The Experts below are selected from a list of 19542 Experts worldwide ranked by ideXlab platform
Sophie Missonnier - One of the best experts on this subject based on the ideXlab platform.
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multidisciplinary system optimisation on the design of Cost effective space Launch vehicle
World Congress of Structural and Multidisciplinary Optimisation, 2017Co-Authors: Cedric Dupont, Andrea Tromba, Sophie MissonnierAbstract:This paper presents the methodology and the optimization strategy applied by Bertin Technologies for over 10 years to perform space Launch vehicle design and implemented by using the property software platform HADES V15.0. The problem formulation consists in finding the best Launch vehicle concept i.e. the one maximising performances (payload mass on final orbit) and minimising Launch Cost while satisfying technical, mission and architecture constraints. The strategy is based on a Multidisciplinary Design Feasible (MDF) approach coupled with the use of Genetic Algorithms (GA) for global optimization, and Gradient-Based Algorithms for final tuning and results refining. HADES V15.0 platform provides the associated software environment integrating a number of technical and economic modules consistently interconnected within a system optimization loop. The main disciplines taken into account in the platform are related to the Launcher’s propulsion, structure, aerodynamics, trajectory optimization and Cost. The use of an integrated platform for multi-objective and multi-disciplinary optimization enables an efficient process and quick optimization. This methodology is particularly well fitted to the design of a small space Launch vehicle, allowing to take into account the multidisciplinary nature of such a complex system and to manage the inherent sensitivity for this kind of vehicle. The application case presented was used to design Bertin Technologies’ Cost-effective expandable Space Launch Vehicle (SLV) for Microsatellites, ROXANE.
Cedric Dupont - One of the best experts on this subject based on the ideXlab platform.
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multidisciplinary system optimisation on the design of Cost effective space Launch vehicle
World Congress of Structural and Multidisciplinary Optimisation, 2017Co-Authors: Cedric Dupont, Andrea Tromba, Sophie MissonnierAbstract:This paper presents the methodology and the optimization strategy applied by Bertin Technologies for over 10 years to perform space Launch vehicle design and implemented by using the property software platform HADES V15.0. The problem formulation consists in finding the best Launch vehicle concept i.e. the one maximising performances (payload mass on final orbit) and minimising Launch Cost while satisfying technical, mission and architecture constraints. The strategy is based on a Multidisciplinary Design Feasible (MDF) approach coupled with the use of Genetic Algorithms (GA) for global optimization, and Gradient-Based Algorithms for final tuning and results refining. HADES V15.0 platform provides the associated software environment integrating a number of technical and economic modules consistently interconnected within a system optimization loop. The main disciplines taken into account in the platform are related to the Launcher’s propulsion, structure, aerodynamics, trajectory optimization and Cost. The use of an integrated platform for multi-objective and multi-disciplinary optimization enables an efficient process and quick optimization. This methodology is particularly well fitted to the design of a small space Launch vehicle, allowing to take into account the multidisciplinary nature of such a complex system and to manage the inherent sensitivity for this kind of vehicle. The application case presented was used to design Bertin Technologies’ Cost-effective expandable Space Launch Vehicle (SLV) for Microsatellites, ROXANE.
Kimiya Komurasaki - One of the best experts on this subject based on the ideXlab platform.
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Replacement of chemical rocket Launchers by beamed energy propulsion.
Applied Optics, 2014Co-Authors: Masafumi Fukunari, Anthony Arnault, Toshikazu Yamaguchi, Kimiya KomurasakiAbstract:Microwave Rocket is a beamed energy propulsion system that is expected to reach space at drastically lower Cost. This Cost reduction is estimated by replacing the first-stage engine and solid rocket boosters of the Japanese H-IIB rocket with Microwave Rocket, using a recently developed thrust model in which thrust is generated through repetitively pulsed microwave detonation with a reed-valve air-breathing system. Results show that Microwave Rocket trajectory, in terms of velocity versus altitude, can be designed similarly to the current H-IIB first stage trajectory. Moreover, the payload ratio can be increased by 450%, resulting in Launch-Cost reduction of 74%.
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In-space transportation of a solar power satellite using a hall thruster propulsion system
2012 International Conference on Renewable Energy Research and Applications (ICRERA), 2012Co-Authors: Yuki Ito, Kimiya Komurasaki, Masakatsu Nakano, Tony Schönherr, Shinatora Cho, Hiroyuki KoizumiAbstract:A feasibiity study of solar power satellite (SPS) in-space transportation using a Hall thruster propulsion system was conducted based on Cost evaluation. The transportation scenario was optimized through the Cost evaluation: the choice of reusing or disposing orbit transfer vehicle (OTV), and power of propulsion system. From the result, the case of reusing OTVs was superior to the case of disposing them because the OTVs' manufacturing Cost is predominant in the total Cost. In addition, the power had only limited influence on the Cost. In order to achieve the target Cost of $3.75 billion (300 billion yen) from LEO to GEO including propellant Launch Cost from Earth to LEO, further improvements are required, and related desirable innovations are discussed.
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Microwave Rocket with 30N thrust and further thrust augmentation with reed-valve air intake
2012 IEEE Vehicle Power and Propulsion Conference, 2012Co-Authors: Shohei Saitoh, Yasuhisa Oda, Kimiya Komurasaki, Toshikazu Yamaguchi, Reiji Komatsu, Ken Kajiwara, Koji Takahashi, Keishi SakamotoAbstract:Microwave Rocket is a future low Cost transportation system for a large-scale infrastructure construction such as SSPS (Space Solar Power System). It is expected to realize a high payload ratio and low Launch Cost, because propulsive energy is remotely supplied from a clustered Gyrotron on the ground and air-breathing flight without fuel will be achieved using microwave detonation. For a feasibility study, it is important to know maximum thrust available with a single 1MW Gyrotron. In this study, main objective is to maximize time-averaged thrust under high power operation conditions. As a result, new thrust record of 30 N was accomplished. In addition, reed valve air-breathing system was introduced, and the effect of reed valves was experimentally investigated. Although further augmentation was not observed, air-refreshment in a thruster was promoted with the reed valve system.
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A preliminary study of pulse-laser powered orbital Launcher
Acta Astronautica, 2009Co-Authors: Hiroshi Katsurayama, Kimiya Komurasaki, Yoshihiro ArakawaAbstract:Abstract An air-breathing pulse-laser powered orbital Launcher has been proposed as an alternative to conventional chemical Launch systems. The aim of the present study is to assess its feasibility through the estimation of its achievable payload mass per unit beam power and Launch Cost. A transfer trajectory from the ground to a geosynchronous Earth orbit (GEO) is proposed, and the Launch trajectory to its geosynchronous transfer orbit (GTO) is computed using the realistic performance modeled in the pulsejet, ramjet, and rocket flight modes of the Launcher. Results show that the Launcher can transfer 0.084 kg of payload per 1 MW beam power to a geosynchronous earth orbit. The Cost becomes a quarter of existing systems if one can divide a single Launch into 24,000 multiple Launches.
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Competitiveness-Analysis of a Future Space Transportation System: The Microwave Rocket
AIP Conference Proceedings, 2008Co-Authors: Armin Herbertz, Yasuhisa Oda, Kimiya KomurasakiAbstract:This paper evaluates the potential performance of a microwave propelled craft as a future space transportation system. The engine performance is evaluated on the basis of a the thermodynamic Lenoir‐cycle. Different propellants are discussed for the in‐space part of the ascent trajectory. A Launch trajectory analysis with parameter variation is performed. Based on the results of the trajectory analysis the recurring Launch Cost is estimated. The study concludes with the derived margins for the vehicle's airframe design.
Andrea Tromba - One of the best experts on this subject based on the ideXlab platform.
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multidisciplinary system optimisation on the design of Cost effective space Launch vehicle
World Congress of Structural and Multidisciplinary Optimisation, 2017Co-Authors: Cedric Dupont, Andrea Tromba, Sophie MissonnierAbstract:This paper presents the methodology and the optimization strategy applied by Bertin Technologies for over 10 years to perform space Launch vehicle design and implemented by using the property software platform HADES V15.0. The problem formulation consists in finding the best Launch vehicle concept i.e. the one maximising performances (payload mass on final orbit) and minimising Launch Cost while satisfying technical, mission and architecture constraints. The strategy is based on a Multidisciplinary Design Feasible (MDF) approach coupled with the use of Genetic Algorithms (GA) for global optimization, and Gradient-Based Algorithms for final tuning and results refining. HADES V15.0 platform provides the associated software environment integrating a number of technical and economic modules consistently interconnected within a system optimization loop. The main disciplines taken into account in the platform are related to the Launcher’s propulsion, structure, aerodynamics, trajectory optimization and Cost. The use of an integrated platform for multi-objective and multi-disciplinary optimization enables an efficient process and quick optimization. This methodology is particularly well fitted to the design of a small space Launch vehicle, allowing to take into account the multidisciplinary nature of such a complex system and to manage the inherent sensitivity for this kind of vehicle. The application case presented was used to design Bertin Technologies’ Cost-effective expandable Space Launch Vehicle (SLV) for Microsatellites, ROXANE.
D.j. Goldstein - One of the best experts on this subject based on the ideXlab platform.
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small payload orbit transfer sport sup tm system lowering Launch Cost without increased risk
IEEE Aerospace Conference, 2001Co-Authors: P.w. Gloyer, D.j. GoldsteinAbstract:The past decade has seen efforts to lower Costs by "doing more with less", instead of making innovative changes in the way missions are designed and implemented. Now, the industry is turning towards more intelligent approaches to mission design. AeroAstro has developed the Small Payload ORbit Transfer (SPORT/sup TM/) system to provide a flexible low-Cost orbit transfer capability, enabling small payloads to use low-Cost secondary Launch opportunities and still reach their desired final orbits. This allows small payloads to effectively use a wider variety of Launch opportunities, including numerous under-utilized geosynchronous transfer orbit (GTO) slots. Its use, in conjunction with growing opportunities for secondary Launches, enables "better, cheaper, faster" missions through innovative mission design and lower Cost access to space, not increased risk. SPORT uses a suite of innovative technologies that are packaged in a simple, reliable, modular system. SPORT achieves its orbit transfer capability through a combination of chemical propulsion and aerobraking technology. This paper discusses the SPORT design and its application to overall small satellite mission development.
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Small payload orbit transfer (SPORT/sup TM/) system: lowering Launch Cost without increased risk
2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542), 1Co-Authors: P.w. Gloyer, D.j. GoldsteinAbstract:The past decade has seen efforts to lower Costs by "doing more with less", instead of making innovative changes in the way missions are designed and implemented. Now, the industry is turning towards more intelligent approaches to mission design. AeroAstro has developed the Small Payload ORbit Transfer (SPORT/sup TM/) system to provide a flexible low-Cost orbit transfer capability, enabling small payloads to use low-Cost secondary Launch opportunities and still reach their desired final orbits. This allows small payloads to effectively use a wider variety of Launch opportunities, including numerous under-utilized geosynchronous transfer orbit (GTO) slots. Its use, in conjunction with growing opportunities for secondary Launches, enables "better, cheaper, faster" missions through innovative mission design and lower Cost access to space, not increased risk. SPORT uses a suite of innovative technologies that are packaged in a simple, reliable, modular system. SPORT achieves its orbit transfer capability through a combination of chemical propulsion and aerobraking technology. This paper discusses the SPORT design and its application to overall small satellite mission development.