Готові списки джерел за темами / Payload sizing

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Добірка наукової літератури з теми "Payload sizing"

Автор: Grafiati

Опубліковано: 24 червня 2022

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Статті в журналах з теми "Payload sizing"

Haley, J. G., T. P. McCall, I. W. Maynard, and B. Chudoba. "A sizing-based approach to evaluate hypersonic demonstrators: demonstrator-carrier constraints." Aeronautical Journal 124, no. 1279 (April 17, 2020): 1318–49. http://dx.doi.org/10.1017/aer.2020.30.

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ABSTRACTThe objective of this study is to identify, evaluate, and provide recommendations towards the realisation of near-term hypersonic flight hardware through the consideration of carrier vehicle constraints. The current rush of available funds for hypersonic research cannot cause a program to ignore growth potential for future missions. The prior NB-52 carrier vehicles, famous for the X-15 and X-43A missions, are retired. Next generation hypersonic demonstrator requirements will necessitate a substitution of carrier vehicle capability. Flight vehicle configuration, technology requirements, and recommendations are arrived at by constructing and evaluating a hypersonic technology demonstrator design matrix. This multi-disciplinary parametric sizing investigation of hypersonic vehicle demonstrators focuses on the evaluation of the combined carrier platform, booster, and hypersonic cruiser solution space topography. Promising baseline configurations are evaluated against operational requirements by trading fuel type, endurance cruise time, and payload weight. The multi-disciplinary study results are constrained with carrier payload mass and geometry limitations. The multi-disciplinary results provide physical insights into near-term hypersonic demonstrator payload and cruise time requirements that will stretch the capability of existing carrier aircraft. Any growth in hypersonic research aircraft size or capability will require new carrier vehicle investments.

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Avanzini, Giulio, Emanuele L. de Angelis, Fabrizio Giulietti, and Edmondo Minisci. "Optimal Sizing of Electric Multirotor Configurations." MATEC Web of Conferences 233 (2018): 00028. http://dx.doi.org/10.1051/matecconf/201823300028.

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A sizing tool for the definition of the configuration of electrically powered multirotor platforms is developed, which accounts for a realistic battery discharge model. The tool is developed to provide the community with the possibility of deriving the best configuration for performing a given task, while accounting for specific constraints and performance requirements. An evolutionary algorithm is used for searching the design space and to identify feasible designs with optimal performance in terms of maximum hovering time on the target and payload weight fraction.

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ONEL, Alexandru-Iulian, and Teodor-Viorel CHELARU. "Weights and sizing assessment in the context of small launcher design." INCAS BULLETIN 12, no. 3 (September 1, 2020): 137–50. http://dx.doi.org/10.13111/2066-8201.2020.12.3.11.

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The paper presents mathematical models that can be used to quickly define preliminary key aspects regarding the sizing and weight characteristics of studied small launchers. The tool developed based on the proposed mathematical models can be used for standalone liquid propelled stage design or it can be integrated in an iterative multidisciplinary optimisation design scheme (MDO) for a preliminary small launcher design, able to insert the desired payload into a predefined orbit.

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Kumar, A., S. C. Sati, and A. K. Ghosh. "Design, Testing, and Realisation of a Medium Size Aerostat Envelope." Defence Science Journal 66, no. 2 (March 23, 2016): 93. http://dx.doi.org/10.14429/dsj.66.9291.

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<p>The design, testing and realisation aspects during the development of a medium size aerostat envelope in the present work. The payload capacity of this aerostat is 300 kg at 1 km above mean sea level. The aerostat envelope is the aerodynamically shaped fabric enclosure part of the aerostat which generally uses helium for lifting useful payloads to a specified height. The envelope volume estimation technique is discussed which provides the basis for sizing. The design, material selection, testing and realisation aspects of this aerostat envelope are also discussed. The empirical formulas and finite element analysis are used to estimate the aerodynamic, structural and other design related parameters of the aerostat. Equilibrium studies are then explained for balancing forces and moments in static conditions. The tether profile estimation technique is discussed to estimate blow by distance and tether length. A comparison of estimated and measured performance parameters during trials has also been discussed.</p>

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Chávez, Javier Enrique Orna, Otto Fernando Balseca Sampedro, Jorge Isaías Caicedo Reyes, Diego Fernando Mayorga Pérez, Edwin Fernando Viteri Núñez, and Catalina Margarita Verdugo Bernal. "Análisis Y Diseño De Una Aeronave No Tripulada Para Uso Agrícola." European Scientific Journal, ESJ 13, no. 6 (February 28, 2017): 135. http://dx.doi.org/10.19044/esj.2017.v13n6p135.

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The present research proposes to diversify the use of unmanned aerial vehicles (UAV) with rotating wings for applications in the agricultural sector. For this we have analyzed and designed an unmanned aircraft. In first instance the applications of this type of aircraft in this sector were reviewed to determine possible design conditions that would aid in the sizing and design of the aircraft. Once the requirements had been determined, aerodynamic analysis was carried out to size up and launch the required power output for the craft. This in order to optimize the weight and autonomous fight time to finally design an aircraft prototype built in carbon fiber with the aid of fault theories as applied to composite materials. At the end of the research, an unmanned aircraft of 6 rotors, each with an installed power supply of 700W was designed. The aircraft has an autonomous flight time of 40 minutes without a payload, 20 minutes with a payload of 3Kg, and 8 minutes with a payload of 5Kg. The commercial application of these aircraft are the monitoring of land and fumigation in inaccessible areas.

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Patil, Ankur S., and Emily J. Arnold. "Sensor-Driven Preliminary Wing Ground Plane Sizing Approach and Applications." International Journal of Aerospace Engineering 2018 (July 2, 2018): 1–15. http://dx.doi.org/10.1155/2018/6378635.

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Structurally integrated antenna arrays provide synergies allowing the integration of large apertures onto airborne platforms. However, the surrounding airframe can greatly impact the performance of the antenna array. This paper presents a sensor-driven preliminary wing ground plane sizing approach to provide insight into the implications of design decisions on payload performance. The improvement of a wing-integrated antenna array that utilizes the wing as a ground plane motivated this study. Relationships for wing span, wing chord, and thickness are derived from extensive parametric electromagnetic simulations based on optimum antenna performance. It is expected that these equations would be used after an initial wing-loading design point has been selected to provide the designer guidance into how various wing parameters might affect the integrated antenna performance.

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Behroo, Mahan, Afshin Banazadeh, and Andisheh Rahimi Golkhandan. "Design Methodology and Preliminary Sizing of an Unmanned Mars Exploration Plane (UMEP)." Applied Mechanics and Materials 332 (July 2013): 15–20. http://dx.doi.org/10.4028/www.scientific.net/amm.332.15.

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This paper discusses the mission requirements and design constraints for an Unmanned Martian research aircraft based on a tailor-made classical airplane design methodology. First, the exploration mission is described using the information from previous real-world experiences and the desired payload is proposed accordingly. The environmental conditions that dictate severe constraints to the design space are characterized afterwards. The conventional airplane design cycle is modified to address the lack of statistical data and to define a proper design recycling criteria. Eventually, the outcome is presented in the form of a novel configuration that is well suited to carry out the specified exploration mission, flying low and slow over the Martian surface.

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da Silva, José Roberto Cândido, and Gefeson Mendes Pacheco. "An Extended Methodology for Sizing Solar Unmanned Aerial Vehicles: Theory and Development of a Python Framework for Design Assist." Sensors 21, no. 22 (November 12, 2021): 7541. http://dx.doi.org/10.3390/s21227541.

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There is a growing interest in using unmanned aerial vehicles (UAVs) in the most diverse application areas from agriculture to remote sensing, that determine the need to project and define mission profiles of the UAVs. In addition, solar photovoltaic energy increases the flight autonomy of this type of aircraft, forming the term Solar UAV. This study proposes an extended methodology for sizing Solar UAVs that take off from a runway. This methodology considers mission parameters such as operating location, altitude, flight speed, flight endurance, and payload to sizing the aircraft parameters, such as wingspan, area of embedded solar cells panels, runway length required for takeoff and landing, battery weight, and the total weight of the aircraft. Using the Python language, we developed a framework to apply the proposed methodology and assist in designing a Solar UAV. With this framework, it was possible to perform a sensitivity analysis of design parameters and constraints. Finally, we performed a simulation of a mission, checking the output parameters.

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Sridharan, Ananth, Bharath Govindarajan, and Inderjit Chopra. "A Scalability Study of the Multirotor Biplane Tailsitter Using Conceptual Sizing." Journal of the American Helicopter Society 65, no. 1 (January 1, 2020): 1–18. http://dx.doi.org/10.4050/jahs.65.012009.

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This paper presents a methodology for preliminary sizing of unconventional rotorcraft using a physics-based approach to estimate the weight of primary load-carrying members and rotor efficiencies. The methodology is demonstrated for a quadrotor biplane tailsitter, a tilt-body configuration that can operate in both helicopter and airplane mode. A beam lattice framework for the airframe structure is iteratively adjusted in the sizing loop to accommodate the limit loads. A similar semianalytical approach is followed to size and estimate weight of the rotor blades. Using this analysis, a consistent combination of vehicle macrodimensions (rotor radius, wing span) and tip speed as well as detailed design parameters (spar height, skin thickness, and cross-section weight) are obtained simultaneously. To compare the effectiveness of various power plants within a weight class, the sizing methodology was modified to identify the payload for three different vehicle takeoff weights: 20, 50, and 1000 lb. To enable operation within constrained urban canyons, the effect of restricting maximum vehicle dimensions to 10 ftfor the 1000-lb designs is also examined. An electric transmission model is used in these designs owing to its relative insensitivity of transmission efficiency to the operating RPM. A variable-pitch and variable-RPM rotor design allows for control redundancy within each rotor.

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Rajendran, Parvathy, and Howard Smith. "Development of Design Methodology for a Small Solar-Powered Unmanned Aerial Vehicle." International Journal of Aerospace Engineering 2018 (2018): 1–10. http://dx.doi.org/10.1155/2018/2820717.

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Existing mathematical design models for small solar-powered electric unmanned aerial vehicles (UAVs) only focus on mass, performance, and aerodynamic analyses. Presently, UAV designs have low endurance. The current study aims to improve the shortcomings of existing UAV design models. Three new design aspects (i.e., electric propulsion, sensitivity, and trend analysis), three improved design properties (i.e., mass, aerodynamics, and mission profile), and a design feature (i.e., solar irradiance) are incorporated to enhance the existing small solar UAV design model. A design validation experiment established that the use of the proposed mathematical design model may at least improve power consumption-to-take-off mass ratio by 25% than that of previously designed UAVs. UAVs powered by solar (solar and battery) and nonsolar (battery-only) energy were also compared, showing that nonsolar UAVs can generally carry more payloads at a particular time and place than solar UAVs with sufficient endurance requirement. The investigation also identified that the payload results in the highest effect on the maximum take-off weight, followed by the battery, structure, and propulsion weight with the three new design aspects (i.e., electric propulsion, sensitivity, and trend analysis) for sizing consideration to optimize UAV designs.

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Більше джерел

Дисертації з теми "Payload sizing"

Camino, Jean-Thomas. "Co-optimisation charge utile satellite et système télécom." Thesis, Toulouse 3, 2017. http://www.theses.fr/2017TOU30401.

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L'augmentation continue des besoins en télécommunications dans notre société se traduit par une suite de défis technologiques pour les systèmes fournissant ce type de services, qu'il s'agisse de télédiffusion, de téléphonie, ou bien d'échange de données. Les satellites de télécommunications sont ainsi particulièrement concernés par ce besoin d'innover, à la fois sur les technologies mises en orbite, mais aussi et surtout au niveau de l'exploitation de ces ressources embarquées. Sur ce dernier point, pour une mission de télécommunications définie précisément en termes de zone à servir, de type, de quantité et de qualité de service à fournir, il faut effectivement être capable de dimensionner de la manière la plus adéquate possible la charge utile du satellite de télécommunications, sous les différentes contraintes auxquelles elle est soumise : masse, volume, coût, et consommation énergétique des équipements embarqués. Cette thèse développe ainsi une approche algorithmique pour un tel dimensionnement dans le cas particulier des systèmes de télécommunications dits "multifaisceaux". Une procédure d'optimisation globale de ces systèmes satellitaires est ainsi proposée. Elle repose sur une décomposition en un ensemble de problèmes mathématiques interconnectés dont les complexités respectives, réduites par rapport au problème global, permettent d'espérer des solutions algorithmiques efficaces. Ce travail a permis d'exhiber deux problèmes phares dans ce dimensionnement de la charge utile satellite, adressés par l'angle de la recherche opérationnelle : l'optimisation du placement de faisceaux, et l'optimisation de plans de fréquences. Ce premier problème de placement de faisceaux sous contraintes de charge utile a été l'occasion de proposer des méthodologies inédites de gestion des contraintes en norme euclidienne sur des variables continues pour les problèmes mixtes non-linéaires non-convexes. Ces techniques ont alors été appliquées avec succès au sein de solutions à ce premier problème qui s'appuient pleinement sur la programmation linéaire mixte. Dans un deuxième temps, une exploitation novatrice de certaines propriétés du clustering en k-moyennes est proposée et permet de simplifier ces modèles mathématiques et ainsi accélérer l'optimisation du placement des faisceaux. Ces algorithmes de programmation mathématique sont ensuite confrontés à une heuristique gloutonne randomisée également développée dans le cadre de ces travaux. Le deuxième problème central de dimensionnement identifié au cours de ces travaux de thèse est la définition de plans de fréquences. Il s'agit d'une allocation de ressource disponible à bord du satellite aux différents faisceaux de ce dernier, tels qu'ils ont été définis dans le problème précédent de placement de faisceaux. Avec un objectif de minimisation du nombre d'un certain type d'équipement à embarquer dans la charge utile satellite, on cherche à satisfaire la mission de télécommunications qui s'exprime en une demande de chaque utilisateur au sol. Ce problème complexe a lui-même donné lieu à une décomposition en deux sous-problèmes d'allocation de fréquences, puis d'allocation d'équipements de la charge utile, qui sont traités par programmation par contraintes et programmation linéaire en nombres entiers, en exploitant des résultats théoriques qui servent à la fois à la modélisation des problèmes, mais aussi à leur résolution
The continuous growth in telecommunication needs in our society translates into a series of technical challenges for the systems that provide such services, whether it is television broadcasting, telephone, or data exchange. The telecommunication satellites are particularly concerned by this need for innovation, both on the embarked technologies but also on the way the resulting resources are exploited for the end users. On the latter point, for a telecommunication mission defined precisely in terms of service zone, type, quantity and quality of service, one has to be able to size as adequately as possible the telecommunication satellite payload, under the several constraints it is subject to: mass, volume, cost, and power consumption of the embarked hardware. This thesis develops an algorithmic approach for a such a sizing in the particular case of the telecommunication systems that are said to be "multi-beam". A global optimization process of these satellite system is proposed. It relies on a decomposition into a set of mathematical problems whose respective complexities, reduced with respect to the original problem, allow to reasonably aim for efficient algorithmic solutions. This work allowed to identify two key problems in this satellite payload sizing, addressed through an operations research angle: the beam layout optimization and the frequency plan optimization. This first beam layout problem under payload constraints has been an occasion to propose novel ways to handle Euclidean norm constraints on continuous variables for non-convex non-linear mixed programs. These techniques have been then successfully applied in for the generation of solutions to this first problem that fully exploits the mixed integer linear programming formalism. Then, a novel exploitation of some of the properties of the k-means clustering has been proposed as it allows to simplify these mathematical models and therefore accelerate the beam layout optimization. These mathematical programming algorithms have been then compared to a greedy heuristic developed during this thesis work. The second central sizing problem that has been identified is the frequency plan definition. It consists in a resource allocation of on-board satellite resources to the several beams that have been defined in the preceding beam layout optimization problem. With an objective of minimizing the number of a certain type of hardware to be embarked on the payload, the satisfaction of the telecommunication mission defined by an individual demand of all the end users on the ground is aimed. This complex problem itself lead to a decomposition into two sub-problems of frequency and on-board payload hardware allocation, that are treated with constraints programming and integer linear programming, exploiting theoretical results that are useful both at the problem modeling and problem solving levels

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Книги з теми "Payload sizing"

Roche, Joseph M. Structural sizing of a 25,000-lb payload, air-breathing launch vehicle for single-state-to-orbit. [Cleveland, Ohio]: National Aeronautics and Space Administration, Glenn Research Center, 2001.

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Частини книг з теми "Payload sizing"

Alexander, David, and Neil Murphy. "Payload Design and Sizing." In The International Handbook of Space Technology, 117–42. Berlin, Heidelberg: Springer Berlin Heidelberg, 2014. http://dx.doi.org/10.1007/978-3-642-41101-4_6.

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Brodsky, R. F. "Defining and Sizing Space Payloads." In Space Mission Analysis and Design, 229–84. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2692-2_9.

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Brodsky, R. F. "Defining and Sizing Space Payloads." In Space Mission Analysis and Design, 213–54. Dordrecht: Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3794-2_9.

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Brodsky, R. F. "Erratum to: Defining and Sizing Space Payloads." In Space Mission Analysis and Design, 874. Dordrecht: Springer Netherlands, 1992. http://dx.doi.org/10.1007/978-94-011-2692-2_25.

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Dinc, Ali. "Preliminary Sizing and Performance Calculations of Unmanned Air Vehicles." In Automated Systems in the Aviation and Aerospace Industries, 242–72. IGI Global, 2019. http://dx.doi.org/10.4018/978-1-5225-7709-6.ch009.

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In this chapter, preliminary sizing and performance calculations of unmanned air vehicles (UAV), with relation to its propulsion system, are explained. Starting with the mission profile of the air vehicle, which is one of the important design drivers, the UAV is sized for the requirements. The requirements in design consist of a set of target values (e.g., payload amount to be carried, range, endurance time, cost, etc.). Additionally, the parameters within mission profile such as cruising altitude and speed of aircraft affect engine type, power level required, fuel quantity, and therefore general dimensions and the gross weight of the aircraft. It is often an iterative process to size the air vehicle and engine together. UAV is designed in a loop of calculations in which sizing, flight performance, and engine performance are done for each phase of the mission or flight profile to satisfy the overall design mission and requirements.

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Тези доповідей конференцій з теми "Payload sizing"

Hung, Chien-Chun, Chao-Hung Lin, Yao-Jen Teng, Chih-Ming Chang, and Yi-Kuang Wu. "Study on Mini UAV Designs to Payload Requirements by Airplane Sizing Methodology." In AIAA Infotech@Aerospace 2010. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-3507.

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de Carvalho Bertoli, Gustavo, Geraldo José Adabo, and Gefeson Mendes Pacheco. "Conceptual Design of Solar Powered Unmanned Aircraft System Considering Payload Power Requirements on Sizing." In 25th SAE BRASIL International Congress and Display. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2016. http://dx.doi.org/10.4271/2016-36-0437.

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Andersen, Torben Ole, and Michael R. Hansen. "Automated Sizing Procedure of Servo-Driven Robot for Pallettes Handling." In ASME 2004 International Mechanical Engineering Congress and Exposition. ASMEDC, 2004. http://dx.doi.org/10.1115/imece2004-62409.

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A procedure for the automated sizing of spatial servo mechanisms is presented. The design performance is measured by means of a work task moving a payload from one point to another within a certain time. The design variables are composed of continuous and discrete parameters with the latter associated with the servo motor and planetary gears making up the servo drive. The costs are identified as the main objective for minimization whereas a number of side constraints related to accuracy, fatigue, vibrations and thermal conditions are presented and formulated mathematically. The two-level design procedure generates design from a motor and gear database that a subsequently subjected to minimization with a view to eliminate any constraint violations. The least costly of the feasible design are considered the optimal.

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Takahashi, Timothy, and Shane Donovan. "Incorporation of Mission Payload Power and Thermal Requirements into the Multi-Disciplinary Aircraft Performance and Sizing Process." In 13th AIAA/ISSMO Multidisciplinary Analysis Optimization Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-9169.

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Liu, Tuanjie, Xiaohong Chen, and Wei Ye. "Concept Selection Philosophy for Floating Control Facilities." In ASME 2010 29th International Conference on Ocean, Offshore and Arctic Engineering. ASMEDC, 2010. http://dx.doi.org/10.1115/omae2010-20805.

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Floating control facilities (FCFs) are designed to support fields using only subsea production system. Potential concepts, including Tension Leg Platform (TLP), Spar and semi-submersible can be selected as the FCFs. This paper discusses the philosophy of concept selection for FCFs. Two basic considerations for concept selection for FCFs are functional requirements and costs. Different structure types are first to be sized to meet the functional requirements for given water depths, environmental conditions and soil conditions. Then the costs for the procurement, construction, installation, hook up and commissioning for different concepts are estimated based on the sizes. Finally, the most cost-effective concept is chosen for further study to confirm the feasibilities of the concept by detailed analyses. Global sizing tools assisting concept selection have been developed by Ocean Dynamics LLC (Limited Liability Company) (ODL) over the past years. For a given concept, these sizing tools can find the optimized size based on costs to meet the functional requirements. Capabilities of the sizing tools cover the general layout, weight estimate (hull and deck), riser weight and stiffness estimate, loading conditions (transportation, normal operating, extreme, survival), hydrostatics and stability, natural periods, motions, air gap, environmental loads (wind, current, and mean wave forces), mooring sizing, cost estimate, and optimization based on the total costs. Two case studies in two different water depths, 140m and 1200m, are presented to illustrate the procedures and considerations in concept selection for floating control facilities. The FCFs used in the case studies are to support a Super Puma helideck, satellite communication equipment, an umbilical riser and option for a 3.5″ pipeline riser, with a total estimated topside payload as 400 Metric Ton (MT).

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Gerdes, John, Hugh A. Bruck, and Satyandra K. Gupta. "A Systematic Exploration of Wing Size on Flapping Wing Air Vehicle Performance." In ASME 2015 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/detc2015-47316.

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The design of a flapping wing air vehicle is dependent on the interaction of drive motors and wings. In addition to the wing shape and spar arrangement, sizing and flapping kinematics affect vehicle performance due to wing deformation resulting from flapping motions. To achieve maximum payload and endurance, it is necessary to select a wing size and flapping rate that will ensure strong performance and compatibility with drive motor capabilities. Due to several conflicting trade-offs in system design, this is a challenging problem. We have conducted an experimental study of several wing sizes at multiple flapping rates to build an understanding of the design space and ensure acceptable vehicle performance. To support this study, we have designed a new custom test stand and data post-processing procedure. The results of this study are used to build a design methodology for flapping wing air vehicles with improved performance and to highlight system design challenges and strategies for mitigation. Using the methodology described in this paper, we have developed a new flapping wing air vehicle called the Robo Raven II. This vehicle uses larger wings than Robo Raven and flight tests have confirmed that Robo Raven II has a higher payload capacity.

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Kunt, Cengiz O., Lawrence J. Mignosa, and James T. Pontius. "An Algorithm for Enveloping Linear Structural Response With Application to Spacecraft Stress Analysis." In ASME 1995 Design Engineering Technical Conferences collocated with the ASME 1995 15th International Computers in Engineering Conference and the ASME 1995 9th Annual Engineering Database Symposium. American Society of Mechanical Engineers, 1995. http://dx.doi.org/10.1115/detc1995-0146.

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Abstract An algorithm and a computer program are developed for spacecraft structural analysis to determine the maximum linear static response (stress, deformation, etc.) and the corresponding “worst direction” of the loading. Compared to the brute force approach of repeating the structural analysis to cover all the possible orientations of the load vector, the proposed approach is faster, more accurate, and computationally more efficient. Maximum structural response determination is illustrated through a case study of stress analysis conducted for the TRMM (Tropical Rainfall Measuring Mission) payload developed by NASA Goddard Space Flight Center and NASDA (National Space Development Agency of Japan). The paper includes part of the structural analysis conducted in sizing the Upper Instrument Support Platform, which provides support for two of TRMM’s major instruments.

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Zhang, Hanqing, and Derek Smith. "Interference of Top Tensioned Risers for Tension Leg Platforms." In ASME 2017 36th International Conference on Ocean, Offshore and Arctic Engineering. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/omae2017-61334.

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Dry tree top-tensioned risers (TTRs) are widely used on floating production systems such as TLPs and Spars for drilling, completion, workover and production. The interference between neighboring TTRs is an important consideration which has a direct impact on the total TTR payload budget and the wellbay size for floater sizing and cost. Since the realistic sizing of a floater is essential towards the concept selection process for a field development, TTR interference should be addressed at the early stages of an offshore oilfield development. If the floater is a tension leg platform (TLP) and the field has strong current with associated extreme waves, riser interference may be very challenging and can have direct impact on riser design and the sizing and layout of the TLP. The waves and the oscillating motions of the TLP will have effects on riser interference. The oscillating motion of the TLP can excite the vibrational motion of the risers, and the wave-induced velocity of water particles and the motions of the risers with the movement of the TLP increases the relative flow acting on each riser. The combined effects will increase the deflection of the risers and thus the likelihood of riser interference. The industry has not seen an acceptable interference analysis approach yet which can account for the combined effects of current, waves, and TLP motions. This paper proposes two engineering approaches for the interference analysis of top tensioned risers for tension leg platforms with the combined effects of current, surface waves, and associated floater motions being addressed.

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Gkoutzamanis, Vasilis G., Arjun Srinivas, Doukaini Mavroudi, Anestis I. Kalfas, Mavroudis D. Kavvalos, Konstantinos G. Kyprianidis, and George Korbetis. "Conceptual Design and Energy Storage Positioning Aspects for a Hybrid-Electric Light Aircraft." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15477.

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Abstract This work focuses on the feasibility of a 19-passenger hybrid-electric aircraft, to serve the short-haul segment within the 200–600 nautical miles. Its ambition is to answer some dominating research questions, during the evaluation and design of aircraft based on electric propulsion architectures. The potential entry into service of such aircraft is foreseen in 2030. A literature review is performed, to identify similar concepts that are under research and development. After the requirements definition, the first level of conceptual design is employed. Based on a set of assumptions, a methodology for the sizing of the hybrid-electric aircraft is described to explore the basis of the design space. Additionally, a methodology for the energy storage positioning is provided, to highlight the multidisciplinary aspects between the sizing of an aircraft, the selected architecture (series/parallel partial hybrid) and the energy storage operational characteristics. The design choices are driven by the aim to reduce CO2 emissions and accommodate boundary layer ingestion engines, with aircraft electrification. The results show that it is not possible to fulfill the initial design requirements (600 nmi) with a fully-electric aircraft configuration, due to the far-fetched battery necessities. It is also highlighted that compliance with airworthiness certifications is favored by switching to hybrid-electric aircraft configurations and relaxing the design requirements (targeted range, payload, battery technology). Finally, the lower degree of hybridization (40%) is observed to have a higher energy efficiency (12% lower energy consumption and larger CO2 reduction), compared to the higher degree of hybridization (50%), with respect to the conventional configuration.

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James, Daniel, and Maurizio Collu. "Aerodynamically Alleviated Marine Vehicle (AAMV): Bridging the Maritime-to-Air Domain." In SNAME 13th International Conference on Fast Sea Transportation. SNAME, 2015. http://dx.doi.org/10.5957/fast-2015-019.

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As high performance marine vessels with improved performance characteristics are being requested by governments (DARPA 2015) and commercial operators, the Aerodynamically Alleviated Marine Vehicle (AAMV) provides a solution that combines speeds typical of rotary-wing and light fixed-wing aircraft with payload and loitering ability found in current high speed craft. The innovative AAMV hybrid aero-marine platform utilizes an alternative implementation of wing-in-ground effect (WIG), a proven technology with a fascinating history of high speed marine operation. This paper outlines some challenges and the work completed towards the development of a hybrid class of vessel that is able to bridge the maritime-to-air domain, comfortably operating in the water surface yet still delivering the speed of aircraft during an airborne cruise phase. An overview of current WIG design is briefly presented, leading to the conceptual approach for the AAMV. Development and assessment of the aerodynamic properties of the lifting surfaces are shown, with analysis of several wing profiles and their effect on the total lift force, drag force, and pitching moment that directly influence the stability characteristics of the vehicle. A methodology for sizing an appropriate platform is summarized, along with experimental results of a high speed hullform with characteristics suitable for this intended application. Finally, particulars of a potential AAMV are derived using an iterative numerical method and briefly compared to current craft. For close to a century, the influence of ground effect has promised economy for low-skimming flight over smooth water (Raymond 1921), a promise that has yet to reach its full potential.

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