.
From the analysis structure has been optimally designed which satisfies the strength and stability criteria. The detailed
design of trainer aircraft wing structure is modelled using CATIA V5 R20. Then stress analysis of the wing structure is
carried out by using the finite element approach with the help of MSC NASTRAN/PATRAN to find out the safety factor of
the structure.

Vent holes can be used to reduce the aerodynamic pressure loads on nonstructural elements of buildings. The analysis of these loads applied on nonstructural elements of buildings (window panes, closure panels, etc.) with vent holes, under gusty wind conditions, have been studied both experimentally and employing a theoretical model. An experimental setup based on an open circuit, closed test section, and low speed wind tunnel, designed and built at the Instituto de Microgravedad “Ignacio Da Riva” of the Universidad Politécnica de Madrid (IDR/UPM) has been used. A mechanism in the wind tunnel generates sinusoidal gusty winds inside the test section. Theoretical predictions of the pressure loads have been obtained using a mathematical model based on the mass conservation equation and polytropic law gas evolution. In the experimental setup, an air reservoir with a vent hole has been selected as a model to simulate the internal pressure loads acting on the walls of a building under a ta...

The role of transverse shear is crucial in modeling ultrasonic wave propagation in composites. The approximate plate theories have been extremely useful in providing solutions to problems involving static and dynamic loadings of uniform or laminated plates of finite dimensions. Moreover, since their simple formulations, they can also be useful for solving wave propagation problems in laminates of finite thickness and large lateral dimensions. A four-node plate bending element based on first order shear deformation theory is used in this work to predict the propagation velocity of first antisymmetric Lamb wave mode in graphite/epoxy composite plates by numerical simulation. Calculations are made using material properties obtained from a unidirectional panel via mechanical tests. For investigation, propagation along multiple directions is evaluated. Experimental and numerical results are compared at different angles of propagation and agreement between experimental and numerical approaches is found. © 2014 Elsevier Ltd.

The common challenge of all aerospace advancements is greening the air transport. This led the recent research programs towards the study of 'metamorphic' wing structures, capable of adapting their geometry to the different conditions of flight. The development of morphing structures allows the reduction of drag and the increase of range, together with the growth of load control effectiveness. In this context, the European research project SARISTU addressed the physical integration of smart and morphing structural concepts, by implementing them on a true scale outer wing belonging to a CS-25 category aircraft finally tested in a large Wind Tunnel. In the framework of SARISTU project, the design of an Adaptive Trailing Edge Device was developed. The morphing skin concept consisted of a segmented skin, with aluminum and silicone foam strips covered by a protective silicone top-layer. A two-bay demonstrator was tested inside the Wind Tunnel at the Department of Industrial Engineering of the University of Naples 'Federico II'; experimental analyses were performed in order to verify whether the silicone parts could show out of plane bumps induced by the aerodynamic loads occurring during the Wind Tunnel test campaign. A photogrammetric optic approach was adopted, in order to reach the aforementioned targets in a non-invasive way; such methodology was selected due the high resolution assured at a very low implementation costs. Obtained results allowed to confirm the demonstrator well done design and opened the doors to the next experimental test campaign performed in TsAGI Russian Wind Tunnel, on the outer wing equipped with a five-bay demonstrator of the Adaptive Trailing Edge Device. © 2017 IEEE.

This paper is focused on numerical investigations that analyze the advantages obtained from high-aspect-ratio wings with unconventional roll control strategies based on wing twist morphing. The sailplane G103-B, produced by the GROB Werke company, was chosen as the reference aircraft for the analyses. For confidentiality reasons, the data disclosed by the builder covered only general properties such as the main dimensions, the lifting surface airfoils and attitudes, the characteristic speeds, and a rough mass budget. As a consequence of this, "reverse-engineering" was considered necessary to define a reasonable wing structural layout that enabled the analysis of the elastic-aircraft roll dynamics.Apreliminary sizing of the wing structure was addressed using CS-22 airworthiness requirements and by adopting fast elementary approaches. The estimated structural arrangement, which was verified using a finite element analysis, was then used to generate the aircraft aeroelastic model. The conventional (aileron-based) and the unconventional (wing twist morphing) roll control strategies were compared from the aerodynamic and the aeroelastic standpoints, and the benefits achieved with the unconventional strategy are summarized.

Integrated System Health Management (ISHM) is a promising technology that fuses sensor data and historical state-of-health information of components and subsystems to provide actionable information and enable intelligent decision-making regarding the operation and maintenance of aerospace systems. ISHM fundamentally relies on assessments and predictions of system health, including the early detection of failures and estimation of Remaining Useful Life (RUL). Model-based, data-driven or hybrid reasoning techniques can be utilized to maximise the timeliness and reliability of diagnosis and prognosis information. The benefits of ISHM include enhancing the maintainability, reliability, safety and performance of systems. The next evolution of the ISHM concept, Intelligent Health and Mission Management (IHMM), delves deeper into the utilization of on-line system health predictions to modify mission profiles to ensure safety and reliability, as well as efficiency through predictive integ...

https://www.ijert.org/chandrayaan-2-indias-2nd-lunar-exploration-mission

https://www.ijert.org/research/chandrayaan-2-indias-2nd-lunar-exploration-mission-IJERTV9IS070499.pdf

Chandrayaan-2 was a great achievement for India and the mankind and it made a history as 1 st mission in the world which was projected on the southern pole of moon. This region always remains in darkness and temperature is extreme cold there and these two things are most dangerous and affect negatively on mission. Therefore it was very challenging mission for India and entire world was curious about its success. Its budget was 9.62 billion Indian rupees and it is the most expansive space mission of India till now. Chadrayaan-2 consisted of 3 parts; Orbiter, Lander and Rover. This mission was launched in 2019. In this mission, Orbiter was successful its mission to reach in moon's orbit but unfortunately communication was lost with Lander which causes Lander did not perform well and it crashed along Pragyan rover and other sciencetific equipments. This paper presents a detailed review about Mission Chandrayaan-2 and its landing failure.

— In digital communication system, digital information can be sent on a carrier through changes in its fundamental characteristics such as phase, frequency and amplitude. The use of a filter plays an important part in a communication channel because it is effective at eliminating spectral leakage, reducing channel width, and eliminating interference from adjacent symbols (Inter Symbol Interference) ISI. It describe the developed and dynamic method of designing finite impulse response filter with automatic rapid and less error by an efficient genetic and neural approach. GA and Neural are powerful global optimization algorithm introduced in combinational optimization problems. Here, FIR filter is designed using Genetic, Neural approach by efficient coding schemes. We need to design these filters with some constraints imposed by requirements of the communication system in which we are going to use them. The use of optimization techniques have been proved to be quite useful towards the design of those digital filters with certain specifications. This paper reviews about the uses of optimization systems in digital filter design.

Significant interest towards unmanned aerial vehicles (UAV) has developed nowadays. These aircraft systems are designed to carry out certain missions such as surveillance, reconnaissance, and monitoring in civil, military and custom applications. Due to the various requirements and mission constraints, various UAV configurations exist, among which conventional and morphing aircrafts. The latter category refers to aircrafts whose configuration can be altered to achieve certain performance characteristics, namely increased flight range and endurance. This paper discusses the design process and manufacturing of a remote-controlled, experimental UAV for two wing configurations: fixed and variable span, in order to assess the potential benefits of a morphing-wing aircraft. The morphing actuation is projected to be by means of a belt-and-pulley mechanism. The aircraft is intended to transmit live images to a ground station, transmitted from a camera attached underneath the fuselage.

Significant advances in sensor technology, along with economies of scale due to large production volumes have supported the miniaturization of navigation sensors, allowing widespread low-cost integration on Unmanned Aircraft Systems (UAS). In small-size UAS applications, standalone sensors are not a viable option since the reduction in navigation sensor form-factor, weight and cost typically results in lowered accuracy and precision. Fusion of multiple sensor measurements in UAS navigation systems can support greater accuracy, integrity and update rates than is achievable employing individual sensors. This chapter introduces the fundamentals of state-estimation methods employed on UAS and presents different sensor integration architectures, along with an assessment of their advantages and trade-offs. Attention is devoted primarily to recursive optimal estimation algorithms such as the Kalman Filter and its variants owing to its prolific employment in various classes of UAS. The need to support robust navigation performance in Global Navigation Satellite System (GNSS) denied environments, and the proliferation of visual sensors has led to the development of numerous methods for integrating visual sensor measurements (primarily) with inertial sensors. Therefore, the reader is introduced to the most popular system architectures for visual-inertial sensor integration, in order to provide an understanding of the current state-of-the-art and to support the identification of future research pathways.

This paper summarizes the results of the design study and provides a description of three morphing wing devices developed for a turboprop regional aircraft in the framework of the Clean Sky 2 REG-IADP Airgreen 2 project. In sinergy with a natural laminar flow wing, morphing wing technologies are investigated to improve both high-lift performance and aerodynamic efficiency in off-design conditions of the aircraft, by demonstrating also load control and alleviation capabilities over the flight envelope. The combined use of a deformable droop nose and a multifunctional morphing flap, designed by PoliMi and UniNA respectively, is able to meet the minimum high-lift performance requirement of the AG2-NLF aircraft for both take-off and landing conditions. The controlled flap is deployed during take-off by using a fairingless concept, totally hosted in the wing, that offers additional benefits on structural weight and aerodynamic efficiency at high speed. The flap camber is then morphed to gain the extra lift required for landing operations. An adaptive winglet concept, designed by CIRA, is also presented to further enhance aircraft aerodynamic efficiency also in climb/descent conditions by lowering at the same time wing-bending moments due to aircraft maneuvers. Such a mechanical system is characterized by two movable surfaces aimed at performing variable camber and differential tab settings depending on the flight conditions. Both aerodynamic performance and benefits of the three morphing devices are assessed by ONERA on the natural laminar flow wing.

TURCAN
Greatly Reduced Turbulence and Drag of Aircraft
Repetitive MetaStable Cancellation of Turbulence
Flow in large Pipelines can also be improved
All aircraft except gliders have enormous turbulence losses during flight.  Gliders are only excepted because they fly so slow that better airflow patterns exist, where less turbulence occurs, and that the effects of turbulence regarding energy goes as the second power of airspeed.  An aircraft flying at 500 mph has around 400 times more aerodynamic (drag) energy losses than if the same size-and-shape glider was flying at 25 mph.
An Active Skin technology has been invented, TURCAN, where the vast majority of turbulence is eliminated.  Theoretically, total aerodynamic drag might be reduced to 1/7 current drag factors, meaning that fuel would then last around 7 times as long or as far!




More practically, this new TURCAN technology should be able to reduce total aircraft drag to about half of current levels.  This would DOUBLE fuel economy.  Instead of an airline having to buy $120,000 of jet fuel for a specific trip, maybe only $60,000 would need to be bought!  Then, with the gross airframe weight being 150,000 pounds less at takeoff (due to not needing to load those thousands of extra gallons of Jet Fuel) the overall efficiency would be even greater than that!
Below, reference is made to the US government spending millions of dollars to try to improve overall efficiency by 1.5%, several years ago.  Interesting, since they never showed any interest in THIS TURCAN technology which would CERTAINLY improve efficiency by 50% and probably 100% or more!

For the hundred years of powered flight, it has always been accepted that very large amounts of drag from air turbulence was unavoidable.  This fact is closely related to the fact that virtually all aircraft are designed to use BOTH of two very different methods of creating Lift, called Bernoulli Lift and Reaction Lift, and the Reaction Lift is notoriously bad regarding creating massive turbulence and loss.  There appears to be a method, TURCAN, to meta-stably eliminate most of that turbulence, and therefore most of the drag which must be overcome.  The result would be extremely efficient flight, using far less than half as much aviation fuel to accomplish the same performance, and possibly less than one-fourth as much fuel consumption, without otherwise changing performance.
Powered aircraft must produce forward "thrust" to overcome rearward "drag" and then also be able to accelerate forward.  The forward thrust also enables aerodynamic lift to occur, which balances the weight of the aircraft.  Much of the drag that exists that is associated with airfoils (wings) is due to turbulence that develops along the top of airfoil and behind the airfoil surface.  In many situations regarding Bernoulli Lift, around 6/7 of the total drag is due to this turbulence, with only 1/7 actually being unavoidable.
Until now, very sleek airfoil shapes and relatively thin wings have been the standard ways of trying to minimize this turbulence effect.  However, these sleek shapes also necessarily have less Bernoulli lift effect, due to standard physics and aerodynamic reasons.
Another trend in modern aviation is due to the enormous power now available in aircraft engines.  It is the reliance on a second manner of lift, "reaction lift".  This type of lift is entirely due to the wing surface being tilted, so that oncoming air is deflected down by impact against the bottom of the wing.  This is simple Newtonian action-and-reaction.  Massive amounts of air is given a downward Momentum, which again according to Newton, necessarily creates an upward Momentum to the wing structures.  Unfortunately, that type of lift creates even more drag due to massive turbulence behind and above the wing surface.  With plenty of power available, that is not a problem, but it causes much more consumption of jet fuel.

— Designing an efficient Distributed Database System (DDBS) is considered as one of the most challenging problems because of multiple interdependent factors which are affecting its performance. Allocation and fragmentation are two processes which their efficiency and correctness influence the performance of DDBS. Therefore, efficient data fragmentation and allocation of fragments across the network sites are considered as an important research area in distributed database design. In this paper presents an approach which simultaneously fragments data vertically and allocates the fragments to appropriate sites across the network. Bond Energy Algorithm (BEA) is applied with a better affinity measure that improves the generated clusters of attributes.

https://www.ijert.org/analysis-of-morphing-airfoil-structures-and-fabrication-of-the-wing-using-the-concept-of-additive-manufacturing

https://www.ijert.org/research/analysis-of-morphing-airfoil-structures-and-fabrication-of-the-wing-using-the-concept-of-additive-manufacturing-IJERTV9IS060054.pdf

This paper briefs about the morphing airfoil with variable camber and it makes use of compliant rib mechanism. Lightweight system for actuation, complaint internal structure and a flexible skin are some of the key requirements for such mechanisms. Wing morphing is a biologically inspired technique where-in, the change in shape of wings can offer various advantages compared to the conventional solutions we currently have. In this research, we have used the combination of materials such as PLA and TPU in the wing prototype that are printed using the concept of additive manufacturing. To meet desirable shape changes, stiffness can either be tailored or actively controlled to guarantee flexibility in the chord-wise (or span-wise) direction with tailored actuation forces. Hence, corrugated structures, segmented structures, reinforced elastomers or flexible matrix composite tubes embedded in a low modulus membrane are all possible structures for morphing skins.

The measurement accuracy of volumetric airflow velocity is a real issue for aircraft. Several aeronautical accidents derive from Pitot sensors static and total pressure measurements. To control and assess Pitot sensors measurement inaccuracy, several techniques and methods are proposed. This paper deals with the need to improve Pitot sensors static ports efficiency by controlling static pressure measurement in order to define measurement inaccuracy factors and therefore to reduce critical situations deriving from this issue.

 Abstract— Distribution design involves making decisions on the fragmentation and allocation of data across the sites of a computer network. Multiple vertical splitting is the process of subdividing the attributes of a relation to generate fragments. In this paper, we propose an analysis for multiple vertical splitting algorithm using Slop Based Partitioning Algorithm (SBPA). This approach starts from the attribute affinity matrix and generates initial clusters based on the affinity values between attributes. Then, it uses the database according to optimal splitting solution to produce final groups that will represent the fragments. Then we analyzed these fragments according to their contribution level. The result is generated that shows how to find optimal solutions.

The current project is a study of the Laplace equation that is used nowadays in many applications related to the electrical, magnetic, gravitational potentials, steady state temperatures, and in hydrodynamics.. The system corresponds to an elliptic second order partial differential equation and is widely used in the study of the inviscid incompressible potential flow in fluid mechanics. To solve this equation, numerical methods are used and different schemes are introduced to better control the solution through stability, accuracy and consistency. In what follows, a numerical study and investigation of the 2D Laplace Equation.

— Thermo-physical properties of butter, hydrogenated fat, palm oil, coconut oil, sunflower oil, and groundnut oil were examined. Experimental results revealed the highest slip melting point (38oC) and specific gravity for hydrogenated fat whereas the lowest slip melting point (-18oC) and hardness values for sunflower oil. However, sunflower oil showed the highest refractive index. The consistency of butter and hydrogenated fat was reported acceptable plastic and spreadable. Palm oil was found soft and spreadable. The melting curve of palm oil, butter, and hydrogenated fat showed two endothermic peaks. However, coconut oil, sunflower oil, and groundnut oil showed only one peak. The solid fat content (SFC) of butter, hydrogenated fat, palm oil, and coconut oil were found within the recommended range for baking performance. Melting enthalpy was strongly correlated to hardness (r = 0.8604, P < 0.001) of fat and oil samples. Correlation coefficient (r) of 0.8977 (P < 0.001) was found between SFC and hardness. The results strengthen the premise that hardness of the fat is not dependent solely on the SFC and as the results demonstrated that the melting enthalpy also plays a key role in influencing the hardness of fats and oils.

Data analytics seems a promising approach to address the problem of unpredictability in MRO organizations. The Amsterdam University of Applied Sciences in cooperation with the aviation industry has initiated a two-year applied research project to explore the possibilities of data mining. More than 25 cases have been studied at eight different MRO enterprises. The CRISP-DM methodology is applied to have a structural guideline throughout the project. The data within MROs were explored and prepared. Individual case studies conducted with statistical and machine learning methods, were successfully to predict among others, the duration of planned maintenance tasks as well as the optimal maintenance intervals, the probability of the occurrence of findings during maintenance tasks.

The requirements set by the most important Air Traffic Management (ATM) research initiatives (SESAR and NextGen) and environmentally sustainable aviation research initiatives (Clean Sky, and Environmentally Responsible Aviation), aim at lowering operating costs and improving the environmental sustainability of aviation. In line with these requirements, the methodology of using noise modelling and simulation techniques in conjunction with Demographic Distribution Database (D3) and Digital Terrain Elevation Database (DTED), allows the development of novel approaches and algorithms for aircraft trajectory optimisation in the present and likely future airspace scenarios and, in particular, in proximity of airports and densely populated areas. Aircraft noise modelling in major Australian airports is essential in order to understand the noise impacts associated with air traffic, determining the Australian Noise Exposure Forecasts (ANEFs) and to assist in effective airport planning strategies. Based on the statuary requirements prescribed, the aircraft trajectories are optimised to minimize the effects of noise around the airports considering both population and digital terrain data. The key mathematical models for noise and trajectory optimisation are presented. The objective of the noise modelling process is to describe the noise parameters currently adopted for airport design and operations, and to predict values for all relevant future scenarios. Noise analysis and impact mitigation measures are discussed. Quantification of noise at the major Australian airports, including Sydney and Melbourne airports is presented.

This paper addresses one of the recognized barriers to the unrestricted adoption of Unmanned Aircraft (UA) in mainstream urban use—noise—and reviews existing approaches for estimating and mitigating this problem. The aircraft noise problem is discussed upfront in general terms by introducing the sound emission, propagation, and psychoacoustic effects. The propagation of sound in the atmosphere, which is the focus of this paper, is then analysed in detail to isolate the environmental and operational factors that predominantly influence the perceived noise on the ground, especially looking at large-scale low-altitude UA operations, such as in the envisioned Urban Air Mobility (UAM) concepts. The physics of sound propagation are presented, considering all attenuation effects and the anomalies due to Doppler and atmospheric effects, such as wind, thermal inversion, and turbulence. The analysis allows to highlight the limitations of current mainstream aircraft noise modelling and certifi...

— Preliminary investigation on laterite soil sample collected from old Julius Berger borrow pit in Ejio area of Arigbajo in Ifo Local Government Area, Ogun State (6.849˚N, 3.211˚E), classified the soil as A-2-7(4) [AASHTO classification]. The soil was mixed with Banana Leaf Ash (BLA) in varying percentages of 0%, 2%, 4%, 6%, 8%, 10%, and 12% and the effect of BLA on the soil sample was determined for Liquid Limit, Plastic Limit, Compaction (MDD % OMC), CBR and Unconfined Compression Test. These tests were repeated for the soil sample + BLA + cement. The results of the treated soil showed increase in the plastic limit, liquid limit, plasticity index and optimum moisture content (OMC) as the BLA content increased. The values of maximum dry density (MDD), California Bearing Ratio (CBR) and Unconfined Compressive Strength (UCS) increased up to 2% BLA before starting to decrease steadily. This implies that the Banana Leaf Ash (BLA) is a weak pozzolan. Index Terms— Laterite; Banana Leaf Ash (BLA); Stabilization; California Bearing Ratio (CBR); Unconfined Compressive Strength (UCS)

By introducing the progresses on Morphing currently achieved within the European Project “AIRGREEN2”, in Clean-Sky 2 GRA platform, this work presents a review of the research step forwards accomplished in the last decade by three Italian Partners largely active in the field: the Italian Aerospace Research Centre, the University of Naples “Federico II” and the Politecnico of Milano. A chronologic overview is at first presented, revisiting the research programs and the achieved results; an organic development path has been then built, starting from low TRL achievements up to arrive at the most complete technical accomplishments, characterized by a high level of integration and targeting specific aerospace applications.

Weeds in the wet paddy field were plucked by manually with use of hand tools and collectively taken away during some years ago. Now-a-days weeds are being utilized as fertilizer. Manual weeder is a device which is having two cylindrical rollers is mounted on the metallic frame structure with handle. It's a push and pull type of operation where a person pushes the device in forward direction for about 3 feet and then pulls back for the same distance and the operation repeats accordingly. While pushing action, weeds are uprooted. While pulling action, those uprooted weeds are buried there itself. To overcome from push and pull operation, this project provides a Semi automatic weeder which operable in only in forward direction. Semi automatic weeding device is same as manual weeder with implementation of a petrol engine, spur gears, chain and sprockets arrangements. The device is developed in such a way that, the front roller rotates clockwise and uproots the weeds and soil gets loose. The rear roller automatically rotates anticlockwise and buries those roots simultaneously. One of the major challenges in this project will be pushing the device in forward direction which reduces human fatigue and increases productivity. The design will be considered for easy handling and to not to increase the weight of the device.

In this article, machining characteristics of titanium alloy grade-5 (Ti–6Al–4V) have been examined at different cutting speeds, feed rates and approaching angles under dry condition. It has been observed that with the increase in cutting speeds, the magnitude of cutting forces and tool tip temperature increase. If both cutting force and temperature level were considered together, the optimum approaching angle works out to be 45° and 90° for 49.5 and 76.7 m/min, respectively. For 116.9 m/min increase of cutting forces at 60° approaching angle can be attributed to low-shear angle which is function of the average chip thickness. Positive rake angle produces higher shear angle which leads to the reduction of cutting forces, tool tip temperature and thus help obtaining a better surface finish. Surface roughness measurements obtained prior and subsequent to the machining of titanium alloy (Ti–6Al–4V) were used to characterize the change in roughness caused by variation in machining parameters like cutting speed, feed rate and approaching angle. The average surface roughness is observed to be maximum at 0.11 mm/min and minimum at 0.04 mm/min feed rate for all approaching angles.