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Littérature scientifique sur le sujet « Space flight to Saturn »

Auteur : Grafiati
Publié le 4 juin 2021
Mis à jour le 31 juillet 2024

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Articles de revues sur le sujet "Space flight to Saturn"

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Himelblau, H., D. Kern et G. Davis. « Summary of Cassini Acoustic Criteria Development Using Titan IV Flight Data ». Journal of the IEST 36, no 5 (1 septembre 1993) : 19–27. http://dx.doi.org/10.17764/jiet.2.36.5.c408vvk263q216u5.

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The Cassini spacecraft is being developed by the Jet Propulsion Laboratory (JPL) for the National Aeronautics and Space Administration (NASA) to orbit and explore the planet Saturn, its rings, and satellites. Cassini will be launched on a Titan IV and boosted out of Earth orbit by a Centaur. This paper discusses the development of Cassini acoustic criteria using Titan IV flight data. Factors affecting the development of Cassini acoustic criteria using corrected Titan IV flight data1 include the statistical methods used to account for spatial and flight-to-flight variations, the use of maximax spectra, data corrections for acoustic pressure increases near the payload fairing surfaces, and corrections for payload fill factor effects. Separate acoustic criteria were developed for the two launch sites.
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Solórzano, Carlos Renato Huaura, Antonio Fernando Bertachini de Almeida Prado et Alexander Alexandrovich Sukhanov. « Analysis of Electric Propulsion System for Exploration of Saturn ». Mathematical Problems in Engineering 2009 (2009) : 1–14. http://dx.doi.org/10.1155/2009/756037.

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Exploration of the outer planets has experienced new interest with the launch of the Cassini and the New Horizons Missions. At the present time, new technologies are under study for the better use of electric propulsion system in deep space missions. In the present paper, the method of the transporting trajectory is used to study this problem. This approximated method for the flight optimization with power-limited low thrust is based on the linearization of the motion of a spacecraft near a keplerian orbit that is close to the transfer trajectory. With the goal of maximizing the mass to be delivered in Saturn, several transfers were studied using nuclear, radioisotopic and solar electric propulsion systems.
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Weber, Jessica M., Theresa C. Marlin, Medha Prakash, Bronwyn L. Teece, Katherine Dzurilla et Laura M. Barge. « A Review on Hypothesized Metabolic Pathways on Europa and Enceladus : Space-Flight Detection Considerations ». Life 13, no 8 (11 août 2023) : 1726. http://dx.doi.org/10.3390/life13081726.

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Enceladus and Europa, icy moons of Saturn and Jupiter, respectively, are believed to be habitable with liquid water oceans and therefore are of interest for future life detection missions and mission concepts. With the limited data from missions to these moons, many studies have sought to better constrain these conditions. With these constraints, researchers have, based on modeling and experimental studies, hypothesized a number of possible metabolisms that could exist on Europa and Enceladus if these worlds host life. The most often hypothesized metabolisms are methanogenesis for Enceladus and methane oxidation/sulfate reduction on Europa. Here, we outline, review, and compare the best estimated conditions of each moon’s ocean. We then discuss the hypothetical metabolisms that have been suggested to be present on these moons, based on laboratory studies and Earth analogs. We also detail different detection methods that could be used to detect these hypothetical metabolic reactions and make recommendations for future research and considerations for future missions.
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Cartlidge, Edwin. « Space scientists return to Saturn ». Physics World 17, no 6 (juin 2004) : 10. http://dx.doi.org/10.1088/2058-7058/17/6/20.

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Anonymous. « Space flight ». Eos, Transactions American Geophysical Union 75, no 48 (1994) : 562. http://dx.doi.org/10.1029/eo075i048p00562-04.

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Jones, Willie D. « Space Flight ». IEEE Spectrum 60, no 11 (novembre 2023) : 14–15. http://dx.doi.org/10.1109/mspec.2023.10309283.

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Burne, Sofía, César Bertucci, Nick Sergis, Laura F. Morales, Nicholas Achilleos, Beatriz Sánchez-Cano, Yaireska Collado-Vega, Sergio Dasso, Niklas J. T. Edberg et Bill S. Kurth. « Space Weather in the Saturn–Titan System ». Astrophysical Journal 948, no 1 (1 mai 2023) : 37. http://dx.doi.org/10.3847/1538-4357/acc738.

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Abstract New evidence based on Cassini magnetic field and plasma data has revealed that the discovery of Titan outside Saturn’s magnetosphere during the T96 flyby on 2013 December 1 was the result of the impact of two consecutive interplanetary coronal mass ejections (ICMEs) that left the Sun in 2013 early November and interacted with the moon and the planet. We study the dynamic evolution of Saturn's magnetopause and bow shock, which evidences a magnetospheric compression from late November 28 to December 4 (at least), under prevailing solar wind dynamic pressures of 0.16–0.3 nPa. During this interval, transient disturbances associated with the two ICMEs are observed, allowing for the identification of their magnetic structures. By analyzing the magnetic field direction, and the pressure balance in Titan’s induced magnetosphere, we show that Cassini finds Saturn’s moon embedded in the second ICME after being swept by its interplanetary shock and amid a shower of solar energetic particles that may have caused dramatic changes in the moon’s lower ionosphere. Analyzing a list of Saturn's bow shock crossings during 2004–2016, we find that the magnetospheric compression needed for Titan to be in the supersonic solar wind can be generally associated with the presence of an ICME or a corotating interaction region. This leads to the conclusion that Titan would rarely face the pristine solar wind, but would rather interact with transient solar structures under extreme space weather conditions.
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Gordon, Robert S. C. « Rings of Saturn : Fellini Rosi ». Journal of Italian Cinema & ; Media Studies 10, no 3 (1 juin 2022) : 449–74. http://dx.doi.org/10.1386/jicms_00139_1.

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This article offers a comparative reading of Gianfranco Rosi’s Sacro GRA (‘Holy GRA’) (2013) and Federico Fellini’s Roma (1972). It sets Sacro GRA within Rosi’s career, his ambiguous identity as an ‘Italian’ filmmaker and the film’s relation to the history of cinema in/on Rome and psycho-geographical road movies. It moves on to analyse Rosi’s treatment of place and urban space, comparing key motifs and patterns in Sacro GRA with the short episode of Fellini’s Roma, also set on the GRA, Rome’s urban outer ring road. This dual reading is articulated around four axes of comparison in the construction and evocation of the ring-road space: street furniture, metacinematic frames and recordings, noises and silences, machines and monsters. Through these and other incidental constellations, the article argues that the two films display parallel, at times symmetrical, fascinations with the urban as simultaneously a space of utopia and dystopia, nature and the man-made, past and future.
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ROBERTSON, DONALD F. « Human space flight ». Nature 338, no 6210 (mars 1989) : 10. http://dx.doi.org/10.1038/338010a0.

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Woolford, Barbara J. « Manned Space Flight ». Proceedings of the Human Factors Society Annual Meeting 30, no 4 (septembre 1986) : 354–57. http://dx.doi.org/10.1177/154193128603000410.

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An overview of manned space flight is given. This describes the key goals and achievements of the space programs of the United States and of the Soviet Union. The importance of the “Man” in manned space flight is emphasized. Human factors are shown to have played an ever increasing role in the design of manned space craft.
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Thèses sur le sujet "Space flight to Saturn"

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Wakley, Glenn Keith. « Space flight and bone ». Thesis, University of Bristol, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.246296.

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Shebanits, Oleg. « Pre-biotic molecules and dynamics in the ionosphere of Titan : a space weather station perspective ». Licentiate thesis, Uppsala universitet, Institutet för rymdfysik, Uppsalaavdelningen, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:uu:diva-248118.

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Saturn’s largest moon Titan (2575 km radius) is the second largest in the Solar system. Titan is the only known moon with a fully developed nitrogen-rich atmosphere with ionosphere extending to ~2000 km altitude, hosting complex organic chemistry. One of the main scientific interests of Titan’s atmosphere and ionosphere is the striking similarity to current theories of those of Earth ~3.5 billion years ago. The Cassini spacecraft has been in orbit around Saturn since 2004 and carries a wide range of instruments for investigating Titan’s ionosphere, among them the Langmuir probe, a “space weather station”, manufactured and operated by the Swedish Institute of Space Physics, Uppsala. This thesis reviews the first half of the PhD project on the production of pre-biotic molecules in the atmosphere of Titan and early Earth, focusing on the ion densities and dynamics in Titan’s ionosphere derived from the in-situ measurements by the Cassini Langmuir probe. One of the main results is the detection of significant, up to ~2300 cm-3, charge densities of heavy (up to ~13000 amu) negative ions in Titan’s ionosphere below 1400 km altitude. On the nightside of the ionosphere at altitudes below 1200 km, the heavy negative ion charge densities are comparable to the positive ion densities and are in fact the main negative charge carrier, making this region of the ionosphere exhibit properties of dusty plasma. The overall trend is the exponential increasing of the negative ion charge densities towards lower altitudes. Another important result is the detection of ion drifts that between 880-1100 km altitudes in Titan’s ionosphere translate to neutral winds of 0.5-5.5 km/s. Ion drifts define three regions by altitude, the top layer (above ~1600 km altitude) where the ions are frozen into the background magnetic field, the dynamo region (1100 – 1600 km altitudes) where the ions are drifting in partly opposing directions due to ion-neutral collisions in the presence of the magnetic and electric fields and the bottom layer (below 1100 km altitude) of the ionosphere, where the ions are coupled to neutrals by collisions.
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Curry, Diarmuid. « Data Acquisition Blasts Off - Space Flight Testing ». International Foundation for Telemetering, 2009. http://hdl.handle.net/10150/606142.

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ITC/USA 2009 Conference Proceedings / The Forty-Fifth Annual International Telemetering Conference and Technical Exhibition / October 26-29, 2009 / Riviera Hotel & Convention Center, Las Vegas, Nevada
In principle, the requirements for a flight test data acquisition system for space testing (launch vehicles, orbiters, satellites and International Space Station (ISS) installations) are very similar to those for more earth-bound applications. In practice, there are important environmental and operational differences that present challenges for both users and vendors of flight test equipment. Environmental issues include the severe vibration and shock experienced on take-off, followed by a very sharp thermal shock, culminating (for orbital vehicles) in a low temperature, low pressure, high radiation operating environment. Operational issues can include the need to dynamically adapt to changing configurations (for example when an instrumented stage is released) and the difficulty in Telemetering data during the initial launch stage from a vehicle that may not be recoverable, and therefore does not offer the option of an on-board recorder. Addressing these challenges requires simple, rugged and flexible solutions. Traditionally these solutions have been bespoke, specifically designed equipment. In an increasingly cost-conscious environment engineers are now looking to commercial off-the-shelf solutions. This paper discusses these solutions and highlights the issues that instrumentation engineers need to consider when designing or selecting flight test equipment.
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Upshaw, Kathy Suzanne. « Long duration manned space flight systems considerations ». Master's thesis, This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-12232009-020150/.

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Leung, Tonny. « Human space flight training centre a cradle for preparation of future space exploration / ». Click to view the E-thesis via HKUTO, 2004. http://sunzi.lib.hku.hk/hkuto/record/B31987163.

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Leung, Tonny, et 梁啟東. « Human space flight training centre : a cradle for preparation of future space exploration ». Thesis, The University of Hong Kong (Pokfulam, Hong Kong), 2004. http://hub.hku.hk/bib/B31987163.

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Holland, Dwight A. « Systems and human factors concerns for long-duration spaceflight ». Master's thesis, This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-01202010-020232/.

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Guidi, Mark Arthur. « Human factors implications of psychological stress in long duration space flight ». Master's thesis, This resource online, 1990. http://scholar.lib.vt.edu/theses/available/etd-03302010-020138/.

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Alves, Daniel F. Jr. « Space-Based Flight Termination System Incorporating GPS Telecommand Link ». International Foundation for Telemetering, 1997. http://hdl.handle.net/10150/609823.

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International Telemetering Conference Proceedings / October 27-30, 1997 / Riviera Hotel and Convention Center, Las Vegas, Nevada
This paper will investigate the areas which must be addressed to implement a truly integrated Range instrumentation system on a GPS-based Range, using a patented L-Band commanding scheme. Hardware issues will be highlighted as well the issues to be addressed in changing from an audio tone-frequency modulated command system to a digital system incorporating encryption and spread spectrum. Some thoughts addressing costs and schedule to incorporate this approach into the architecture of the U. S. Air Force Range Standardization and Automation (RSA) architecture, as a candidate GPS-based Range are also presented, as well as a discussion of the benefits to be accrued over the existing system, if this approach were adopted.
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O'Brien, Robin A. « Generic Decommutation Capabilities in the Space Flight Operations Center ». International Foundation for Telemetering, 1988. http://hdl.handle.net/10150/615254.

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International Telemetering Conference Proceedings / October 17-20, 1988 / Riviera Hotel, Las Vegas, Nevada
A generic decommutation capability has been created as part of the Space Flight Operation Center's goal of developing a multi-mission telemetry system. Generic decommutation involves separating the algorithmic description for extracting data from the actual implementation of decommutation. This was done by creating a Decommutation Map Language, which allows mission designers to describe decommutation algorithms without the restrictions imposed by a standard programming language. A Decommutation Map Compiler converts this description into C code, which is then linked with a decommutation library to provide an executable decommutation program. So far, this approach has been used successfully to decommutate several different types of data.
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Livres sur le sujet "Space flight to Saturn"

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Godwin, Robert. Project Apollo : Exploring the Moon. Burlington, Ont : Apogee Books, 2006.

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Bova, Ben. Saturn. New York : Tor, 2003.

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Bova, Ben. Saturn. New York, NY : Tor Books, 2003.

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Guleman, M. Space flight. Haifa : The Israel National Museum of Science Planninag and Technology, 1998.

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Donald, Davis, dir. Saturn. New York : Facts on File Publications, 1989.

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Davis, Don. Saturn. New York : Facts on File, 1989.

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United States. National Aeronautics and Space Administration, dir. Office of Space Flight : Space shuttle, flight systems, Space Station Freedom. [Washington, DC (Mail Code M-1, NASA Headquarters, Washington 20546)] : NASA, 1991.

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Mortillaro, Nicole. Saturn. Richmond Hill, Ont : Firefly Books, 2010.

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Erik, Gregersen, dir. Unmanned space flight. New York : Britannica Educational Pub. in association with Rosen Education Services, 2010.

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Tewari, Ashish. Optimal Space Flight Navigation. Cham : Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-03789-5.

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Chapitres de livres sur le sujet "Space flight to Saturn"

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Dlugos, Jenn, et Charlie Hatton. « Running Rings Around Saturn ». Dans Awesome Space Tech, 50–51. New York : Routledge, 2021. http://dx.doi.org/10.4324/9781003233190-33.

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Tewari, Ashish. « Space Flight ». Dans Basic Flight Mechanics, 99–121. Cham : Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-30022-1_6.

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Fischer, Georg, Donald A. Gurnett, William S. Kurth, Ferzan Akalin, Philippe Zarka, Ulyana A. Dyudina, William M. Farrell et Michael L. Kaiser. « Atmospheric Electricity at Saturn ». Dans Space Sciences Series of ISSI, 271–85. New York, NY : Springer New York, 2008. http://dx.doi.org/10.1007/978-0-387-87664-1_17.

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Harvey, Brian. « Manned flight ». Dans China in Space, 359–442. Cham : Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-19588-5_7.

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Woolford, Barbara, et Frances Mount. « Human Space Flight ». Dans Handbook of Human Factors and Ergonomics, 929–44. Hoboken, NJ, USA : John Wiley & Sons, Inc., 2006. http://dx.doi.org/10.1002/0470048204.ch34.

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Nixon, John. « Commercial Space Flight ». Dans Modern English for Aeronautics and Space Technology, 124–31. München : Carl Hanser Verlag GmbH & ; Co. KG, 2011. http://dx.doi.org/10.3139/9783446428348.011.

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Banik, Jeremy A., et Benjamin J. Urioste. « Space Flight Testing ». Dans Testing Large Ultra-Lightweight Spacecraft, 211–50. Reston ,VA : American Institute of Aeronautics and Astronautics, Inc., 2017. http://dx.doi.org/10.2514/5.9781624104657.0211.0250.

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Woolford, Barbara, Walter E. Sipes et Edna R. Fiedler. « Human Space Flight ». Dans Handbook of Human Factors and Ergonomics, 910–27. Hoboken, NJ, USA : John Wiley & Sons, Inc., 2012. http://dx.doi.org/10.1002/9781118131350.ch31.

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Greatrix, David R. « Introduction to Space Flight ». Dans Powered Flight, 293–321. London : Springer London, 2012. http://dx.doi.org/10.1007/978-1-4471-2485-6_9.

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Arridge, C. S., N. André, C. L. Bertucci, P. Garnier, C. M. Jackman, Z. Németh, A. M. Rymer et al. « Upstream of Saturn and Titan ». Dans Space Sciences Series of ISSI, 25–83. New York, NY : Springer US, 2011. http://dx.doi.org/10.1007/978-1-4614-3290-6_3.

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Actes de conférences sur le sujet "Space flight to Saturn"

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SHELTON, B., et T. MURPHY. « The Saturn V F-1 engine revisited ». Dans Space Programs and Technologies Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-1547.

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Asmar, S. W., D. V. Johnston, E. Maize et R. T. Mitchell. « Critical Monitoring of the Cassini Saturn Orbit Insertion Maneuver ». Dans Space OPS 2004 Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-617-413.

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Oleson, Steven R., Lisa Kohout et Ralph Lorenz. « Saturn Spacecraft Power : Trading Radioisotope, Solar, and Fission Power Systems ». Dans AIAA SPACE 2016. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-5361.

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Maize, Earl H. « The Cassini-Huygens Mission to Saturn and Titan ». Dans SPACE TECHNOLOGY AND APPLICATIONS INT.FORUM-STAIF 2005 : Conf.Thermophys in Micrograv;Conf Comm/Civil Next Gen.Space Transp ; 22nd Symp Space Nucl.Powr Propuls.;Conf.Human/Robotic Techn.Nat'l Vision Space Expl. ; 3rd Symp Space Colon. ; 2nd Symp.New Frontiers. AIP, 2005. http://dx.doi.org/10.1063/1.1867138.

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« Cassini/Huygens Arrives at Saturn ». Dans 55th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.iac-04-q.2.a.01.

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Mitchell, Robert T. « Saturn Revisited and Titan Unveiled ». Dans 56th International Astronautical Congress of the International Astronautical Federation, the International Academy of Astronautics, and the International Institute of Space Law. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.iac-05-p.e.6.01.

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Lipin, Amanda. « Robotic Hovercraft for Surface Mobility on Titan A Moon of Saturn ». Dans AIAA SPACE 2008 Conference & Exposition. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-7890.

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Bering, Edgar A., Matthew Giambusso, Mark Carter, Jared Squire et Franklin Chang Díaz. « Obtaining Faster Transit to Saturn Without A Jovian Flyby ». Dans 2018 AIAA SPACE and Astronautics Forum and Exposition. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-5104.

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Koschny, D., V. Dhiri, D. Frew, R. Hoofs, R. Lumb, G. Schwehm, K. Wirth et J. Zender. « Managing Risk to Ensure a Successful Cassini/Huygens Saturn Orbit Insertion (SOI) ». Dans Space OPS 2004 Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-304-155.

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Simplicio, Pedro, Paul Acquatella et Samir Bennani. « Launcher Attitude Control based on Incremental Nonlinear Dynamic Inversion : a Feasibility Study towards Fast and Robust Design Approaches ». Dans ESA 12th International Conference on Guidance Navigation and Control and 9th International Conference on Astrodynamics Tools and Techniques. ESA, 2023. http://dx.doi.org/10.5270/esa-gnc-icatt-2023-030.

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The so-called “New Space era” has been marked by a disruptive change in the business models, manufacturing technologies and agile practices of launch vehicle companies, aimed at minimising their production and operating costs in an ever more competitive market. Yet, only limited consideration has been given to the benefits that innovation in the field of control theory can bring, not only in terms of increasing the limits of performance, but also reducing mission preparation (“missionisation”) efforts. Also on government-led developments, recent launchers such as Ares I and VEGA [R1] still use the same design approach of the Saturn V rocket, i.e. linear controllers. This approach relies on single channel-at-a-time tuning and ad hoc gain-scheduling followed by extensive V&V, which are very time and cost consuming processes. In contrast to the approach presented above, the past few years have seen a growing interest in the application of artificial intelligence and machine learning methods for launcher GNC, but the industrial use of such data-driven/model-free methods remains limited by well-known issues related to training and certification of the algorithms on the full flight envelope of intended operation. In that sense, there is a clear gap between these strategies and the current state-of-practice, in which other techniques could bring relevant improvements; this is the case for nonlinear control algorithms, especially those based on Nonlinear Dynamic Inversion (NDI). On one hand, agile practices of New Space companies provide the ideal opportunity to explore the benefits of this type of design approach. On the other hand, a successful adoption of nonlinear launcher control will likely facilitate the augmentation with and transition to data-driven methods in the future. The NDI technique consists in cancelling the nonlinearities of a nonlinear system by means of state feedback so that the system is transformed into a linear form (for this reason, NDI is often known as “feedback linearisation”). For the resulting linear system, a single linear control law can be applied without the need for gain-scheduling to tailor the controller to different conditions. Being a multivariable technique, NDI allows to decouple and handle all the control channels in a systematic manner. The main drawback of this technique is that the linearisation fully relies on the accurate knowledge of the system, thus model mismatches may lead to substantial performance and stability losses. To tackle this drawback, an approach called Incremental NDI (INDI) was proposed in the early 2000s. By generating incremental commands (instead of total inputs) and employing acceleration feedback, the model dependency of the INDI technique is greatly reduced (for this reason, INDI is also known as a “sensor-based” approach). Being less model-dependent, INDI-based controllers become easier to design and significantly more robust. The resulting nonlinear control law still relies on an approximate model of the system’s control effectiveness, which in turn can be integrated with data-driven methods. Incremental NDI has been elaborated theoretically and applied successfully to high-performance systems including advanced aircraft flight control and a few studies for spacecraft attitude control. More recently, it has been applied to fault-tolerant control of aircraft subjected to sensor and actuator faults, as well as in real flight tests of small unmanned aircraft and of a business passenger jet [R2], demonstrating INDI’s performance and robustness against aerodynamic model uncertainties and disturbance rejection. However, to the best of the authors’ knowledge, its applicability to launch vehicles has never been adequately investigated. The potential benefits of INDI become even more relevant for the case of reusable launchers, which are characterised by much tighter dynamical couplings between (online-generated) trajectory and attitude during descent flight. It is therefore the objective of this study to present and raise awareness of the INDI technique among the launcher GNC community, to showcase its implementation on a representative application scenario, and to highlight its strengths and challenges in the face of the industrial state-of-practice. To achieve this, the paper provides a concise description of the NDI and INDI approach, followed by the detailed design and comparison of different control laws: linear, linear with angular acceleration feedback and INDI-based. The application scenario is that of a launcher model in ascent flight featuring attitude and drift degrees-of-freedom, actuator dynamics and moving-mass effects. All the controllers and filters are implemented at a sampling frequency that is compatible with current onboard capabilities (25 Hz). There are mainly two well-known challenges associated with the practical implementation of INDI-based control. The first one is that, by relying on angular acceleration and control input measurements/estimates, INDI controllers are generally more sensitive to sensor noise and actuator delay than classical controllers. The second challenge of INDI is that, due to its nonlinear nature, attaining an analytical proof of stability is not trivial [R3]. To assess the severity of the first challenge, the paper shows a comprehensive nonlinear simulation campaign with wind disturbances, uncertainties, as well as different levels of sensor noise and actuator delay. For the second challenge, the paper proposes a simple yet insightful linearisation-based approach to evaluate stability degradation related to an inexact feedback linearisation and to deviations from the control tuning conditions. From the results obtained in this feasibility study, the two limitations above seem to be outweighed by the potential benefits of INDI-based launcher control. Further analysis on this topic will address the impact of flexible modes and non-collocated sensing. [R1] A. Marcos, D. Navarro-Tapia, P. Simplício, S. Bennani, “Robust Control for Launchers: VEGA Study Case,” Journal of the Society of Instrument and Control Engineers, vol. 59, March 2020; [R2] F. Grondman, G. Looye, R. Kuchar, Q.P. Chu, E. van Kampen, “Design and Flight Testing of Incremental Nonlinear Dynamic Inversion-based Control Laws for a Passenger Aircraft,” AIAA SciTech Forum 2018; [R3] X. Wang, E. van Kampen, Q.P. Chu, P. Lu, “Stability Analysis for Incremental Nonlinear Dynamic Inversion Control”, Journal of Guidance, Control, and Dynamics, vol. 42, May 2019.
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Rapports d'organisations sur le sujet "Space flight to Saturn"

1

Burton, Russell R. Artificial Gravity in Space Flight. Fort Belvoir, VA : Defense Technical Information Center, janvier 1994. http://dx.doi.org/10.21236/ada273420.

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2

Giri, Chaitanya. Transcending politics with space flight. Sous la direction de Sara Phillips. Monash University, avril 2022. http://dx.doi.org/10.54377/36a2-b4fd.

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AIR FORCE SPACE COMMAND SPACE MISSILE SYS CTR. Space and Missile Systems Center Standard : Space Flight Pressurized Systems. Fort Belvoir, VA : Defense Technical Information Center, février 2015. http://dx.doi.org/10.21236/ada619899.

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4

Dyer, G. High Current Electron Gun for Space Flight. Fort Belvoir, VA : Defense Technical Information Center, décembre 1986. http://dx.doi.org/10.21236/ada178467.

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5

Higbie, P. R., S. S. Han et R. S. Wagner. The utility of diamond sensors for space flight. Office of Scientific and Technical Information (OSTI), mars 1996. http://dx.doi.org/10.2172/211374.

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Smith, Frank D., Dennis J. Camp et Katherine K. Leister. Lightweight Exo-Atmospheric Projectile Space Test--LEAP 2 Flight. Fort Belvoir, VA : Defense Technical Information Center, février 1992. http://dx.doi.org/10.21236/ada338970.

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Spravka, John J., et Timothy R. Jorris. Current Hypersonic and Space Vehicle Flight Test and Instrumentation. Fort Belvoir, VA : Defense Technical Information Center, juin 2015. http://dx.doi.org/10.21236/ada619521.

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TETRA TECH INC SAN ANTONIO TX. Environmental Assessment for Flight Test to the Edge of Space. Fort Belvoir, VA : Defense Technical Information Center, décembre 2008. http://dx.doi.org/10.21236/ada611293.

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Sullivan, John, Laurence Twigg, Trong Nguyen et Maurice Roots. TRACER NASA Goddard Space Flight Center TOLNet Field Campaign Report. Office of Scientific and Technical Information (OSTI), octobre 2022. http://dx.doi.org/10.2172/1894663.

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Usher, Tracy. GAMMA-RAY LARGE AREA SPACE TELESCOPE (GLAST) BALLOON FLIGHT ENGINEERING MODEL : OVERVIEW. Office of Scientific and Technical Information (OSTI), novembre 2002. http://dx.doi.org/10.2172/808684.

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