Aeronautical Engineering

The Black Nightmare Bombardier V.7.3 is an advanced hydrogen-powered unmanned aerial vehicle (UAV) integrating cutting-edge stealth, AI guidance, and vectoring aileron technology. With superior maneuverability, an extended operational range, and an innovative defensive missile system, this UAV redefines modern aerial combat capabilities.

In contemporary architecture there is an increasing demand for transparency and curved shape. The Cold-Bending process is an effective and relatively inexpensive way of creating double curved surface glass. This thesis focuses on the shaping of a plate with the application of an out-of-plane displacement at its corner, also called cold-warping.

conjunto de aerogeneradores con el objeto de proveer de energía eléctrica para el alumbrado público y para una radio FM del lugar. Con el transcurso del tiempo se observó que los aerogeneradores no cargaban las baterías. Se desmontó entonces uno de ellos y se los ensayó en el Campus Universitario. Se evaluaron una curva de carga "real" de batería, y por consiguiente la cantidad de energía que es capaz de proveer el equipo y otras. Se observaron además, fallas en el controlador de carga; los resultados se presentan en este trabajo. Palabras clave: Aerogeneradores, ensayo de aerogenerador, cargas de acumuladores, sostenibilidad San Isidro es un pueblo de montaña, cuya calle principal se muestra en la Figura 1, ubicado a 3100 metros sobre el nivel del mar, 22.75º Latitud Sur, 65.25º Longitud Oeste, cuyas características fueron descriptas en un trabajo anterior [1]; en este lugar se instalaron los aerogeneradores que muestra la Figura 2, en la misma torre se instaló un anemómetro.

The Russian MC-21 commercial aircraft, developed by Irkut Corporation under the United Aircraft Corporation (UAC), represents a significant advancement in Russia's aerospace industry. This paper explores the features of the MC-21, its competitive position against Western counterparts like the Boeing 737 MAX and Airbus A320neo, and its potential impact on the global aviation industry. Additionally, it examines the benefits the MC-21 could bring to developing nations, including countries like Sri Lanka, in terms of affordability, accessibility, and economic opportunities in aviation.

The steering column is constructed by front suspension forks in most two wheelers. The paper focuses on the Finite Element Analysis of the suspension fork for motor bike, and developing an empirical equation in terms of internal diameter and central bush wall thickness. Finite element analysis has been done to verify the analytical analysis done with the help of thick wall theory. An empirical relation is necessary as different combinations of internal diameter and bush wall thickness are available in the industry. The empirical relation can be utilized to design a new fork for two wheelers.

Ich bin all jenen zu Dank verpflichtet, die diese Arbeit möglich gemacht haben und mit ihrer unbezahlten Mühe in Form von Abschlussarbeiten und Projektarbeiten Vorarbeit geleistet haben. Zwar ist umfangreicher Aufwand oft in wenige Sätze und einzelne Bilder komprimiert (entsprechende Stellen sind gekennzeichnet), um dann allerdings darauf aufzubauen und weiter in die Tiefe zu gehen. Die Kürze verbirgt, wie wichtig diese Grundlagen sind. Zu nennen sind besonders Timon Eckstein, Bernd Eisenbarth und Gent Cerimi. Ich danke meinen Freund*innen, die meine Stimmung aufgebessert haben und die Rechtschreibung und Form der Arbeit verbessert haben. Danke an die Mitarbeiter im Robotiklabor, für Unterstützung und Ablenkung.

The paper presents initial application and further development of a resilience engineering (RE) assessment method to the multiple remote towers (MRTWR) concept. The RE method is operationalised through a set of eight principles identified from existing RE literature. These principles are 1) Work-as-Done; 2) Varying conditions; 3) Signals and Cues; 4) Goal trade-offs; 5) Margins and adaptive capacity; 6) Coupling, interactions and cascades; 7) Timing, synchronisation and time scales; and 8) Under-specification and approximate adjustments. The application of the RE method to the concept of MRTWR has helped to understand the significance of the change and associate design requirements at a larger scale, focusing not only on the function of specific components, but on the ATM system as a whole. Results from this application show how understanding everyday operations (work-as-done) helps to evaluate the gaps between current and envisaged design of a new operational concept (MRTWR). Based on work-as-done the principles are used to develop design requirements how to enhance resilient performance of systems. Sharing this experience may offer practitioners and researchers from aviation and other domains the opportunity to build on lessons learnt from this application to investigate how resilience can be enhanced in their systems.

An in-house method of Newton-Euler inverse dynamics guidance based on a simplified airplane model in horizontal flight was proposed in a previous paper presented at NMAS 2018 workshop [1]. The goal was to guide the airplane between two locations situated at 100 km distance

In this work welded joints made of dissimilar steels: Maraging (18Ni) and 300M-ESR steel by the laser beam welding process (LBW) was evaluated. After the laser welding, different heat treatments were applied with the purpose to approximate the hardness of both steels in the fusion zone and heat affected zone. Subsequently, the joints were submitted to tensile and microhardness test for mechanical properties evaluation. Metallographic analyses of the welded joints were also performed and the microstructure and mechanical properties were correlated. The heat treatments applied after welding proved to be convenient for improvement of the hardness and the tensile strength. The increase in tensile strength due to the heat treatment applied after the welding was about 400 MPa. The laser welding process proved to be efficient to achieve the union of the proposed dissimilar steels and the heat treatment applied contributed to improve the mechanical properties.

From Pioneering Satellites to a Youth-Led Space Revolution As we celebrate National Science Day, I reflect on the extraordinary life of Professor Vasagam, a legendary figure synonymous with India's space program. More than just a scientist and educator, he was a visionary who possessed a remarkable ability to foresee the future, a future he tirelessly pursued through the power of technology. This memoir is my heartfelt reverence for his enduring legacy.

We investigated students' understanding of satellite motion around the Earth. For that purpose, we surveyed high-school and university students from Croatia. With the objective of gaining insight into teachers' understanding of students' abilities, physics teachers were asked to predict students' answers. The results of the study suggest that most students have difficulties with providing physically based explanations. They tend to approach such problems through the use of phenomenological primitives. Specifically, they tend to use the "closer is stronger" p-prim when attempting to identify the satellite orbit which would ensure receiving satellite television signal at a certain location paying no attention to the direction of the gravitational force. We found no statistically significant association between the students' ability to correctly explain the satellite motion and their educational background. The teachers considerably overestimate students' abilities. Generally, the results of this study suggest that diagram-based problem can be useful tool for probing students' understanding of satellite motion.

A method is presented whereby incremental pitching moments can be estimated for swept and triangular wings having arbitrary types of trailing-edge high-lift flaps. In the method use is made of span-loading theory together with two-dimensional airfoil data adjusted for the effects of sweep. The method as presented was limited to low speeds and small angles of attack. Application of the method is demonstrated for some 58 cases covering various types of flaps on wings having a wide range of sweep, aspect ratio, and taper ratio. For all wings, swept as well as triangular, a mean deviation from experiment of about 0.02 in incremental pitchingmoment coefficient was found. Two-dimensional-flap data pertinent to the general application of the method are summarized in graphical form.

Tests in the Ames 40-by 80-foot wind tunnel of the static longitudinal characteristics of the Republic RF -84F were made to determine both the origin and a suitable remedy for a pitch up tendency of the airplane encountered at moderate lift coefficients. The results indicated that the pitch-up at moderate lift coefficients was caused by an abrupt change in downwash at the tail which in turn was traceable presumably to flow conditions associated with the inlet-to-wing leading-edge discontinuity.. Attempts to eliminate this pitch-up characteristic with various fairings and stall-control devices. were not wholly successful. The investigation revealed, however, that significant gains in the performance of the airplane could be achieved in the upper lift range.. Three different configurations consisting of a partial-span modified leading edge combined with one or with two-fenees or a leading-edge extension each delayed the onset of separation to higher lift coefficients and provided large improvements in the stability of the airplane in the upper lift range.

A method is presented whereby incremental pitching moments canbe estimated forsweptandtriangular wingshaving arbitrary typesof trailing-edge high-lift flaps.In themethod useismadeof span-loading q theory together withtwo-dimensional airfoil dataadjusted fortheeffects of sweep.Themethod as presented waslimited to lowspeeds andsmall q angles of attack. Application of themethcxl is demonstrated forsane58 casescovering various t~es of flapson wingshating a tiderangeof sweep, aspect ratio, andtaperratio.Forallwings, sweptas wellas triangular, a meandeviation frcmexperiment of about0.02in incremental pitchingmomentcoefficient wasfound. Two-dimensional-flap datapertinent to thegeneral application of themethod aresummarized in graphical form.

A study has been made of the application of two-dimensional data and span-loading theory for estimating the local loading characteristics on a swept wing with flaps. Estimated results, including local pressure distributions, span loadings, and the nonlinear local lift characteristics, are compared with similar results measured at large scale on a 45 0 sweptback wing of aspect ratio 6 having a O.4-epan double-elotted flap both with and without a full-span slat. Two-dimensional pressure distributions when corrected for sweep were found to agree closely with the wing pressures for most local sections either on or off the flap. This agreement continued to the higher lift coefficients and even improved near maximum lift where the flap-induced effects became minimized. The Weissinger 7Xl method was found to provide reasonably accurate span lciadings for this awept-wing configuration which had a relatively highly loaded type of flap. Twodimensional lift data, together with span-loading theory, afforded quite accurate estimates of the local nonlinear lift characteristics, includiLg maximum lift of sections outboard of the flap but were inadequate for inboard sections of the wing where the three-dimensional boundary-layer control exercises a dominant effect.

The convergent-divergent design of the nozzle of a rocket engine is the most defining part of it. The nature of the nozzle design enables it to convert the high pressure, temperature and relatively low velocity adiabatic expanding gaseous fluids into very high velocity and thrust gases. The rapidly exiting gas as a consequence of the rapid expansion process results in low pressure and temperature. It is critical in research to find out the influence of modification (grooves) would have in the application and design of a reaction device such as a rocket engine. The Computational Fluid Dynamics software, Analysis System (ANSYS) was employed together with necessary boundary conditions to design and simulate such a modified rocket engine nozzle. The interaction and relationship existing among the pressure, velocity, Mach number and temperature in the grooved divergent rocket nozzle was found and observed. From the plots and nozzle simulation contours, both velocity and Mach number increased rapidly along the nozzle area but decreased steadily. Pressure varied directly withtemperature and inversely with density. It is observed that divergent nozzle grooving influences the velocity, Mach number, pressure and temperature within the divergent nozzle area of a rocket nozzle.

A representação do comportamento das substâncias com o uso de equações de estado pode apresentar dificuldades na região próxima ao ponto crítico. As equações de estado podem apresentar desvios significativos nessa região quando se compara os valores calculados via equação de estado com os valores das variáveis de estado obtidos experimentalmente. Com o objetivo de minimizar os desvios na região próxima ao ponto crítico, no caso do eteno, foi feito um ajuste dos parâmetros da equação com o uso de métodos numéricos para se obter uma melhor representação do diagrama de Mollier via equação de estado. O método numérico para o ajuste dos coeficientes da equação -Peng-Robinson modificada por Melhem -foi o método dos mínimos quadrados com ajuste dos parâmetros da equação de modo a aproximar os valores calculados com os valores experimentais. O objetivo desse estudo é obter uma equação que represente comportamento do eteno na região próxima ao ponto crítico sem alterar a equação propriamente dita, ou seja, ajustando apenas os seus coeficientes (PIBIC/UFRGS)

I l potenziamento dei moderni sistemi di cal- colo ha permesso un inaspettato sviluppo della ricerca scientifica e quindi delle sue applicazioni anche nel settore della nautica. Programmi sempre più sofisticati e precisi possono girare su un semplice laptop e hanno costi contenuti e accessibili a tutti. Sia i piccoli cantieri di imbarcazioni da crociera sia i disegnatori di lussuosi mega-yacht, si stanno velocemente fornendo dei più recenti strumenti di progettazione e gestione dei processi. La diffusione di nuovi programmi di calcolo nasconde dietro a sé lo sviluppo di nuove tecnologie e conoscenze, frutto del lavoro di ricerca condotto negli ultimi anni in vari settori scientifici tra cui l'analisi numerica, il software design e la visualizzazione scientifica (Figura 1). Come avviene in molti altri settori, per esempio quello dell'automotive, anche nella nautica, una delle maggiori opportunità per la ricerca scientifica risiede nelle competizioni sportive in grado di muovere ingenti capitali che giustificano importanti investimenti nella ricerca. Inoltre, regate come l'America's Cup (AC) sono

The popularity of air travel has resulted in several new technologies and research to build more efficient and quicker planes. An aerofoil is a curved surface structure designed to maximize lift and drag during flight. The airfoil is critical in any plane because it provides the lift required to raise the plane with the least drag. It is challenging to create an airfoil with the necessary aerodynamic properties. Initially, the design was randomly generated and evaluated in a flow section. And then there is the Wright Brothers' cambered portion. NACA has defined an airfoil properly, enabling us to build airfoils using formulae rather than arbitrarily. An aerofoil structure has a curved surface utilized as the fundamental shape of wings and fins in most aircraft. The present study examines the experimental and analytical development of pressure variation, drag lift forces, and other aerofoil section characteristics. The study is based on modeling fluid flow via a symmetrical and asymmetrical aerofoil in a wind tunnel. Ansys software is used to conduct the simulation. This article presents a comparative analysis of symmetric and asymmetric aerofoils.

Bird Flight as a Model for a Course in Unsteady Aerodynamics JAMEY JACOB, JONATHAN MITCHELL, MICHAEL PUOPOLO, Oklahoma State University -Traditional unsteady aerodynamics courses at the graduate level focus on theoretical formulations of oscillating airfoil behavior. Aerodynamics students with a vision for understanding bird-flight and small unmanned aircraft dynamics desire to move beyond traditional flow models towards new and creative ways of appreciating the motion of agile flight systems. High-speed videos are used to record kinematics of bird flight, particularly barred owls and red-shouldered hawks during perching maneuvers, and compared with model aircraft performing similar maneuvers. Development of a perching glider and associated control laws to model the dynamics are used as a class project. Observations are used to determine what different species and sizes of birds share in their methods to approach a perch under similar conditions. Using fundamental flight dynamics, simplified models capable of predicting position, attitude, and velocity of the flier are developed and compared with the observations. By comparing the measured data from the videos and predicted and measured motions from the glider models, it is hoped that the students gain a better understanding of the complexity of unsteady aerodynamics and aeronautics and an appreciation for the beauty of avian flight.

An attempt has been made in this research work to probe the sequel of initial grain size of the steel and its impact on tensile strength. Low carbon-manganese steel in respect of initial grain size and final grain size has been deliberately investigated. Two steel samples having similar chemical composition were austenized at temperatures of 925°C and 1100°C respectively with same holding time in the box furnace followed by quenching. Initial microstructure at 925°C and 1100°C were calculated as 62.34 um and 124.4 um respectively. Just after heat treatment both the samples were prepared for tensile testing as per standard. UT machine was used with a cross head speed of 0.5 mm/min. The raw data obtained from the UT were analyzed stress and strain equations and stress-strain diagram was plotted by using origin software. It was concluded that the sample with initial grain size of 62.34 um showed high elongation curve and large plastic range. The large grain sized samples having initial...

the future standard ARP-6983|ED-324 "Recommended Practice for Development and Certification/Approval of Aeronautical Safety-Related Products Implementing ML" is dedicated to machine learning AI technique. It provides a set of objectives and process to support the development and the certification of aeronautical system using AI ML technique. This article presents two products that include AI components or may include in the future: TopSkySequencer and Conflict Detection and Resolution (CDR). The first one embeds a supervised Deep Learning based component and the second a Deep Reinforcement Learning based component.

Though it is easier to model and create an airfoil profile in CAD environment using camber cloud of points, after the creation of vane profile it is very difficult to change the shape of profile for analysis or optimization purpose by using cloud of points. In this paper, we investigate and described the creation of airfoil profile in CAD (CATIA) environment using the control point of the camber profile. By means of changing the values of control points, the shape of the profile can be easily changed and also the design of the cambered airfoil was established without affecting the basic airfoil geometry. In this paper, the Quintic Reverse Engineering of Bezier curve formula was used to find the camber control points from the existing camber cloud of points.

O sucesso do projeto aeronáutico está diretamente relacionado às metodologias utilizadas na elaboração e organização do trabalho, de forma que possibilite ao projetista uma visão global do projeto, mantendo a flexibilidade e troca de informações entre as etapas de desenvolvimento deste, mesmo considerando o elevado nível de conhecimento envolvido. Entre estas etapas, destaca-se pela importância e complexidade o projeto aerodinâmico, estabilidade e controle de uma aeronave, em razão do fato de que esta fase permite ao projetista determinar as condições de voo da aeronave, capacidade de carga, níveis de estabilidade e dimensionamento das superfícies de comando. Ao término desta etapa é possível obter as dimensões primárias da aeronave que influenciarão diretamente qualquer outra etapa desenvolvida. Ainda, o sucesso do voo da aeronave, bem como a aeronavegabilidade, estão relacionados com os resultados obtidos nesta fase do projeto. Assim, este trabalho tem como objetivo fornecer ao leitor as informações necessárias, embasado na literatura técnica para desenvolver a análise e dimensionamento aerodinâmico, estabilidade e controle de veículos aéreos não tripulados. Os veículos aéreos não tripulados (VANT's), ou, do inglês, unmanned aerial vehicles (UAV's) são definidos como plataformas de vôo, (avião, helicóptero, dirigível, etc.) capazes de operar de forma autônoma ou operada remotamente por terra. Apesar da literatura técnica e científica abordar de forma semelhante os fundamentos do projeto aeronáutico é difícil iniciar o trabalho de uma aeronave tendo em vista o elevado nível de conhecimento exigido e de variáveis envolvidas. No artigo, apresentam-se os procedimentos para o dimensionamento aerodinâmico e de estabilidade e controle com o objetivo de contribuir para o desenvolvimento destas aeronaves. Para apresentar o procedimento de cálculo é tomado como exemplo o projeto desenvolvido por Padilha (2010) referente ao projeto de uma aeronave não tripulada para a aquisição de imagens aéreas. Para melhor entendimento, os procedimentos teóricos e recomendações dos autores são apresentados com os resultados e discussões deste trabalho.

The next paragraphs are meant as a quick summary of some definitions and results in linear algebra necessary to remove the exponential of a matrix from Lagrange's formula and express the solution of a linear system of ordinary differential equations in a more meaningful and manageable form. The topics we need to recap are three: diagonalization of a matrix, the Jordan canonical form, and the exponential of a square matrix.

This paper presents the teaching and research activities carried out at the National University of Cordoba (UNC) on issues directly related to Gas Dynamics. Currently, this University offers three courses on this subject: Gas Dynamics I, Gas Dynamics II and Advanced Gas Dynamics. The first two correspond to undergraduate studies, while the third to graduate studies. Gas Dynamics I is a required subject for all Aeronautical Engineering students at UNC, and represents the most advanced degree course within the area of Fluid Mechanics taught at the Department of Aeronautics. While Gas Dynamics II is an elective course that is only taken by students who are interested in deepening concepts in compressible flows. On the other hand, Advanced Gas Dynamics is a valid course for the Aerospace Master's Degree and the Doctorate in Engineering Sciences. In addition, the growth in activity at the UNC in recent years stands out, both in the number of professors trained in the area, as well as in the number of Undergraduate, Master and Doctoral Theses and in the number of research projects.

Se conoce como magnetogasdinamica o MGD para abreviar, a la rama de la mecanica del continuo que estudia el movimiento de un gas electricamente conductor en presencia de un campo magnetico. La MGD computacional representa una de las mas prometedoras tecnologias computacionales interdisciplinarias para el diseno aeroespacial. En la actualidad, en Argentina, se esta desarrollando un propulsor magnetoplasmadinamico de propelente solido (AMPD) como una opcion de propulsion para satelites; en particular, para el control de orbita y/o de actitud de microsatelites. Un modelo MGD se basa generalmente en el supuesto de que el plasma puede considerarse como un medio continuo y por lo tanto se puede caracterizar por relativamente pocas cantidades macroscopicas. El modelo para un flujo afectado por fuerzas electromagneticas incluye el conjunto completo de las ecuaciones de Maxwell, junto con las ecuaciones de Navier-Stokes. Las ecuaciones de la MGD real constituyen un sistema de ecuaciones dife...

El principal objetivo de este trabajo es presentar los resultados obtenidos mediante un codigo computacional que resuelve las ecuaciones de la magnetogasdinamica ideal, inestacionaria y bidimensional (MGD). Las ecuaciones que gobiernan los flujos magnetogasdinamicos son la de continuidad, cantidad de movimiento, energia, induccion magnetica y una ecuacion de estado. En este trabajo dichas ecuaciones son escritas en forma conservativa. El metodo numerico empleado consiste en un seguidor de Riemann aproximado junto al esquema TVD propuesto por Yee. Ademas se ha implementado la tecnica de ocho ondas dada por Powell y la normalizacion de los vectores propios. Finalmente para verificar el adecuado comportamiento del codigo se simula el problema de Riemann introducido por Brio y Wu pero con la malla rotada con respecto a la direccion principal del flujo. Los resultados obtenidos satisfacen los hallados en la simulacion unidimensional.

In the context of aircraft cabin environmental control, the goal of this work is to build a mathematical model of the cabin pressure control system and to simulate it for some important design cases. The developing of the model is based on the recommendation document ARP 1270 (SAE, 2000) with some modifications in order to apply it to a specific aircraft design, developed in academic work. From the model of the cabin pressure control system built for this aircraft, normal flight operation (climb, cruise and descent) and some failure cases are simulated. The first failure event studied is when the outflow valve fails open and the cabin depressurizes. The second one is the failure of the outflow valve in the closed position, with continuous increase of the cabin pressure, and the third failure case is the complete loss of the pneumatic system, another depressurization case. These cases are especially interesting in the initial analysis of the system, allowing the preliminary design of the aircraft's emergency descent profile (depressurizing cases) and safety valve, that prevents great pressure differentials on the cabin (outflow valve fail closed).

This editorial paper examines the cutting-edge advancements in aerodynamics, a critical field within fluid mechanics, with wide-ranging applications in aviation, automotive engineering, wind energy, and beyond. As aerodynamics evolves, it influences the design of aircraft, turbines, vehicles, and energy systems, necessitating specialized tools and methods for in-depth research and application. Recent advancements in experimental techniques, computational methods, material science, and flow control technologies are driving significant changes in aerodynamic design and performance. Figure 1 presents a detailed chart illustrating the recent advancements in aerodynamic tools, methodologies, technologies, and applications.

The main objective of this study is to investigate the impact of ground effects on the aerodynamic coefficients of a delta wing aircraft model. Since the flow on the delta wing exhibits vortical flow inherently, it is crucial to examine the influence of ground effects under these conditions. An experimental study was conducted to enhance understanding of the aerodynamic behavior of an aircraft model incorporating a delta wing-body-vertical tail. Experiments were conducted in a subsonic wind tunnel with a test section measuring 2.8 m × 2.2 m. Measurements were taken using a sting type balance to determine the aerodynamic forces and moments. All experimental tests were performed at a Reynolds number of 1.5 × 10 6 , with the specific aim of examining and identifying the influence of the ground on aerodynamic coefficients. To investigate how ground effect affects the aerodynamic performance of the model, a fixed plate with an adjustable height was placed underneath it. The distance between the model and the ground was varied, and resulting data indicated that increased proximity to the ground improved longitudinal static stability. The results revealed that the presence of the ground plane resulted in a 6% increase in the maximum lift coefficient. Meanwhile, the lift increases around 25% due to ground effects at an angle of attack of 14 °as it approaches the ground. The lift coefficient was enhanced across all angles of attack, while the induced drag coefficient decreased, resulting in an overall increase in aerodynamic efficiency. The lift curve slope saw a 16.9% increase when the model's height from the ground plane was less than half of the wing span. As the height decreased further, the aerodynamic center shifted backward, leading to an increase in longitudinal static stability. The rolling moment and yawing moment coefficients becomes unstable at angles of attack above 30 °.

Three planar, untwisted wings with the same elliptical chord distribution but with dierent curvatures of the quarter-chord line were tested in the Langley 8-Foot Transonic Pressure Tunnel (8-Ft TPT) and the Langley 7-by 10-Foot High-the tip of the crescent wing is swept outboard with a signicant separated ow region at the trailing edge of the tip. The ow at the tip of the elliptical wing with the straight trailing-edge and the ow at the tip of the crescent-shaped wing are probably inuenced by a vortex originating at the highly swept leading edges.

Three planar, untwisted wings with the same elliptical chord distribution but with dierent curvatures of the quarter-chord line were tested in the Langley 8-Foot Transonic Pressure Tunnel (8-Ft TPT) and the Langley 7-by 10-Foot High-the tip of the crescent wing is swept outboard with a signicant separated ow region at the trailing edge of the tip. The ow at the tip of the elliptical wing with the straight trailing-edge and the ow at the tip of the crescent-shaped wing are probably inuenced by a vortex originating at the highly swept leading edges.

The emerging sector of unmanned aircraft systems has been gaining interest in recent years. Researchers at the University of Salford’s Acoustics Research Centre are addressing several aspects of the topic, including aeroacoustics and fluid mechanics, noise control design, perceptual psychoacoustics, soundscape applications, and response to sound exposure for both humans and wildlife. This article provides an overview of developments from these efforts, along with a summary of recent conference activities addressing associated topics.

Maximizing flying qualities of a UAV is not a new topic in the aeronautical branch. Therefore, there is a significant amount of growing interest shown by researchers to integrate the flying mechanism of both conventional fixed wing UAV and rotorcraft UAV and thus, results in the birth of hybrid VTOL UAV. This paper investigates the difference in wing deflection of a hybrid VTOL UAV, a quadrotor fixed-wing with two independent propulsion systems and a conventional fixed wing. Quantitative method is chosen throughout this study where data collected are mainly from experiments and literature study. Firstly, the general wing specification is determined. To achieve this, a design analysis is conducted based on theoretical calculation and data from previous researches. The most suitable wing is found to be a straight wing with 0.3m chord length and 2m wingspan. Following that, a structural analysis is done to compare the difference in wing deflection for both mentioned UAV. After fabricating the model wing spar, an experimental set up for vibration test to determine wing deflection of a quadrotor fixedwing is being prepared and ran. At the same time, wing deflection of a fixed wing UAV is calculated by using beam deflection equation. The maximum deflection obtained is 0.0865385m and 0.0002516m respectively. The result shows that maximum deflection at wing tip for hybrid VTOL is higher than a conventional fixed wing. Factors that contributed to this finding were the concentrated upward lift force and also fluctuated force coming from vibration of the motor driven propeller.

es necesario disponer de instrumental que, con adecuados niveles de exactitud, permitan medir los valores cresta y eficaz aplicados sobre el objeto bajo ensayo. Los criterios básicos para estas mediciones se establecen en las normas IEC 60060. Con el avance tecnológico de los últimos años, las mediciones eléctricas se encuentran en un proceso de modernización, contemplando la implementación de instrumentos virtuales. Con ello, un sistema de medición consistiría de una placa adquisidora apropiada y de un software que cumpla los requisitos de medición necesarios. Debido a esto, están bajo estudio las normas IEC 61083-3 e IEC 61083-4 que tratan sobre el hardware y el software de medición respectivamente, para las mediciones de tensiones de frecuencia industrial en ensayos de alta tensión. El sistema de medición de alta tensión de frecuencia industrial de 300 kV del IITREE está compuesto por un divisor de tensión capacitivo y dos voltímetros analógicos, uno de tensión eficaz y otro de tensión cresta (dividido raíz de 2). El instrumento de valor eficaz es del tipo electroestático y el de valor cresta posee un detector de valor máximo de la onda, que se convierte a corriente y finalmente es medida por un galvanómetro. Ambos poseen una indicación por haz de luz deflactada por un espejo y la cupla antagónica se obtiene con un fleje metálico calibrado. Las calibraciones y mantenimiento de dicho instrumental resultan lentos y costosos. En el mercado convencional, fácilmente se disponen de instrumentos digitales de valor eficaz, no así de valor cresta de la onda. Por ello, se ha recurrido a la instrumentación virtual, mediante una placa adquisidora que registra la señal (tensión) y un software dedicado que realiza los cálculos correspondientes. En el presente trabajo se describe la implementación de un nuevo sistema de medición digital virtual, indicando los requerimientos de la placa de adquisición y el desarrollo del software que realiza el cálculo del valor eficaz y cresta a partir de la señal adquirida. Además de las funciones principales de medición, se han podido desarrollar otras funciones respecto a un voltímetro convencional, como la adquisición de la forma de onda, el perfil de tensión y otros parámetros de interés establecidos por la norma. Adicionalmente se complementó con la corrección por condiciones ambientales Palabras clave: Instrumentación virtual -Alta tensión -Ensayos -Calibración -Voltímetro El reemplazo de los instrumentos analógicos por digitales no es nada reciente, sin embargo, la utilización de estos equipos en las pruebas de alta tensión de frecuencia industrial o continua no fue discutido hasta la década de 2010. 19 a 23 de maio de 2019 Comitê de Estudos D1 -Materiales y técnicas de ensayo emergentes D1-CATALANO Foz do Iguaçu, Brasil

The static pressure, dynamic pressure and velocity magnitude are important parameters and have a strong influence on airfoil lift force. In this paper a slotted NACA 4412 airfoil profile is considered for analysis by using the commercial code ANSYS 14.5.7 WORKBENCH FLUENT® at an inlet boundary condition of different approaching wind velocities for various airfoil angles of attack in the range 0˚to 24˚. Renormalized group (RNG) k- turbulence model with enhanced wall function is used for the analysis. Variations of static pressure, dynamic pressure and velocity magnitude are plotted in form of contours and / or vectors.

This present paper describes the techniques and methodologies adopted by IDS in modelling complex GNSS scenarios such as airport sites, where local/ground augmentation system siting problems need an evaluation of the positioning signal degradation caused by multipath effects and interfering emissions. An overview is given of the main results achieved during a validation campaign, starting from basic laboratory tests, up to comparison with data measured in actual airport environments.

U ovom diplomskom radu je prikazana i objašnjena konstrukcija bespilotne letjelice autogira uz proračune performansi. Opisane su karakteristike autogira koje se razlikuju od aviona i helikoptera, osobito na malim brzinama. Također je opisan i prikazan način upravljanja autogirom, koji se razlikuje od načina upravljanja helikoptera i aviona. Detaljno je opisano i prikazano konstrukcijsko rješenje rotora koji je izrađen za bespilotnu letjelicu autogira, i mehanizma upravljanja, za što je napravljen CAD model letjelice. Također je prikazan i opisan način izrade i modifikacije dijelova rotora i priložena tehnička dokumentacija. Performanse bespilotne letjelice autogira izračunate su iz snage potrebne za let i raspoložive snage. Raspoloživa snaga je dobivena iz izmjerenog statičkog potiska i podataka za propeler od proizvođača. Napravljena je i alternativna metoda za slučaj da podataka propelera nema, koja se zasniva na teoriji diska, i pokazala se kao pouzdana za manje brzine leta, ali ...