Auswahl der wissenschaftlichen Literatur zum Thema „Moteurs fusée“
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Zeitschriftenartikel zum Thema "Moteurs fusée"
Lefrançois, Emmanuel, Gouri Dhatt und Dany Vandromme. „Modèle numérique de couplage fluide-structure avec application aux moteurs fusée“. Revue Européenne des Éléments Finis 8, Nr. 2 (Januar 1999): 159–99. http://dx.doi.org/10.1080/12506559.1999.10511362.
Der volle Inhalt der QuelleGuichard, D. „Sélection des matériaux pour les rouets centrifuges cryotechniques de moteurs de fusée“. Revue de Métallurgie 93, Nr. 12 (Dezember 1996): 1501–7. http://dx.doi.org/10.1051/metal/199693121501.
Der volle Inhalt der QuelleVerthier, Brian, Gian Piero Celata, Giuseppe Zummo, Catherine Colin und Jérémy Follet. „Impact de la micro pesanteur sur le flux de chaleur et la température de remouillage lors de la mise en froid d'un tube : application au rallumage de moteurs-fusée“. Mécanique & Industries 10, Nr. 3-4 (Mai 2009): 231–37. http://dx.doi.org/10.1051/meca/2009062.
Der volle Inhalt der QuelleRothmund, Christophe. „70 ans de moteurs-fusées à Vernon“. Études Normandes 7, Nr. 1 (2018): 39–45. http://dx.doi.org/10.3406/etnor.2018.3836.
Der volle Inhalt der QuelleBernard, R., C. Rebattet, J. Desclaux und F. Martignac. „Essais hydrauliques de l'inducteur hydrogène du moteur fusée Vulcain“. La Houille Blanche, Nr. 7-8 (November 1988): 603–9. http://dx.doi.org/10.1051/lhb/1988058.
Der volle Inhalt der QuelleMoraux, J. Y., D. Girodin und J. M. de Monicault. „Choix et évolution des matériaux dans les roulements de turbopompe cryotechnique de moteur fusée“. Matériaux & Techniques 89, Nr. 1-2 (2001): 15–20. http://dx.doi.org/10.1051/mattech/200189010015.
Der volle Inhalt der QuelleKermarec, J., J. Desclaux und F. Martignac. „Mesures de contraintes en écoulement cavitant dans les pales de l'inducteur oxygène du moteur fusée Vulcain“. La Houille Blanche, Nr. 7-8 (November 1988): 611–18. http://dx.doi.org/10.1051/lhb/1988059.
Der volle Inhalt der QuelleYao, Xiaoquan, Robin Skinner, Steven McFaull und Wendy Thompson. „Hospitalisations pour blessure au Canada en 2018-2019“. Promotion de la santé et prévention des maladies chroniques au Canada 40, Nr. 9 (September 2020): 311–18. http://dx.doi.org/10.24095/hpcdp.40.9.03f.
Der volle Inhalt der Quelle„Brûlures causées par des moteurs de modèles réduits de fusées: des règle-ments plus stricts s'iimposent“. Journal of Emergency Medicine 12, Nr. 3 (Mai 1994): 432. http://dx.doi.org/10.1016/0736-4679(94)90325-5.
Der volle Inhalt der QuelleDissertationen zum Thema "Moteurs fusée"
Lefrançois, Emmanuel. „Modèle numérique de couplage fluide-structure avec application aux moteurs fusée“. Rouen, 1998. http://www.theses.fr/1998ROUES061.
Der volle Inhalt der QuelleIannetti, Alessandra. „Méthodes de diagnostic pour les moteurs de fusée à ergols liquides“. Thesis, Université Paris-Saclay (ComUE), 2016. http://www.theses.fr/2016SACLS243.
Der volle Inhalt der QuelleThe main objective of this work is to demonstrate and analyze the potential benefits of advanced real time algorithms for rocket engines monitoring and diagnosis. In the last two decades in Europe many research efforts have been devoted to the development of specific diagnostic technics such as neural networks, vibration analysis or parameter identification but few results are available concerning algorithms comparison and diagnosis performances analysis.Another major objective of this work has been the improvement of the monitoring system of the Mascotte test bench (ONERA/CNES). This is a cryogenic test facility based in ONERA Palaiseau used to perform analysis of cryogenic combustion and nozzle expansion behavior representative of real rocket engine operations.The first step of the work was the selection of a critical system of the bench, the water cooling circuit, and then the analysis of the possible model based technics for diagnostic such as parameter identification and Kalman filters.Three new algorithms were developed, after a preliminary validation based on real test data, they were thoroughly analyzed via a functional benchmark with representative failure cases.The last part of the work consisted in the integration of the diagnosis algorithms on the bench computer environment in order to prepare a set-up for a future real time application.A simple closed loop architecture based on the new diagnostic tools has been studied in order to assess the potential of the new methods for future application in the context of intelligent bench control strategies
Schreiber, Didier. „Quelques problèmes de combustion lies à l'allumage dans les moteurs fusée cryotechniques“. Châtenay-Malabry, Ecole centrale de Paris, 1991. http://www.theses.fr/1991ECAP0204.
Der volle Inhalt der QuelleLacas, François. „Modélisation et simulation numérique de la combustion turbulente dans les moteurs fusée cryotechniques“. Châtenay-Malabry, Ecole centrale de Paris, 1989. http://www.theses.fr/1989ECAP0095.
Der volle Inhalt der QuelleBernardi, Jean de. „Aspects expérimentaux et théoriques des instabilités de cavitation dans les turbopompes de moteurs de fusée“. Grenoble INPG, 1996. http://www.theses.fr/1996INPG0217.
Der volle Inhalt der QuelleHydraulic loop instabilities and radial forces generated by partial cavitation on a turbopump inducer were investigated in water with the 4-bladed inducers of the ARIANE 5 VULCAIN engine liquid hydrogen and oxygen turbopumps. With the help of the synchronization of high speed movies with radial load measurements on the inducer shaft and with the dynamic pressures signals, we could establish an identification method and an analysis approach to the instabilities in a turbopump cavitating inducer. Characteristic frequencies of unsteady cavitation phenomenon were identified at various operating points. This analysis clearly demonstrates the evolution of radial loads with cavitation number : (1) constant, (2) rotating and supersynchronous, (3) chaotic, (4) constant. The evolution of radial load is strongly related to cavitation configurations. Instabilities of cavitating 4-bladed inducer have been explained qualitatively and imbalances have been estimated in terms of radial loads and cavity lengths. This study has been completed by a theoretical model of the inducer based on the actuator disk theory in which the cavitating volume appears to be the main parameter. A measuring method of the cavitating volume in the rotary inducer is therefore proposed which could give results with a 90% accuracy
Gioud, Thibault. „Simulation aux grandes échelles de l'atomisation pour moteur-fusée à injection liquide en regime sous-critique“. Electronic Thesis or Diss., Université de Toulouse (2023-....), 2024. http://www.theses.fr/2024TLSEP049.
Der volle Inhalt der QuelleIn recent years, the space launchers market has experienced significant growth, marked by the emergence of increasingly compact satellites and a progressively more affordable production cost, attributable to recent technological advancements. This cost reduction has met the rising demand, with new private entities entering the launcher manufacturing sector. A key strategy to minimize costs lies in the use of methane as a fuel, replacing hydrogen, which incurs significantly higher operating costs (storage, temperature, etc.) despite superior performance.The evolution of numerical models and the increasing computational power have made numerical simulation particularly attractive for predicting and optimizing the performance and lifespan of rocket engines. This PhD thesis focuses on Large Eddy Simulation of rocket engine combustion in sub-critical regimes. Rocket engines can experience multiple thermodynamic conditions, ranging from sub-critical to supercritical regimes. In sub-critical regimes, one or both propellants may exist in a liquid state. The presence of a two-phase mixture (gas + liquid) makes numerical simulation complex due to the strong gradients at the liquid/gas interface. Therefore, developing models able to represent this interface and its dynamics under various thermodynamic conditions is an undergoing research direction.In this thesis, the diffuse multi-fluid interface method, assuming equilibrium of temperature, pressure, velocity, and Gibbs potentials, is used to simulate two-phase flows in rocket engine conditions. This approach aims to address the challenges associated with the complexity of numerical simulations arising from the presence of a two-phase mixture. Additionally, the approach considers surface tension forces, which play a crucial role in atomization phenomena. This method has been evaluated on a reactive configuration similar to a rocket engine (experimental setup investigated at the Technische Universität München (TUM)), yielding highly encouraging results and demonstrating the benefits of simulating the liquid jet compared to a method modeling it with Lagrangian particle injection.Injecting liquid into a gaseous atmosphere leads to atomization phenomena, manifested by a consecutive series of breakups in the streamwise direction. Far from the injection, droplets diameter becomes very small, making the precise resolution of these structures computationally expensive. Additionally, the use of a diffuse interface method does not provide the required accuracy for the complete capture of these atomization phenomena.Therefore, an approach is proposed, involving the simulation of larger structures using an Eulerian approach and modeling the smallest particles with a Lagrangian approach. A secondary atomization model then predicts the characteristics of the final spray. During this thesis, the coupling algorithm providing mass, energy, and momentum transfer between these two formalisms was implemented in a multi-species context. The entire strategy was evaluated on a Jet In Cross Flow (JICF) configuration, showing highly encouraging results, particularly for droplet size distribution.Finally, this coupling strategy was applied to simulate the reactive TUM case. Although the dedicated time did not allow for sufficient convergence time to draw conclusions, initial promising results demonstrate the capability and robustness of this methodology under reactive conditions. Moreover, this methodology provides access to statistical spray data, such as droplet size distributions and velocities
Leboucher, Nicolas. „Stabilité et atomisation d'une nappe annulaire liquide soumise à deux courants gazeux avec effets de swirl : application aux futurs moteurs fusée cryotechniques“. Phd thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aéronautique, 2009. http://tel.archives-ouvertes.fr/tel-00476808.
Der volle Inhalt der QuelleMuller, Mathieu. „Modélisation de la combustion de gouttes d'aluminium dans les conditions d'un moteur fusée à propergol solide“. Thesis, Sorbonne université, 2019. http://www.theses.fr/2019SORUS267.
Der volle Inhalt der QuelleThe purpose of this thesis is to study the aluminum (Al) droplet combustion in solid rocket motor propellant. We need to model this process to evaluate the burning time and the residues length because their characterization in real conditions is very complex. A combustion model of a single droplet with a multiphysical spherical approach has been developed taking into account various phenomena. This model has been validated and used to study gaseous and surface mechanisms. Simulations in controlled atmospheres were made and the results were compared to experimental data. The study of the combustion of two particle classes (primary particle and agglomerate) under conditions typical for the Ariane 5 solid booster was conducted to evaluate the effect of different heterogeneous surface kinetics on the simulated combustion process. After the integration of the reactive surface model in the ONERA code CEDRE, simulations of the combustion using a two-dimensional axisymmetric approach were made to study the impact of the cap on the droplet surface and the convection velocity of oxidizers. By simulating the established combustion of two droplet classes at two pressures (5 and 9 MPa) in different stages of combustion, we evaluated main characteristics of the combustion and we deducted a global burning law. Finally, the heating of the droplet before an established combustion was studied to complete the characterization
Verthier, Brian. „Une étude sur les transferts associés aux écoulements diphasiques de fluides cryogéniques en microgravité : application à la mise en froid de moteurs-fusée“. Thesis, Toulouse, INPT, 2010. http://www.theses.fr/2010INPT0104.
Der volle Inhalt der QuelleThe objective of this thesis is to study the boiling regimes encountered during the transient cooling of a heated tube by an internal fluid flow. The experimental apparatus LORETA was designed for experiments on ground in vertical upward flow and on microgravity during parabolic flights. The effect of flow rate, liquid temperature and level of gravity in different boiling regimes has been clearly shown. A decrease of heat transfer in microgravity is observed, especially during film boiling. Models based on solving equations of two-fluid model allow the prediction for the two levels of gravity. The entire boiling curve could be modeled by modified laws of literature. The use of these laws for cryogenic fluids seems reasonable, given the comparison with some data from the bibliography
Kiyoshi, Shimote Wilson. „Modélisation des phénomènes d'ablation de l'insert d'une tuyère de moteur-fusée à propergol solide. Approche expérimentale et numérique“. Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2016. http://www.theses.fr/2016ESMA0028/document.
Der volle Inhalt der QuelleThe main objective of this study is understand the ablation mechanisms in the presence of a critical environment in pressure and temperature within a solid propellant rocket motor. The well-known parameters, aluminum percentage in the flow, adiabatic flame temperature and the consequent heat flux in front of the geometry of the insert and its thermochemical properties are studied from anumerical and experimental strategy. The ablation phenomenon, which occurs at the nozzle insert during the operation of the solid propellant rocket motor, is th us studied and results of tests of the small and full-scale motors are presented as well as numerically simulated. Indeed, tests carried-out provide results on the conditions of the material of the insert before and after firing tests, do not allow is to provide a complete analysis of the development of the mechanisms involved during the running time of the engines. To introduce these rather complex physical phenomena a strategy of progressive development is followed. Initially, a 1D model treated the heat transfer equations using a multi-block numerical discretization technique. From the 1D method, simple expressions to represent the evolution of the ablation and pyrolysis fronts are defined. These expressions are then used directly on the treatment of axisymmetric problems and confronted with simulations of the scale motor. Finally, the immersed boundary method is applied to tackle coupling between flow and heat transfer on the insert, highlighting the phenomenon of ablation. The numerical simulations reproduce the experimental results and show a robust numerical methodology, corresponding to expectations in what concerns the evaluation of the ablation phenomenon within a solid propellant rocket motor nozzle
Bücher zum Thema "Moteurs fusée"
Panel, North Atlantic Treaty Organization Research and Technology Organization Applied Vehicle Technology. Internal aerodyamics in solid rocket propulsion: L'ae rodynamique interne de la propulsion par moteurs-fuse es a propergois solides. Neuilly-sur-Seine Cedex, France: North Atlantic Treaty Organisation, Research and Technology Organisation, 2004.
Den vollen Inhalt der Quelle findenInternational Symposium on Beamed Energy Propulsion (3rd 2004 Troy, N.Y.). Beamed energy propulsion: Third International Symposium on Beamed Energy Propulsion, Troy, New York, 11-14 October 2004. Herausgegeben von Pakhomov Andrew V, Myrabo Leik und Rensselaer Polytechnic Institute. Melville, N.Y: American Institute of Physics, 2005.
Den vollen Inhalt der Quelle findenInternational Symposium on Beamed Energy Propulsion (3rd 2004 Troy, N.Y.). Beamed energy propulsion: Third International Symposium on Beamed Energy Propulsion, Troy, New York, 11-14 October 2004. Herausgegeben von Pakhomov Andrew V, Myrabo Leik und Rensselaer Polytechnic Institute. Melville, N.Y: American Institute of Physics, 2005.
Den vollen Inhalt der Quelle findenV, Pakhomov Andrew, Myrabo Leik und Rensselaer Polytechnic Institute, Hrsg. Beamed energy propulsion: Third International Symposium on Beamed Energy Propulsion, Troy, New York, 11-14 October 2004. Melville, N.Y: American Institute of Physics, 2005.
Den vollen Inhalt der Quelle findenInternational Symposium on Beamed Energy Propulsion (3rd 2004 Troy, N.Y.). Beamed energy propulsion: Third International Symposium on Beamed Energy Propulsion, Troy, New York, 11-14 October 2004. Herausgegeben von Pakhomov Andrew V, Myrabo Leik und Rensselaer Polytechnic Institute. Melville, N.Y: American Institute of Physics, 2005.
Den vollen Inhalt der Quelle findenRocket propulsion elements - 9. edicion. John Wiley & Sons, 2017.
Den vollen Inhalt der Quelle findenBeamed Energy Propulsion: Third International Symposium on Beamed Energy Propulsion (AIP Conference Proceedings). American Institute of Physics, 2005.
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