Aircraft Design

Abstract:  The proliferation of unmanned aerial systems (UAS) has revolutionized modern warfare, necessitating advanced counter-drone technologies to address evolving threats. This paper explores the critical roles of sensor technologies (radar, electro-optical/infrared, acoustic, radio frequency) and jammer systems (RF, GPS, directed energy) in countering drones, emphasizing their synergistic integration for comprehensive defense. Sensors enable precise detection, tracking, situational awareness, and threat identification, while jammers disrupt drone communication, navigation, and payloads, offering non-kinetic neutralization. Artificial intelligence enhances real-time coordination, threat prioritization, and automated responses, as demonstrated in successful deployments like U.S. military base protections, Gatwick Airport security, and Ukraine’s conflict operations. The paper examines strategic implications, including enhanced defensive and offensive capabilities, alongside ethical and legal considerations such as minimizing civilian risks and ensuring compliance with international regulations. Future trends, including next-generation sensors (e.g., quantum radar) and autonomous counter-drone systems, promise greater scalability, though interoperability, collateral interference, and regulatory challenges persist. A comprehensive approach integrating innovation and regulation is essential to secure airspace and maintain tactical superiority in drone warfare.

In the present study, the effect of hinge position (H) has been numerically investigated to find the appropriate position for improving the aerodynamic performance of the NACA 0012 flapped airfoil. In addition, perpendicular and tangential suctions have been applied to control the flow separation and enhance the aerodynamic performance over the NACA 0012 flapped airfoil at each different hinge positions. The simulations were carried out at a Reynolds number of 5 × 10 5 (Ma = 0.021) based on two-dimensional incompressible unsteady Reynolds-averaged Navier-Stokes calculations to determine the adequate hinge position. The turbulence was modeled using the shear stress transport k-ω turbulence model. The effect of perpendicular suction (θ jet = -90°) and tangential suction (θ jet = -30°) was computationally studied over NACA 0012 flapped airfoil for five different hinge positions (H = 0.7c, 0.75c, 0.8c, 0.85c and 0.9c) and a flap deflection (δ f ) of 15°. Based on the results, the hinge position significantly affects the aerodynamic performance of the airfoil. The lift coefficient increased clearly as the hinge position moved to the trailing edge of the airfoil. Using perpendicular suction caused to increase the lift coefficient and decrease the drag coefficient. Consequently, the maximum value of the lift-to-drag ratio (C L /C D ) for perpendicular and tangential suctions was achieved about 35.8% and 25.1% higher than that of the case without suction at an angle of attack of 12° and H = 0.9c. Also, the effect of perpendicular suction was more considerable compared to the tangential suction. This caused a reduction in the size of the recirculation zone from 0.5 to 0.09 of the airfoil chord length and also transferred it from 1.13 to 1.18 of the airfoil chord length.

Stress analysis on a beam for hat cross-section with fixed ends was done. Only top and lower flanges were fixed without fixing the web, statically making the ends fixed. It was found that stress at edges was far superior to that at the middle for a uniformly distributed loaded beam. This paper presents a FEA study for reducing the stress at the beam ends by providing simple support along with fixed flanges. The simple support is provided at the lower flanges of hat cross-section beam. The support length was varied along the length of beam at both the ends. Optimized length of flange was found for minimized stress in the beam.

Foldable wing designs are becoming increasingly popular due to their advantages in the rapid deployment and compact packaging of fixed-wing UAVs, particularly when compared to horizontal take-off and VTOL counterparts. However, selecting an appropriate wing design requires the careful consideration of aerodynamic performance and volume storage constraints. As a result, a trade-off between performance and practicality must be addressed during the conceptual design phase. The primary objective of this study is to identify the optimal wing configuration for a tube-launched foldable wing design. To achieve this, the analysis combine an in-house design tool developed in Excel and XFLR5 v7.01 software.

Foldable wing designs are becoming increasingly popular due to their advantages in the rapid deployment and compact packaging of fixed-wing UAVs, particularly when compared to horizontal takeoff and VTOL counterparts. However, selecting an appropriate wing design requires the careful consideration of aerodynamic performance and volume storage constraints. As a result, a trade-off between performance and practicality must be addressed during the conceptual design phase. The primary objective of this study is to identify the optimal wing configuration for a tube-launched foldable wing design. To achieve this, the analysis combine an in-house design tool developed in Excel and XFLR5 v7.01 software.

A predominantly experimental investigation into the nature of transonic flow within an aerodynamic corner is treated. The work focuses on exploring the shock-induced separation that can occur due to the corner. Effects of dihedral angle, and sharp and filleted 90 o corners were studied on a RAE2822 profile wing. Tests were conducted in a shock tube operating as a short-duration transonic tunnel, using oil-film surface flow visualisation techniques. The experimental results are compared to numerical simulation studies. The CFD results correlate well with the experiments. It is shown that a fillet radius disperses the region of separated and reversed flow outwardly from the centre of the corner. Increasing the dihedral angle of the corner significantly delays and weakens the separated region.

It is well known that openFoam has become a very popular tool for research work in different fields and particularly, in fluid dynamics. But, it is also known its lack of detailed documentation supporting solvers made using the set of libraries provided by openFoam. Therefore, it becomes necessary to establish appropriate verifications that can be useful to users going for instance, through the selection of equations discretization schemes from fvSchemes libraries and of solution solvers from fvSolutions libraries, to be later applied in the simulation of a given specific problem. With this purpose, executable solvers available in openFoam 1.7 version to solve supersonic air flow problems are tested. Two different approaches have been taken in developing numerical methods to solve problems in transport phenomena at all Mach numbers and traditionally, they have been referred to as pressure-based and density-based methods. In this work, the advantages or disadvantages in applying any ...

Ultrawideband (UWB) antennas are of huge demand and Vivaldi antennas as well as the TEM horn antennas are good candidates for UWB applications as they both have relatively simple geometry and high gain over a wide bandwidth. The aim of this study is to design a compact antenna that achieves maximum gain over a bandwidth between 1.5 and 10.6 GHz while minimizing its size. The idea is to make use of combined respective advantages of Vivaldi and TEM horn antennas to achieve the desired goals by shaping the TEM horn antenna to look like a Vivaldi antenna. The antenna structure is modified by a dielectric load in the center to increase the gain bandwidth. It is placed in a surrounding box made of PEC material to reduce the undesired side lobes and to obtain more directive radiation pattern. The simulations are performed by using the CST STUDIO SUITE electromagnetic (EM) simulation software and they are later verified by the actual measurements. The Vivaldi shaped partially dielectric loa...

This article addresses safety in situations created by negative manifestations of human factors during aircraft flight. Such manifestations include erroneous actions by the pilot, delayed reaction to rapid changes in flight conditions, inattention, fatigue, illness, inaction, suicidal intent, hijacking of the aircraft by intruders, including terrorists, who are among the passengers, panic behavior of passengers, etc. Critical situations of this kind can be managed and a safe outcome can be achieved by blocking dangerous human behavior and transferring aircraft control to automatic mode – until the flight is completed with a safe landing. To implement this idea, the aircraft must be designed as a human-machine system with a high level of robotization. The purpose of this publication is to formulate the problem of developing an onboard automatic control system corresponding to this level and to provide a preliminary analysis of the possibilities of its solution.

: This study investigates the usage of Military Flight Operations Quality Assurance (MFOQA) data as a means to obtain precise, aircraft-specific fuel loads. Currently, USAF C-5M aircraft include a 4% degrade value in their fueling practices. MFOQA data are analyzed in an attempt to refine this value. Case study data are analyzed from a single C-5M. A model is constructed using smoothing techniques which compare MFOQA actual observations to a baseline flight test model. The resulting figures are applicable to fuel planning and fuel efficiency concepts. Validation is presented through comparison with computerized flight planning software output. Results from the case study analysis are presented within the framework of fleet-wide implementation and maintenance practices.

Questo lavoro dimostra che la Congettura di Collatz è vera su ogni numero intero positivo (qualunque sia il numero delle cifre che lo compongono) in quanto nella mia successione particolare e veloce, equivalente alla successione canonica di Collatz (si considerano solo numeri interi positivi dispari tranne il numero N di partenza che può essere pari ed i suoi successivi sono tutti dispari), in ogni iterazione la somma dei passaggi positivi (indicati con b) aumentano sempre di 1 o 2 unità rispetto alla somma dei  passaggi dispari (indicati con a) per cui si arriva ad una iterazione in cui i valori di b e di a sono tali che la seguente espressione (3^a)*N/(2^b) risulta positiva e minore1 per cui il numero finale della successione diventa (essendo sempre un intero positivo) è uguale ad 1.

El tren de aterrizaje es el mecanismo que hace la conexión entre la nave y el suelo (o el agua, según sea el caso). Este proyecto se centra en el diseño del tren de aterrizaje con material compuesto. El material compuesto a utilizar en este proyecto, es un acero AISI-4340 con un arreglo de inclusiones. Este se trabajó con la teoría de inclusiones de Eshelby [1], la cual explica la manera en que actúa un cuerpo compuesto de inclusiones, que es una matriz embebida en otra matriz. Se busca entonces, con este estudio, crear un material anisótropo, para elegir la dirección de las líneas de esfuerzo, en pro de ofrecer una mejor relación rigidez-peso en la dirección de la carga. Se utiliza la herramienta de Análisis de Elemento Finito para realizar el estudio. Se hace un análisis estático y un análisis modal para observar su comportamiento.

Este proyecto tiene el proposito de desarrollar el diseno de un avion a control remoto tipo competencia Aerodesign. Por lo tanto se establecieron varios objetivos como: el diseno del perfil alar, calcular el area de sustentacion, seleccionar el diseno de la estructura de alas y fuselaje, disenar el de tren de aterrizaje y disenar el sistema de dinamica y control. Basados en estos objetivos se realizo el diseno final del avion a control remoto. El proceso de diseno fue basado en la reglas que publica la Sociedad de Ingenieros Automotrices de Estados Unidos (SAE). Esta reglas establecen lo requerimientos minimos del diseno con el objetivo de cumplir la capacidad de el avion de despegue y aterrizaje, asi como poder levantar carga efectiva de 25 lbs. Por otra parte el diseno fue enfocado a obtener un avion capaz de cumplir los requerimientos de diseno de SAE Aerodesign y un bajo costo. En resumen el proyecto fue terminado en tiempo y objetivos planteados al inicio del proyecto se cumpli...

El tren de aterrizaje es el mecanismo que hace la conexion entre la nave y el suelo (o el agua, segun sea el caso). Este proyecto se centra en el diseno del tren de aterrizaje con material compuesto. El material compuesto a utilizar en este proyecto, es un acero AISI-4340 con un arreglo de inclusiones. Este se trabajo con la teoria de inclusiones de Eshelby [1], la cual explica la manera en que actua un cuerpo compuesto de inclusiones, que es una matriz embebida en otra matriz. Se busca entonces, con este estudio, crear un material anisotropo, para elegir la direccion de las lineas de esfuerzo, en pro de ofrecer una mejor relacion rigidez-peso en la direccion de la carga. Se utiliza la herramienta de Analisis de Elemento Finito para realizar el estudio. Se hace un analisis estatico y un analisis modal para observar su comportamiento. Se selecciono una cavidad con geometria elipsoide. Se diseno con una sola elipsoide, pues resulto ser mas eficiente que con otras configuraciones. La r...

Non posso che iniziare stringendo a me le due donne più importanti (la mamma, ovviamente, è fuori gara): la mia Piccola, bellissima, compagna degli ultimi quattro anni di vita; mia sorella, insostituibile. Proseguo ringraziando il Prof. Aldo Frediani, per l'umanità con cui ha agito e la professionalità con cui ha lavorato, e per avermi fatto tornare la voglia di provarci; i miei relatori e l'Ing. Mariotti, per la disponibilità e la competenza dimostrate; ragazze e ragazzi del Dipartimento, che hanno reso più lieve e addirittura piacevole l'ultimo tratto di un percorso per me impervio. Un abbraccio forte alla mia Famiglia. Alla famiglia fiorentina, a quella bresciana e a quella calabrese, per il loro sostegno. Un bacio, nonnina. Grazie a quelle cinque o sei persone che vale la pena chiamare Amici, per esserci state sempre. Grazie all'Amico di una vita, e alla sua dolce metà. Grazie a colleghi, sodali, coinquilini, ai compagni di anni o di una sera sola, protagonisti con me di frammenti di vita e di questo lungo viaggio giunto al capolinea. Grazie a tutti coloro che si sono un pò risentiti per essermi dimenticato di ringraziarli. Grazie alla mia squadretta sgangherata, per aver riempito certi pomeriggi di speranze (tante), delusioni (troppe), ed esultanze (magnifiche). Grazie a Dio... E' finita.

Aircraft design is a complex process that involves many different disciplines to obtain a holistic approach. In order to help the decision-maker in early design phase to improve, more cost-efficiently, the system safety and reliability base line of the design concept, a method (MOSART) that is able to handle trade-offs such as system safety, system reliability and other characteristics, for instance weight and cost, is used. MOSART -Multi-Objective Optimization for Safety and Reliability Trade-off -has been developed and implemented at SAAB Aeronautics. The aim of this paper is to demonstrate how the implemented method might work to aid the selection of optimal design alternatives. The method is a three-step method: step 1 is modelling of each considered target, step 2 is optimization, and step 3 is visualization and selection of results (results processing). The method is implemented by using, for each objective function, the existing available tools at the company and creating a user-friendly interface to guide the potential user. This paper uses the method to find the optimal choice of equipment vendors (the solutions balancing safety, reliability, weight and cost) of a fuel system concept (selection of design alternative). Due to the nature of the optimization problem, the optimization technique used is based on a Genetic Algorithm. The safety and reliability objectives were modelled using existing models within the Reliability Workbench program. In this paper, the analysis is performed within Architecture Design and Preliminary Design steps, according to the company's Product Development Process. The existent failure data and the associated cost and weight of every part included in the system are used to find the optimal design solutions. In order to investigate what can be gained and what can be learned from this demonstration, the problem is formulated in three different ways. Case a is to find the solutions balancing the safety, reliability, weight and cost of a fuel system concept and propose a selection of vendors for equipment. This case uses one main system safety and one system reliability objective as well as cost and weight objectives. Case b has been extended for three slightly different architectures of the system. The same objectives and weighting of objectives against each other are performed for all three architectures (slightly different concepts). Three configurations of the fuel system are compared and one of the architectures might be chosen. Case c has also the same scope as in case a, extended by using multiple safety or reliability objectives. The lessons learned regarding use of the implemented trade-off method in the three cases are presented. The results are a handful of solutions, a basis to aid the selection of a design alternative. While the implementation of the trade-off method is performed for a company, there is nothing to prevent adapting it to be used in other industrial applications with minimal modifications.

Direct lift control (DLC) has been integrated into the L-1011 All Weather Landing System design to enhance the performance and safety capabilities of this Category TTT aircraft. The merits of the improved aircraft behavior achieved with DLC not only provide a higher degree of performance capability for a large vehicle of this nature, but are also firmly reflected in many subtle areas relating to the design, safety margin, and reliability of a  complex, fail operational all weather landing system. The result in terms of influence on autoland system design,
problems and limitations that constrained the design, and resulting improvements in performance and safety characteristics are the subject of this paper'

This paper exposes a simplified preliminary conceptual integrated method to design an aircraft wing in subsonic speeds up to Mach 0.85. The proposed approach is integrated, as it allows an early estimation of main aircraft aerodynamic features, namely the maximum lift-to-drag ratio and the total parasitic drag. First, the influence of the Lift and Load scatterings on the overall performance characteristics of the wing are discussed. It is established that the optimization is achieved by designing a wing geometry that yields elliptical lift and load distributions. Second, the reference trapezoidal wing is considered the base line geometry used to outline the wing shape layout. As such, the main geometrical parameters and governing relations for a trapezoidal wing are reviewed in details. Third, the integrated design method is introduced through an evocative flowchart that describes the wing design process, whose objectives are essentially the determination and the optimization of the different wing parameters, essentially: Wing Area, Sweep Angle, Aspect Ratio, Taper Ratio, Thickness and Twist. Furthermore, refined and assessed formulas identified from an exhaustive literature study and historical trends yielding accurate and logical estimation of each parameter described in the optimization flowchart are provided. Finally, the capability of the proposed method is investigated through two design examples for jet and propeller aircrafts. The obtained layouts are tested and verified through simulations using the NASA OpenVSP simulation software.

Finite Element Analysis (FEA) has become a vital resource in the aerospace industry, allowing engineers to simulate and scrutinize intricate structural, thermal, and fluid dynamics issues with remarkable accuracy. This computational method helps predict stress distribution, deformation, vibration modes, and thermal characteristics in aerospace components like airframes, wings, engines, and landing gear under various operating conditions. By dividing complex structures into smaller, manageable finite elements, FEA offers astute judgments into performance, safety, and durability while minimizing the need for expensive physical prototypes and testing. In the aerospace field, FEA is essential for optimizing weight, enhancing fuel efficiency, ensuring compliance with strict safety regulations, and speeding up the design process.

Die Kriege des Britischen Empire umspannten die Welt und veränderten die historische Entwicklung zahlreicher Länder und Menschen. Für Ruhm und Ehre des Empire spielten in diesen Kriegen jedoch auch unzählige Tiere eine bedeutende Rolle, wie in der vorliegenden Studie anhand einiger Fallstudien eingehender betrachtet und evaluiert wird. Frank Jacob zeigt auf, wie wichtig der Einsatz von Tieren in den Kriegen des Britischen Weltreichs war und inwieweit der Ausgang dieser Kriege vom Zugang zu »tierischen Ressourcen« abhing. Im Zuge dessen stellt Jacob eine dem Anthropozentrismus entgegengesetzte Geschichte der Kriege des britischen Kolonialreichs vor.

Airworthiness certification is to ensure the safety of aircraft. With the surge in novel general aviation aircraft configurations and technologies, the Federal Aviation Administration replaced prescriptive design requirements with performance-based airworthiness standards in Federal Aviation Regulations Part 23 that governs the airworthiness of normal category airplane. The amendment ported over the accepted means of compliance (MoC) from prescriptive advisory circulars to a number of consensus standards from aviation community. Because these MoCs are scattered in multiple documents and cross-reference one another, the certification practice with this new format may be cumbersome and time-consuming.This paper proposes a Model-Based System Engineering (MBSE) approach that is envisioned to parametrically transform the document-centric exercise to a model-based process. The approach helps collect the FAR-23 regulations and the associated MoC in an integrated system model along with the relevant mappings between them. This allows users to automatically generate a compliance checklist for any specific certification requirement. Other benefits of the MBSE approach include circular referencing check, automatically propagating any future changes to the FARs or MoC standards through the model, and potential incorporation with early aircraft design.

The drive for more efficient flying vehicles in all categories may necessitate a significant departure from the tube-and-wing or rotary-wing norms that have been the mainstay of aviation for many decades. This poses challenges for predicting the aerodynamic characteristics and the weight build-up of such unconventional vehicles in early design phases. Additionally, the design and assessment of advanced/unconventional all-electric or hybridelectric propulsion system architectures require consideration of degrees-of-freedom and trade-offs that do not arise for conventional purely fuel-powered architectures. Thus, there is a need for a flexible vehicle sizing, trade-off, and optimization capability that is not limited to a single vehicle configuration (e.g., fixed-wing, rotary-wing) or propulsion system architecture. To be suitable for the early design phases, such a framework must evaluate relatively quickly, not require extensive definition of the vehicle, and lend itself to customizable design optimization setups. This paper describes the initial creation of such a capability and demonstrates its application to design trade-offs for a General Aviation vehicle with an advanced propulsion system architecture.

The drive for more efficient flying vehicles in all categories may necessitate a significant departure from the tube-and-wing or rotary-wing norms that have been the mainstay of aviation for many decades. This poses challenges for predicting the aerodynamic characteristics and the weight build-up of such unconventional vehicles in early design phases. Additionally, the design and assessment of advanced/unconventional all-electric or hybridelectric propulsion system architectures require consideration of degrees-of-freedom and trade-offs that do not arise for conventional purely fuel-powered architectures. Thus, there is a need for a flexible vehicle sizing, trade-off, and optimization capability that is not limited to a single vehicle configuration (e.g., fixed-wing, rotary-wing) or propulsion system architecture. To be suitable for the early design phases, such a framework must evaluate relatively quickly, not require extensive definition of the vehicle, and lend itself to customizable design optimization setups. This paper describes the initial creation of such a capability and demonstrates its application to design trade-offs for a General Aviation vehicle with an advanced propulsion system architecture.

The ongoing efforts to reduce aviation related greenhouse gas emissions and fuel burn have led to advancements in power generation and distribution (PG&D) subsystem technology. Due to the absence of historical data, PG&D subsystem models must be created from first-order analysis without compromising crucial information on their characteristics. This paper demonstrates the development of parametric, physics-based subsystem models such as battery, electric motor, power distribution and management system, and propeller speed reduction unit for rapid and low-cost sizing, simulation and analysis at early design stages. A special focus was put on rechargeable battery technology and implementing a dynamic (rather than steady-state) discharge behavior into the propulsion architecture. A methodology to integrate the developed subsystem models was presented. A sample application was also provided to demonstrate the combined capabilities of the models. To this end, the models were applied within a sample parallel hybrid electric architecture using Dornier 328 as a test bed. The subsystem behaviors under varying power requirements were then analyzed. Finally, the importance of having more dimensionality at the subsystem level at early design stages was highlighted by comparing the results of two different architectural choices.

The ongoing efforts to reduce aviation related greenhouse gas emissions and fuel burn have led to advancements in power generation and distribution (PG&D) subsystem technology. Due to the absence of historical data, PG&D subsystem models must be created from first-order analysis without compromising crucial information on their characteristics. This paper demonstrates the development of parametric, physics-based subsystem models such as battery, electric motor, power distribution and management system, and propeller speed reduction unit for rapid and low-cost sizing, simulation and analysis at early design stages. A special focus was put on rechargeable battery technology and implementing a dynamic (rather than steady-state) discharge behavior into the propulsion architecture. A methodology to integrate the developed subsystem models was presented. A sample application was also provided to demonstrate the combined capabilities of the models. To this end, the models were applied within a sample parallel hybrid electric architecture using Dornier 328 as a test bed. The subsystem behaviors under varying power requirements were then analyzed. Finally, the importance of having more dimensionality at the subsystem level at early design stages was highlighted by comparing the results of two different architectural choices.

This paper presents a methodology for the sizing and synthesis of power generation and distribution (PG&D) subsystems. The PG&D subsystem models developed in a previous work done by the authors were applied within a parallel hybrid electric propulsion architecture using the Dornier 328 as the baseline aircraft. The hybridization took place only during the cruise segment. Analyses were performed in Pacelab SysArc, a system architecture design tool, to assess the impact of different hybrid electric propulsion architectures and changing PG&D subsystem characteristics at aircraft and mission levels. To this end, sensitivity analysis was conducted to reveal the sensitivity to the subsystem level characteristics. Moreover, six different architectures were compared in terms of their mission level performance. These architectures included the PG&D subsystems with current state of the art technology, NASA 15-year technology goals and a more advanced battery technology. Although neither the current state of the art PG&D subsystems nor NASA 15-year technology goals were advanced enough to match the design range requirement of the baseline aircraft, some of the competing architectures met the practical range target while enjoying substantial amount of fuel reductions. Finally, it was observed that in order to reach a break-even point in terms of the design mission range, a battery specific energy of 5 kWh/kg was necessary for a 50% level of hybridization during cruise. In this work the Dornier 328 was used as a testbed, however the methodology can be generalized for all parallel hybrid electric propulsion applications.

In today's business climate, aerospace companies are more than ever in need of rational methods and techniques that provide insights as to the best strategies which may be pursued for increased profitability and risk mitigation. However, the use of subjective, anecdotal decision-making remains prevalent due to the absence of analytical methods capable of capturing and forecasting future needs. Negotiations between airframe and engine manufacturers could benefit greatly from a structured environment that facilitates efficient, rational, decision-making. Creation of such an environment can be developed through a parametric physics-based, stochastic formulation that uses Response Surface Equations as meta-models to expedite the process. This paper describes the implementation of such an approach in order to demonstrate the types of insights that might be gained as an engine manufacturer tries to forecast the effects of the associated airframe uncertainties (structural, aerodynamic, etc. design changes) on engine related characteristics for the design of a hypothetical regional business jet.

The propagation of disturbances through connected beams is considered using finite element theory: the Timoshenko beam model is considered since it exhibits the correct propagation behaviour in single beams. The joint is examined and three joint models are introduced into the model, namely the rigid block model, the filament model and finally a flexible joint model. The numerical results so obtained compare favourably with experimental results produced at UMIST.

In the era of market and work-force globalization engineers need a solid understanding of the impact their products have locally as well as globally. This is why the US Accreditation Board for Engineering and Technology recently put a new spin on this requirement in engineering education. Specifically, outcome 3h of Engineering Criteria 2000 states that engineering graduates must have "the broad education to understand the impact of engineering solutions in a global / societal context". This outcome may be one of the most difficult to achieve since it requires not only a strong technical understanding but also an informed societal and historical perspective that is particularly difficult to achieve. This paper identifies some of the skills students need to be able to evaluate the impact of their solutions in a global / societal context as well as methods used by some universities to address this issue outside of technical engineering courses. The main focus of this paper is the introduction of course design elements that help students master these skills that can be incorporated into required and elective engineering courses. Examples are presented from a variety of thermal/fluid courses where these skills are taught in the Mechanical and Aerospace Engineering Department at San Jose State University.

Three-dimensional, compressible turbulent boundary-layer calculations have been performed for the finite supercritical wing of the NASA modified F8 transonic research airplane. Data on the boundary-layer thickness, displacement thickness, skin friction components, and integrated streamwise skin friction are presented for points along the streamwise stations of which the pressure measurements were previously made. Representative velocity profiles are shown, and boundary-layer-thickness contour plots and skin-friction vector plots are presented. Results are given for a Reynolds number of 1.5 million per foot, and for Mach numbers of 0.50 and 0.99.

Optimization of a High-speed Vac-train with an Axial Flow Air Compressor, an Aerodynamic Bearing Levitation and a Linear Synchronous Electromagnetic Motor" and the work presented in it are our own. We confirm that:  This work was done wholly or mainly while in candidature for a bachelor degree at this University.  Where any part of this thesis has previously been submitted for a degree or any other qualification at this University or any other institution, this has been clearly stated.  Where we have consulted the published work of others, this is always clearly attributed.  Where we have quoted from the work of others, the source is always given. With the exception of such quotations, this thesis is entirely our own work.  We have acknowledged all main sources of help.  Where the thesis is based on work done by ourselves jointly with others, we have made clear exactly what was done by others and what we have contributed ourselves.

This white paper introduces an AI-Integrated Head-Up Display (HUD) System designed to enhance situational awareness for military and law enforcement personnel. The system features a high-resolution graphene quantum dot-organic light-emitting diode (QD-OLED) display, advanced AI-driven object detection using the YOLOv5 algorithm, and secure communication protocols incorporating post-quantum cryptography and blockchain authentication. Integrated sensors-including forward-looking infrared (FLIR), unmanned aerial vehicle (UAV) feeds, LiDAR, and GPS-provide real-time data fusion, while interoperability with existing systems like the U.S. Army's Integrated Visual Augmentation System (IVAS) ensures seamless adoption. The HUD system offers a field of view (FOV) of 70 degrees horizontal by 40 degrees vertical, a resolution of 1920x1080 pixels, and a refresh rate of 120 Hz, delivering clear, real-time visuals in challenging environments. This innovation contributes to academic literature by advancing research in AI, optics, cybersecurity, and wearable technology, with applications in military operations, law enforcement, and potentially civilian augmented reality (AR) systems. The global military AR market, projected to grow from $1.2 billion in 2023 to $2.3 billion by 2028, underscores the system's market relevance.

L'attuale filosofia di progetto per le strutture aeronautiche inizia a divenire troppo conservativa, soprattutto dopo l'introduzione di materiali più efficienti e avanzati strumenti di analisi. Per questo motivo il Progetto Europeo DAEDALOS si prefigge lo scopo di sviluppare nuovi competitivi metodi di progetto per la riduzione di peso strutturale, che potrebbe portare anche alla riduzione di emissioni degli aeroplani civili. L'obiettivo di questo lavoro di tesi, situata all'interno di questo progetto, è di determinare una base comparativa per quanto concerne i carichi dimensionanti dovuti alla turbolenza atmosferica (per il solo modello Discrete Gust Criterion), seguendo le tecniche di progetto correnti, al fine di valutare nuove metodologie. L'attività è focalizzata sulla generazione di modelli numerici strutturali e la definizione delle condizioni di carico dovute alla raffica atmosferica. I modelli ad elementi finiti degli impennaggi di un aereo civile (business jet) vengono definiti e utilizzati nel processo di riduzione; a questo scopo viene proposta una metodologia per ottenere le caratteristiche di rigidezza e massa equivalenti di un modello a trave e verificata con dei semplici modelli di trave. Successivamente il metodo di riduzione viene applicato agli impennaggi, generandone così i modelli a travi. Accanto alla filosofia di progetto attuale viene illustrata una soluzione alternativa, definita Upgraded Design Philosphy; non si tratta di un nuovo metodo, ma può essere la base per futuri sviluppi. Essa consiste nel condurre le analisi dinamiche direttamente su modelli strutturali ad elementi finiti di dettaglio o ibridi. Infine, le due procedure di progetto presentate sono applicate ai modelli del velivolo e confrontate in termini di risposta dinamica e livello di sforzo su componenti strutturali. I risultati hanno mostrato la validità della filosofia di progetto alternativa. Parole chiave: carichi di raffica, raffica discreta, processo di riduzione, filosofia di progetto, modello a travi, carichi dinamici

Choosing the best casting technology is made considering the quality indices (I.C.) of the casted part, in the status of FINICHED PART. Each phase of the technological process has several possibilities with advantages and disadvantages of techno-technological nature, efficiency, production or the domain in which the part is used. The projection of the casting technology is realized taking into consideration several imposed parameters – which much be applied and included in the technology which is used and various operations, phases, materials, SDV and technologic equipments, which support optimization processes in order to assure total quality to the casted part. The current paper intends to present the methodology for choosing the optimum casting technology for a turbo compressor rotor used in the aviation, part which must be assimilated in the national industry.

: Tactical Deception (TD) has always been a critical part of warfare, and it can still be a decisive factor today, especially through the use of physical deception that relies on Unmanned Aerial Vehicles (UAVs). This paper examines how the military can more effectively employ Unmanned Aerial Vehicles (or drones) in a TD role by using physical deception to execute both aviation and ground combat missions more adequately. This thesis will use the problem/solution framework to examine the issues of aircraft vulnerability in the low altitude flight regime and downed aircrew capture, both areas which have not benefited significantly from advancements in military technology and tactics. Physical deception UAVs, which deceive the eyes and ears of the adversary rather than electronic systems, are analyzed as alternatives for these two operational areas. The analysis determines physical deception UAVs can be beneficial in decreasing risk to air and ground combatants during mission execution ...

Die lokale Erinnerungskultur an die NS-Besatzung in Schifflingen wird bis heute vom Widerstand geprägt. Insbesondere die Streiks von 1942 und die Widerstandsbewegung Alweraje dominieren den lokalen Erinnerungsdiskurs. Allerdings sind die Aktivitäten anderer Gruppen kaum bekannt. Am Beispiel des Schifflingers Jacques Goergen beleuchtet der folgende Beitrag die Geschichte der belgischen Brigade Piron mit ihren ca. 139* luxemburgischen Soldaten.

Die lokale Erinnerungskultur an die NS-Besatzung in Schifflingen wird bis heute vom Widerstand geprägt. Insbesondere die Streiks von 1942 und die Widerstandsbewegung Alweraje dominieren den lokalen Erinnerungsdiskurs. Allerdings sind die Aktivitäten anderer Gruppen kaum bekannt. Am Beispiel des Schifflingers Jacques Goergen beleuchtet der folgende Beitrag die Geschichte der belgischen Brigade Piron mit ihren ca. 139 luxemburgischen Soldaten.

This paper contain the content of basic review of an aircraft fuel system .This paper cover the various fuel system and fuel subsystem used in aircraft .Purpose of an aircraft fuel Sub system to monitors the fuel supply, its control, storage, drainage and also maintain stability of aircraft.. Basically the purpose of fuel system is to supply the fuel in all phase of including landing ,takeoff, Banking and sharp maneuvering fuel system should also supply the sufficient amount of neat and clean fuel at required pressure. Types of fuel system may vary in aircraft but all the aircraft keeps their own fuel system. The fuel system must be used keeping the centre of gravity to be stable in mind.

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.

This report is intended to provide a broad knowledge of various topics associated with NASA's Aeronautics Research Mission Directorate (ARMD), with particular interest on the NASA SBIR contracts awarded from 2011-2012 executed by small companies. The content of this report focuses on the high-quality, cutting-edge research that will lead to revolutionary concepts, technologies, and capabilities that enable radical change to both the airspace system and the aircraft that fly within it, facilitating a safer, more environmentally friendly, and more efficient air transportation system.