Bibliografias temáticas / Reusable Launchers

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Literatura científica selecionada sobre o tema "Reusable Launchers"

Autor: Grafiati
Publicado: 23 de novembro de 2024
Última modificação: 31 de julho de 2025

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Artigos de revistas sobre o assunto "Reusable Launchers"

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Baiocco, P., and Ch Bonnal. "Technology demonstration for reusable launchers." Acta Astronautica 120 (March 2016): 43–58. http://dx.doi.org/10.1016/j.actaastro.2015.11.032.

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Lobanovsky, Yu I. "Efficiency analysis of reusable aerospace launchers." Aerospace Science and Technology 1, no. 1 (1997): 37–46. http://dx.doi.org/10.1016/s1270-9638(97)90022-5.

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Chelaru, Teodor-Viorel, Valentin Pană, and Costin Ene. "Performance Evaluation for Launcher Testing Vehicle." Aerospace 9, no. 9 (2022): 504. http://dx.doi.org/10.3390/aerospace9090504.

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The paper’s purpose is to present a calculus model for a testing vehicle that can be used to validate guidance, navigation and control systems for reusable launchers in all flight phases. The technical solution is based on a throttleable engine with thrust vectoring control and a reaction control system (RCS) used for roll. For calculus, we will develop a nonlinear model with six degrees of freedom, based on quaternion, extended with nonlinear equations that use pulse modulation in order to control roll. In order to synthesize the controller, we also develop a linear model similar to the launc
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Simplício, Pedro, Andrés Marcos, and Samir Bennani. "Guidance of Reusable Launchers: Improving Descent and Landing Performance." Journal of Guidance, Control, and Dynamics 42, no. 10 (2019): 2206–19. http://dx.doi.org/10.2514/1.g004155.

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D’Angelo, Salvatore, Edmondo Minisci, Daniele Di Bona, and Luciano Guerra. "Optimization Methodology for Ascent Trajectories of Lifting-Body Reusable Launchers." Journal of Spacecraft and Rockets 37, no. 6 (2000): 761–67. http://dx.doi.org/10.2514/2.3648.

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Musso, Girolamo, Iara Figueiras, Héléna Goubel, et al. "A Multidisciplinary Optimization Framework for Ecodesign of Reusable Microsatellite Launchers." Aerospace 11, no. 2 (2024): 126. http://dx.doi.org/10.3390/aerospace11020126.

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The commercial space launch sector is currently undergoing a significant shift, with increasing competition and demand for launch services, as well as growing concerns about the environmental impact of rocket launches. To address these challenges, within the New Space Portugal project scope, a multidisciplinary framework for designing and optimizing new launch vehicles is proposed. Creating a more resilient and responsible space industry can be achieved by combining technological innovation and environmental sustainability, as emphasized by the framework. The main scope of the framework was to
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Duparcq, J. L., E. Hermant, and D. Scherrer. "Turbojet-type engines for the airbreathing propulsion of reusable winged launchers." Acta Astronautica 29, no. 1 (1993): 41–50. http://dx.doi.org/10.1016/0094-5765(93)90068-8.

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Gulczyński, Mateusz T., Robson H. S. Hahn, Jan C. Deeken, and Michael Oschwald. "Turbopump Parametric Modelling and Reliability Assessment for Reusable Rocket Engine Applications." Aerospace 11, no. 10 (2024): 808. http://dx.doi.org/10.3390/aerospace11100808.

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The development of modern reusable launchers, such as the Themis project with its LOX/LCH4 Prometheus engine, CALLISTO—a reusable VTVL-launcher first-stage demonstrator with a LOX/LH2 RSR2 engine, and SpaceX’s Falcon 9 with its Merlin 1D engine, underscores the need for advanced control algorithms to ensure reliable engine operation. The multi-restart capability of these engines imposes additional requirements for throttling, necessitating an extended controller-validity domain to safely achieve low thrust levels across various operating regimes. This capability also increases the risk of comp
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Simplício, Pedro, Andrés Marcos, and Samir Bennani. "Reusable Launchers: Development of a Coupled Flight Mechanics, Guidance, and Control Benchmark." Journal of Spacecraft and Rockets 57, no. 1 (2020): 74–89. http://dx.doi.org/10.2514/1.a34429.

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Bonnal, Ch, and M. Caporicci. "Future reusable launch vehicles in europe: the FLTP (Future Launchers Technologies Programme)." Acta Astronautica 47, no. 2-9 (2000): 113–18. http://dx.doi.org/10.1016/s0094-5765(00)00050-3.

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Teses / dissertações sobre o assunto "Reusable Launchers"

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Berry, W. "Reusable launchers." Thesis, Cranfield University, 1993. http://hdl.handle.net/1826/3902.

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This research on Reusable Launchers was motivated by the need to reduce substantially the cost of space transportation. The specific objective was to- explore the perception that launcher reusability is the key to achieving these major cost reductions. The exploration was achieved by undertaking a comparative system study on potentially feasible reusable launcher concepts, using a consistent set of design tools, a standard analysis methodology and a standard reference mission. To set the background f or the research, the results of an extensive literature review are 'presented on the vehicle s
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Zaragoza, Prous Guillermo. "Guidance and Control for Launch and Vertical Descend of Reusable Launchers using Model Predictive Control and Convex Optimisation." Thesis, Luleå tekniska universitet, Institutionen för system- och rymdteknik, 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-81354.

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The increasing market of small and affordable space systems requires fast and reliablelaunch capabilities to cover the current and future demand. This project aims to studyand implement guidance and control schemes for vertical ascent and descent phases ofa reusable launcher. Specifically, the thesis focuses on developing and applying ModelPredictive Control (MPC) and optimisation techniques to several kino-dynamic modelsof rockets. Moreover, the classical MPC method has been modified to include a decreasingfactor for the horizon used, enhancing the performance of the guidance and control.Mult
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Gibart, Jules. "Non-linear stability of a liquid propelled rocket engine in closed loop regulation." Electronic Thesis or Diss., université Paris-Saclay, 2024. http://www.theses.fr/2024UPAST110.

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Dans le cadre du développement de moteurs de fusée réutilisables, les exigences de fonctionnement des différents éléments composant un moteur ont connu de grandes évolutions. Alors qu'un moteur classique était conçu pour un nombre restreint de points de fonctionnement, un moteur réutilisable doit répondre à des exigences sur une large plage de points, afin d'effectuer des manoeuvres plus complexes. En conséquence, les lois de commande des moteurs fusées ont subi une évolution similaire, rendant nécessaire la loi de commande en boucle fermée. Bien que de nombreuses études aient été réalisées su
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MABBOUX, ROMAIN. "Optimization of the pressurization system of the Themis reusable rocket first stage demonstrator." Thesis, KTH, Skolan för industriell teknik och management (ITM), 2020. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-301295.

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The design of complex systems such as a launcher, or subsystems like its pressurization system, is known to be fastidious and expensive especially in the space domain. However, the recent emergence of new actors in this domain has been a game changer, binding these systems to fulfil more and more requirements (cheap, efficient, rapidly produced, aesthetic, environmentally friendly…) in order to compete with the market. For these reasons, engineers now need more than ever to consider the full picture of a system or subsystem in order to optimize it. In this context, this document aims to presen
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Bulut, Jane. "Design and CFD analysis of the demonstrator aerospike engine for a small satellite launcher application." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

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Starting with a brief overview of thrust generation for launchers, this study focuses on the design process of the demonstrator aerospike engine, DEMOP-1, of the Pangea Aerospace's commercial grade engine and its flow field analysis. The primary goal of the study is to obtain the plug nozzle design delivers 30 kN thrust using cryogenic liquid oxygen (LOX) as the oxidizer and cryogenic liquid methane (LCH4) as the fuel, with the mixture ratio of 3.4. Design parameters considered as 30 bar of combustion chamber pressure (Po) and expansion ratio as 15 for an optimum expanded nozzle. On the basi
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Lantelme, Melissa. "Modélisation des grandeurs aérothermodynamiques pariétales : application à la rentrée atmosphérique des lanceurs réutilisables." Electronic Thesis or Diss., Toulouse, ISAE, 2024. http://www.theses.fr/2024ESAE0025.

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Cette étude consiste à développer une méthode de prévision de la distribution du flux de chaleur surfacique pour des lanceurs réutilisables qui soit adaptée à une phase de conception préliminaire. Les phases de vol hypersonique les plus critiques lors de la réentrée atmosphérique du lanceur sont celles pour lesquelles les flux de chaleurs les plus importants apparaissent à la surface. Ainsi, pour les études de conception et de préparation de mission, il est indispensable de posséder des outils élaborés et rapides qui permettent d’obtenir des estimations de ces flux de chaleur surfaciques. Cela
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Livros sobre o assunto "Reusable Launchers"

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Gibbins, Martin N. Systems integration and demonstration of advanced reusable structure for ALS. National Aeronautics and Space Administration, Langley Research Center, 1991.

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2

Center, NASA Glenn Research, ed. Advanced electric propulsion for RLV launched geosynchronous spacecraft. National Aeronautics and Space Administration, Glenn Research Center, 1999.

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Advanced electric propulsion for RLV launched geosynchronous spacecraft. National Aeronautics and Space Administration, Glenn Research Center, 1999.

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4

Reentry: SpaceX, Elon Musk, and the Reusable Rockets that Launched a Second Space Age. BenBella Books, Inc., 2024.

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Capítulos de livros sobre o assunto "Reusable Launchers"

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van Pelt, Michel. "Reusable launchers." In Dream Missions. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-53941-6_3.

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Salt, David J. "Could a Subsonic Air-Launched Reusable Launch Vehicle (RLV) Enable a Paradigm Shift in Space Operations?" In Space Operations: Innovations, Inventions, and Discoveries. American Institute of Aeronautics and Astronautics, Inc., 2015. http://dx.doi.org/10.2514/5.9781624101991.0185.0218.

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Kislykh, V. V., and I. A. Reshetin. "Afterbody Effects Study on Energia Reusable Launcher Models. Selection of Jet Propulsive Masses Parameters Within Jet Streams Ejecting Model." In Separated Flows and Jets. Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-84447-8_105.

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Yeager, Kenneth R. "Program Evaluation: This Is Rocket Science." In Evidence-Based Practice Manual: Research and Outcome Measures in Health and Human Services. Oxford University PressNew York, NY, 2004. http://dx.doi.org/10.1093/oso/9780195165005.003.0071.

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Abstract How could the space shuttle Challenger catastrophe and the deaths of all crew members have been prevented? How safe is health care? Can medical errors be prevented? Can process measurement and effective quality programming prevent unnecessary fatalities? This chapter examines processes associated with estimation of safety in arenas where minimal tolerance exists for error. Process measurement and evaluation is recommended as a tool to contribute to reduction of critical errors. The space shuttle program was begun in the early 1970s with the concept of creating reusable craft for trans
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Koshova, Svitlana. "Innovative Trends in the Creation of Rocket and Spacecraft Equipment for the Purpose of Enhancement of National Security". У Стратегія сучасного розвитку України: синтез правових, освітніх та економічних механізмів : колективна монографія / за загальною редакцією професора Старченка Г. В. ГО «Науково-освітній інноваційний центр суспільних трансформацій», 2022. http://dx.doi.org/10.54929/monograph-12-2022-05-01.

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The space industry has grown and evolved significantly over the past six decades. Exploitation of space under the auspices of several space states has become an activity in more than 60 countries around the world. For its financing, in addition to state capital, the private sector began to be actively involved in the form of investment resources, which made it possible to increase the pace of its development several times. In recent years, interest in space exploration and the benefits that can be, derived from it has grown significantly. This became possible due to the significant simplificat
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Trabalhos de conferências sobre o assunto "Reusable Launchers"

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Marey, Raquel, Federico Toso, and Giuseppe Guidotti. "Multidisciplinary Vehicle Design and Trajectory Optimisation for the Preliminary Sizing and Performance Assessment of Reusable Launchers." In IAF Space Transportation Solutions and Innovations Symposium, Held at the 75th International Astronautical Congress (IAC 2024). International Astronautical Federation (IAF), 2024. https://doi.org/10.52202/078373-0033.

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Illig, Michel, Shinji Ishimoto, Etienne Dumont, and Yasuhiro Saito. "A Reusable Launcher 1st Stage Demonstrator for Europe and Japan: CALLISTO." In IAF Space Transportation Solutions and Innovations Symposium, Held at the 75th International Astronautical Congress (IAC 2024). International Astronautical Federation (IAF), 2024. https://doi.org/10.52202/078373-0046.

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Zaragoza Prous, Guillermo, Leonard Felicetti, and Enric Grustan Gutierrez. "Model Predictive Control Strategy with a Decreasing Horizon Interval for a Reusable Launcher in a Landing Scenario." In IAF Astrodynamics Symposium, Held at the 75th International Astronautical Congress (IAC 2024). International Astronautical Federation (IAF), 2024. https://doi.org/10.52202/078368-0159.

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Klevanski, Josef. "Flight Dynamics Simulation and Aerodynamic Database of a Retro-Propulsion Assisted Reusable Launcher Within the RETPRO Project." In IAF Space Transportation Solutions and Innovations Symposium, Held at the 75th International Astronautical Congress (IAC 2024). International Astronautical Federation (IAF), 2024. https://doi.org/10.52202/078373-0103.

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Denaro, Angelo, Elena Brach Prever, and Marco Nebiolo. "Developments on Cryogenic Insulations for Reusable Launchers." In AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference. American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-3436.

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Denaro, A., E. Brach Prever, M. Nebiolo, and H. Ritter. "Screening Tests on Cryogenic Insulations for Reusable Launchers." In International Conference On Environmental Systems. SAE International, 2005. http://dx.doi.org/10.4271/2005-01-2899.

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Denaro, A., and H. Ritter. "Developments on Cryogenic Tank Insulation for Reusable Launchers." In International Conference On Environmental Systems. SAE International, 2004. http://dx.doi.org/10.4271/2004-01-2565.

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Liu, Zibo, and Ran Zhang. "Actuator-constrained Trajectory Optimization for Reusable Launchers’ Landing." In 2022 13th Asian Control Conference (ASCC). IEEE, 2022. http://dx.doi.org/10.23919/ascc56756.2022.9828171.

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Angelino, E., D. Dosio, and G. Borriello. "Reusable launchers tank structures - Requirements definition and experimental development." In 8th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-1592.

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Wulz, H., U. Trabandt, H. Wulz, and U. Trabandt. "Large integral hot CMC structures designed for future reusable launchers." In 32nd Thermophysics Conference. American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2485.

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