Seaplanes and Flying Boats

This project highlights the different steps of a UAV design (fixed wing) to obtain a good model or prototype that will fly and fulfill its specific mission. Generally, it consists of estimating some initial values relying on some minor UAV historical data that will be checked and corrected by the end to optimize the results following an algorithm that every single aerospace engineer can use to realize an FWD with the most straightforward method. Our paper goes through all the steps one by one by providing some details and clarifying any challenge we will encounter in realizing the prototype. The challenge is not limited to the design and optimization part, but it will extend to the manufacturing part in which we are supposed to choose the materials and the manufacturing processes, this adds more intensity to the project because of the limitations that we will face at that level this paper we will use all the expertise that we gathered from a previous project of design that we have realized and the knowledge that we have enhanced in the past years of study at UIR in aerospace and fluid sections The paper is globally summing up conceptual design ,energy optimization, and stability assurance this by integrating analytical methods ,modelling using some advanced software (XFLR5, CATIAV5),and simulation techniques .During this investigation, we aim to add our prototype to the existing realized UAVS so that we enlarge the historical data that are available about UAVS and to facilitate any upcoming innovation in that domain by finding the best design in term of energy saving and performance.

The year 1910 in France proved to be a crucial on international scale for the aviation, as the French Henri Fabre successfully flew the first autonomous seaplane, namely the Fabre Hydration, as well as for Outer Space Law. Nowadays, rules on seaplanes have emerged, towards the future creation of seaplane law.  Besides, according to the theory on hydration of rights, hydration, in the sense of influence of water-based rights, such as the rights to water and to thermalism, not only has a positive impact on the sector to which it specifically addresses, but also indirectly on others, within the constellation of human rights. This theory is applicable in the matter of seaplanes as the right to water influences the right to transport and through it many others, including the right to development.

Resumen. El año 1910 en Francia resultó crucial a escala internacional para la aviación, ya que el francés Henri Fabre pilotó con éxito el primer hidroavión autónomo, el Fabre Hydration, así como para el Derecho del Espacio Exterior. En la actualidad, han surgido normas sobre hidroaviones, con vistas a la futura creación de un derecho de los hidroaviones.  Además, según la teoría de la hidratación de los derechos, la hidratación, en el sentido de influencia de los derechos basados en el agua, como los derechos al agua y al termalismo, no sólo tiene un impacto positivo en el sector al que se dirige específicamente, sino también indirectamente en otros, dentro de la constelación de los derechos humanos. Esta teoría es aplicable en el asunto de los hidroaviones, ya que el derecho al agua influye en el derecho al transporte y, a través de él, en muchos otros, incluido el derecho al desarrollo.

Keywords: Fabre hydration/Fabre hydravion; hydration of rights; seaplane law

Palabras clave: Fabre hydration/Fabre hydravion; hidratación de los derechos; derecho de hidroaviones

An original parameterization of the aerodynamic coupling between trimming and performance of a Flying Wing will be proposed. This will lead to an analytical model for trimming and performance coupling on flying wing, very useful at conceptual stage. An analytical evaluation of the performance of the trimmed Flying Wing at conceptual stage will then be presented. Assumptions and models 1 An innovative approach 1.1 Span loading : an inverse approach It is usual to compute the lift distribution along span from wing planform and twist distribution. The effect of aspect ratio λ, sweep φ and taper ratio ε on span loading have been studied to a certain extent [1]. However those studies do not cover a wide range of geometries. Furthermore, the performance is not easy to parameterize. An alternative approach will here be proposed, it is an inverse approach : The span loading will be considered as a conceptual input. The geometry that leads to this span loading will hence be obtained as an ou...

After the Great War, France expanded its influence across Central Europe. Aeronautics, a cutting-edge technology that reflected this nation’s modernity, was a key element of the French strategic scheme, both on the military and civilian levels. It justified the armed forces laying the groundwork in preparation for the development of commercial aviation. This article sheds new light on the history of international relations through a multifaceted study of the economic, political, and military dimensions of the French presence abroad. It examines local actors, military structures, and the French aviation network in order to illuminate the relationship between France and its partners.

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°.

Quelques cas sont connus dans les périodes de forte demande, comme la construction de frégates à Saint-Malo par le constructeur Chevillard en 1777-1778 (voir la communication de David Plouviez lors de la journée d'étude « Figures d'ingénieurs et mobilités en Europe, XV e-XVIII e siècles », Centre Alexandre Koyré (Paris), 3 décembre 2016), ou la mise en chantier à Honfleur de chaloupes et bateaux-canonniers pour la flottille de Boulogne sous l'Empire (

Causes and contributing factors of amphibious airplane accidents are examined by comparing the proportion of fatal accidents for different causes of accidents, with a focus on landings on water and low-level flying maneuvers. A set of 183 accidents involving amphibious planes from 2005 to 2020 was extracted from the National Transportation Safety Board’s online database. Amphibious airplane accidents are reported to be fatal in 34% of cases, which is higher than the average of 20% for general aviation. Logistic regression analysis shows that the maneuvering flight phase and decision-making factors are significantly more often associated with fatal accidents than other flight phases and causes. In addition, the number of accidents associated with decision-making factors significantly increased during the studied time period. Amphibious airplanes benefit from accident analysis despite the absence of denominator data and the limitations of most general aviation accident reports. Intent...

Causes and contributing factors of amphibious airplane accidents are examined by comparing the proportion of fatal accidents for different causes of accidents, with a focus on landings on water and low-level flying maneuvers. A set of 183 accidents involving amphibious planes from 2005 to 2020 was extracted from the National Transportation Safety Board’s online database. Amphibious airplane accidents are reported to be fatal in 34% of cases, which is higher than the average of 20% for general aviation. Logistic regression analysis shows that the maneuvering flight phase and decision-making factors are significantly more often associated with fatal accidents than other flight phases and causes. In addition, the number of accidents associated with decision-making factors significantly increased during the studied time period. Amphibious airplanes benefit from accident analysis despite the absence of denominator data and the limitations of most general aviation accident reports. Intentional low-level flying is shown to be a central area of concern that may be addressed at the operational as well as the training level. Landing accidents could be avoided by introducing additional warning systems and training regarding (retractable) landing gear as well as general awareness training of decision-making during landings on water.

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The relevance of the subject of research is determined by the need to develop and subsequently implement a mathematical model and the corresponding structural scheme of the convective heating surfaces of the TP-92 steam boiler. The purpose of this research work is to directly model the heat-transfer system of the convective heating surfaces of this boiler, designed for effective use in real conditions. The basis of the methodological approach in the research work is a combination of methods of the system analysis of the key principles of constructing mathematical models of heat-transfer systems of modern steam boilers with an experimental study of the prospects for creating a mathematical model of a heat-transfer system of the convective heating surfaces of a TP-92 steam boiler. In the course of the study, the results were obtained and presented in the form of a mathematical model of a convective heat-transfer system. It allows for making effective mathematical calculations of the main operating modes of the TP-92 steam boiler and calculating the dependences of the temperature and thermal modes of its operation on the change of incoming parameters of the used heat carriers, changes in the heating surface area and the relative flow rate of the heat carriers over the time of their use. The results obtained in the study, including the conclusions formulated on their basis, are of significant practical importance for the designers of steam boilers. The results also are useful for maintenance personnel, whose immediate responsibilities include determining the real possibilities of improving the convective heat-transfer system, based on the known parameters of the temperature of the coolant at the entrance to the system and at the exit from it.

If national governments and certain billionaires have their way, humans will reach Mars sometime in this century and set up permanent bases. Eventually they’ll need a way to get around. This paper describes the conceptual design and analysis of a manned10 Mars airplane configured for exploration, research, cargo transport, photography, and the linking of multiple settlements. Design development is being done by an international team of volunteers based on the configuration concept developed by lead author Dr. Daniel P. Raymer and incorporating rocket propulsion concepts suggested by James French. A two-man vehicle was developed based on overall requirements similar to the capabilities of the classic “Jeep” of WWII fame, namely a crew of two plus cargo to a total of 500 lbs, carried at least 260 nmi. It is assumed that the flight control system will be capable of fully autonomous operation when desired and that when carrying humans, they need not be trained pilots. VTOL operation is ...

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An original parameterization of the aerodynamic coupling between trimming and performance of a Flying Wing will be proposed. This will lead to an analytical model for trimming and performance coupling on flying wing, very useful at conceptual stage. An analytical evaluation of the performance of the trimmed Flying Wing at conceptual stage will then be presented. Assumptions and models 1 An innovative approach 1.1 Span loading : an inverse approach It is usual to compute the lift distribution along span from wing planform and twist distribution. The effect of aspect ratio λ, sweep φ and taper ratio ε on span loading have been studied to a certain extent [1]. However those studies do not cover a wide range of geometries. Furthermore, the performance is not easy to parameterize. An alternative approach will here be proposed, it is an inverse approach : The span loading will be considered as a conceptual input. The geometry that leads to this span loading will hence be obtained as an ou...

Weight components of airplane explained as follows: a) Crew weight ( c W ) The crew comprises the people necessary to operate the airplane in flight. e.g., Pilot, Co-pilot, Airhostess etc. b) Payload weight ( p W ) The payload is what the airplane is mentioned to transport passengers, baggage, freight etc. (Military use the payload includes bombs, rockets and other disposable ordnance) . c) Fuel weight ( f W ) This is the weight of the fuel in the fuel tanks. Since fuel is consumed during the course of flight. is a variable, decreasing with time during the flight. d) Empty weight ( e W ) This is weight of everything else-the structure engines (with all accessory equipment), electronic equipment landing gear, fixed equipment and anything else that is not crew, payload or fuel. e) Gross weight ( 0 W ) The sum of these weights is the total weight of the airplane. Gross weight or total weight varies through the flight because fuel is being consumed. The design take off gross weight is t...

Au début du XX e siècle, le Renseignement technique émerge à travers trois spécialités : les Transmissions, chargées d'intercepter et d'écouter les communications ; la Goniométrie, qui localise un poste émetteur intercepté par triangulation du signal ; et le Chiffre qui comprend à la fois la cryptographie, soit le fait de transformer un texte dit en clair en un message incompréhensible pour qui n'a pas la clef, et la cryptanalyse, dont le but est de percer les télégrammes adverses chiffrés interceptés, d'en trouver la clef et de les déchiffrer, pour prendre connaissance de leur contenu. Lorsque la Marine s'engage dans la guerre, son service de renseignement est sommaire : la 1 re Section de l'Etat-Major Général de la Marine (EMG) organise la collecte et l'analyse des renseignements maritimes, mais ses moyens en renseignement humain comme en renseignement technique sont insuffisants : les fonds, le matériel et les hommes manquent. Présenté ici, l'exemple du Chiffre de la Marine, évoluant d'un simple service de protection de la correspondance à un service de renseignement technique, par la collecte et le traitement de messages interceptés, illustre bien la transformation du Renseignement naval français au cours de la Grande Guerre.

During the conference, I insist on the fact that Gustave Whitehead‘s relationships certainly played a major role in his work. Whether by chance or of his own free will, Whitehead would have some decisive connections throughout his life, at least until 1901. He also found himself in places propitious to aeronautical innovation. In fact, the best possible places. First as an apprentice at Diesel, he is going to learn engine technology and metallurgy. As a sailor, he is going to observe the effect of the wind, and soaring birds (which don’t always need to flap their wings to fly.) A German immigrant to America at the end of the 19th century, he finds himself in Boston, where he meets some of the biggest names in aeronautics. He even has the chance to work with them by joining the BAS (Boston Aeronautical Society). He meets the Australian Hargrave whose kites are at the cutting edge of progress. While working on his kites at the BAS, he receives the first lessons of captive flight of the heavier-than-air devices. Chanute goes so far as to sponsor his first glider project. Octave Chanute, then one of the best engineers in the United States, will be amazed at Whitehead’s progress. He even meets Lilienthal with whom he can learn from his wings and gliding tests. Other big names such as Langley, Phillips and Maxim came to Boston at the same time to work with BAS. No wonder that Gustave Whitehead was able to realize so many flying inventions afterwards. He undoubtedly studied the work of d’Esterno and Mouillard, exchanging ideas with Octave Chanute, who willingly shared his immense knowledge. In short, at the end of the 19th century, Gustave Whitehead has all the ingredients and conditions to become a pioneer of aviation.

Durant la Première Guerre mondiale, les puissances en guerre engagèrent sur les différents fronts des avions ainsi que des hydravions. Suite à l’invasion de la Belgique par l’Allemagne et l’établissement d’une première base d’hydravions à Zeebrugge en 1914, puis une seconde à Ostende, la France réagit avec la mise en place de ses propres hydrobases côtières dans la Manche. Les escadrilles d’hydravions français étaient mobilisées dans la lutte anti-sous-marine, tandis que les escadrilles allemandes remplissaient des missions multitâches en appui aux navires et aux sous-marins. Les constructeurs d’hydravions explorèrent des démarches de conception différentes pour répondre aux besoins opérationnels, amenant des hydravions de diverses spécialisations à opérer dans les Flandres.

Während des Ersten Weltkriegs setzten die Krieg führenden Mächte Flugzeuge und Wasserflugzeuge an den verschiedenen Fronten ein. Nachdem Deutschland in Belgien einmarschiert war und 1914 eine erste Wasserflugzeug-Basis in Zeebrugge und eine zweite in Ostende errichtet hatte, reagierte Frankreich mit der Einrichtung eigener Küstenwasserflughäfen im Ärmelkanal. Die französischen Wasserflugzeugstaffeln wurden für die U-Boot-Bekämpfung genutzt, während die deutschen Staffeln Multitasking-Aufgaben zur Unterstützung von Schiffen und U-Booten erfüllten. Die Hersteller von Wasserflugzeugen erforschten unterschiedliche Konstruktionsansätze, um den operativen Anforderungen gerecht zu werden, was dazu führte, dass Wasserflugzeuge mit unterschiedlichen Spezialisierungen in Flandern eingesetzt wurden.

If national governments and certain billionaires have their way, humans will reach Mars sometime in this century and set up permanent bases. Eventually they’ll need a way to get around. This paper describes the conceptual design and analysis of a manned10 Mars airplane configured for exploration, research, cargo transport, photography, and the linking of multiple settlements. Design development is being done by an international team of volunteers based on the configuration concept developed by lead author Dr. Daniel P. Raymer and incorporating rocket propulsion concepts suggested by James French. A two-man vehicle was developed based on overall requirements similar to the capabilities of the classic “Jeep” of WWII fame, namely a crew of two plus cargo to a total of 500 lbs, carried at least 260 nmi. It is assumed that the flight control system will be capable of fully autonomous operation when desired and that when carrying humans, they need not be trained pilots. VTOL operation is ...

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Engagé dans l'Armée de l'Air en 1914 Télémaque REGNARD a poursuivi une carrière militaire jusqu'en 1942. Spécialisé dans la photographie aérienne il sera amené progressivement à réaliser des clichés "au sol" pour les autorités des territoires coloniaux dans lesquels il est amené à servir (Sénégal et AOF, Maroc, Indochine). Cet article présente sa carrière et un certain nombre de photos qu'il a réalisé ainsi que ses conditions de travail.

A preliminary hull design had been completed for the amphibious aircraft, The ClipperSpirit. This year, the team was tasked with characterizing and analyzing aerodynamic and hydrodynamic properties of the fuselage/hull. This seaplane project had problems not typically encountered in the aviation industry -the interaction of the aircraft with water and a fuselage shape that is not ideal for flight. An experimental setup was designed to investigate the interaction of the fuselage with a water surface for scaled speeds simulating takeoff and landing. Additionally, the flow near the step of the fuselage (a feature typical of seaplanes) was characterized. These tasks involved learning new software, design using SolidWorks, manufacturing scaled models, basic flow visualization, and the experimental process. Qualitative results were obtained and a first iteration of a testing platform to quantify the resistance of the planing fuselage on water was designed and construction. The results of the tests can be used to consider alternate configurations of the fuselage design. Of particular interest was the afterbody, the portion of the fuselage after the step that experiences increased drag.

In 1954, the founders of the Federation for Voluntary Gymnastics (VG) set the latter the goal of encouraging body maintenance for good health through physical exercise that was accessible to all. Although this rather original identity positioning that defined its institutional features and contributed to the construction of its social image appeared to be fairly clear on the surface, it has nonetheless continued to generate numerous questions, internal debates and realignments to this day. The Federation's history may therefore be examined through its permanent construction of identity, expressing both a desire to place specific methods of practice at centre stage and question the relationship with the body, which should be affirmed and specified vis-à-vis other federations. One issue resurging regularly in the discussions and debates of federation leaders was the question 'What is the VG spirit'? In other words, what united members of the Association, leaders, trainers and practitioners alike? How was the unity of this movement created and, more specifically, what made a 'VG session' unique? Three time periods can be identified, characterising three lines of positioning which may be linked to changing social, cultural and scientific contexts.

The aim of the resent work is to predict the aerodynamic performance of modified NACA 4415 airfoil using computational fluid dynamics modelling. The performance is compared to that of NACA 4415 Standard. The simulation is performed using FLUENT with the variables of freestream velocity (i.e. 3, 4, 5, and 18 m/s) and angle of attacks (i.e. -12°, -10°, -8°, -6°, 0°, 6°, 12°, 14°, 16°, 18°, and 20°). The results indicate that the modified NACA 4415 airfoil has better lift and momentum coefficient. The value of lift coefficient of modified NACA 4415 is relatively higher than NACA 4415, especially at -12° < α

Preface xiii xvi xvii Contents vii 4.8.3 Field performance studies 86 4.8.4 Wing geometry studies 87 4.8.5 Economic analysis 91 4.9 Initial 'type specification' 96 4.9.1 General aircraft description 96 4.9.2 Aircraft geometry 97 4.9.3 Mass (weight) and performance statements 97 4.9.4 Economic and operational issues 98 4.10 Study review 99 References 100

Bakalářská práce se zabývá návrhem malého bezpilotního letounu určeného pro soutěž Air Cargo Challenge 2015. Práce je uspořádána dle postupu vývojových prací. Na prvotní koncepční návrh navazuje volba vhodného tvaru letounu a jeho profiláže. Následuje výpočet letových výkonů, maximální vzletové hmotnosti a centráže letounu. Poslední část práce se zabývá konstrukcí letounu a je provedena analýza závislosti užitečného zatížení na hustotě vzduchu

Most wind tunnel models are fabricated of all metal components using computerized numerical control (CNC) milling machines. Fabrication of metal wind tunnel models is very expensive and time consuming. The models can require months to manufacture and are often made by small high technology companies that specialize in wind tunnel model manufacture. Using rapid prototype manufacturing techniques and materials in this way significantly reduces time and cost of production of wind tunnel models. This study was done by fused deposition modelling and their ability to make components for wind tunnel models in a timely and cost effective manner. This paper discusses the application of wind tunnel model configuration constructed using FDM and FDM with chromium coating for subsonic wind tunnel testing. A study was undertaken comparing a rapid prototyping model constructed of FDM technologies using polycarbonate to that of a standard machined steel model. Results from this study show relatively good agreement among the three models and rapid prototyping method with chromium coating does have an effect on the aerodynamic characteristics which produced satisfactory results.

Le 22 février 1924 à la Société de Géographie, René Fonck donne une conférence très médiatisée à l’invitation de la Société des Conférences. En sa qualité de Président de la Ligue aéronautique et de député des Vosges, l’« as des as » de la Première Guerre mondiale propose à un auditoire de choix d’imaginer ce que sera bientôt le voyage d’une Parisienne, reliant Paris à New York en moins de huit heures.
Établissant son exposé « d’après les données que la science possède à l’heure actuelle » (Fonck, 1924b: 83), le pilote délivre une présentation mêlée de romantisme et du futurisme propre à la modernité de son époque. Son expérience du vol et les progrès répétés de l’aviation depuis la guerre transforment son horizon des possibles.
Appuyée tant sur les raids de ses contemporains que sur un imaginaire médiatique en construction, cette conférence à prétention savante permet d’observer comment les réalités du vol ont prêté à la fiction positive, transformant effectivement le rapport à l’espace et au temps, dont les hommes aspirent à rapidement s’affranchir par le développement du moyen aérien. Aviateur autant qu’expert, Fonck y pense ce qui n’a encore jamais été réalisé, marquant la manière dont l’expérience tout autant que les représentations ont agi sur ces hommes.

The close formation flight of UAVs has many significant advantages over single vehicle flight. The aerodynamic stability analysis of two heterogeneous UAVs in close formation flight is detailed in the present paper. The issues of altitude changes and the associated shifts or changes in centre of gravity or moments, the equivalent actuator control surface deflections etc. are explained with the help of simulations. The short period frequency variations with these changes are also correlated with the help of pole-zero diagrams.

Cet article vise à présenter les inventions qui ont eu lieu avec les moyens de transport aérien et spatial à travers l'histoire. Les moyens de transport aérien sont ceux qui se déplacent dans les airs (ballons, dirigeables, avions, hélicoptères et drones) pour transporter des personnes et des marchandises. Les moyens de transport spatial sont ceux qui se déplacent dans l'espace extra-atmosphérique à l'aide de fusées et/ou d'engins spatiaux pour transporter des astronautes, des satellites artificiels, des sondes spatiales, des robots, des rovers ou tout autre type d'équipement d'exploration spatiale. En plus de présenter l'évolution du transport aérien et spatial à travers l'histoire, ses évolutions futures sont également présentées.

The aim of the resent work is to predict the aerodynamic performance of modified NACA 4415 airfoil using computational fluid dynamics modelling. The performance is compared to that of NACA 4415 Standard. The simulation is performed using FLUENT with the variables of freestream velocity (i.e. 3, 4, 5, and 18 m/s) and angle of attacks (i.e. -12°, -10°, -8°, -6°, 0°, 6°, 12°, 14°, 16°, 18°, and 20°). The results indicate that the modified NACA 4415 airfoil has better lift and momentum coefficient. The value of lift coefficient of modified NACA 4415 is relatively higher than NACA 4415, especially at -12° < α

Conventional aircraft are designed for a specific mission and/or set of performance requirements. These requirements often cause the performance for certain mission segments to be compromised because of fixed wing geometry. While some devices, such as flaps, have been used to augment the wing geometry, new materials are being developed that could allow significant wing morphing capability. This paper demonstrates the impact of a morphing wing on aircraft performance and provides a method to compare various morphing strategies. = lift off n = gravity load factor T = thrust V = velocity W = aircraft weight