The attenuation mechanism of shock waves of arbitrary strength propagating in air has been reasonably well understood. On the other hand, very little is known about the precise mechanism of shock wave attenuation and energy dissipation in liquids. The equation of state for shock propagation in water is empirical in nature and considerable differences exist with reference to the exact value of various constants even in the cast of Tait’ s equation of state, which is popularly used by researchers to describe the shock wave propagating through water. In recent times, considerable attention is being focused by researchers on shock wave attenuation and associated features in liquid medium mainly in the backdrop of development of many innovative industrial applications of shock waves. The present study focuses on generating reliable experimental data on shock wave attenuation in liquids of different viscosity. Experiments have been performed in a conventional vertical shock tube and a modified diaphragmless shock tube to understand how shock wave of requisite strength attenuates in liquids. A new vertical shock tube was designed, fabricated and successfully tested in the laboratory as a part of this study. In this new facility shock loading experiments with liquids or any complex fluid medium can be carried out. In the present study five liquids (Water, Castor Oil, Sodium Chloride (10%NaCl aqueous solution), Kerosene and Glycerin) have been subjected to shock wave loading. Exhaustive static pressure measurements in the liquid medium have been carried out to understand the attenuation characteristics of shock waves. The validity of Taits equation state has been experimentally verified for water. Based on the experimental results modified Taits equation of state has been obtained for castor oil, sodium chloride, kerosene and glycerin. Illustrative theoretical study is also carried out to complement the experiments.

Unsteady shock wave propagation through ducts has many applications, ranging from blast wave shelter design to advanced high-speed propulsion systems. The research objective of this study was improved fundamental understanding of the transient flow structures during unsteady shock wave propagation through rectangular ducts with varying cross-sectional area. This research focused on the fluid dynamics of the unsteady shock-induced flow fields, with an emphasis placed on understanding and characterizing the mechanisms behind flow compression (wave structures), flow induction (via shock waves), and enhanced mixing (via shock-induced viscous shear layers). A theoretical and numerical (CFD) parametric study was performed, in which the effects of these parameters on the unsteady flow fields were examined: incident shock strength, area ratio, and viscous mode (inviscid, laminar, and turbulent). Two geometries were considered: the backward-facing step (BFS) geometry, which provided a benchmark and conceptual framework, and the splitter plate (SP) geometry, which was a canonical representation of the engine flow path. The theoretical analysis was inviscid, quasi-1D and quasi-steady; and the computational analysis was fully 2D, time-accurate, and viscous. The theory provided the wave patterns and primary wave strengths for the BFS geometry, and the simulations verified the wave patterns and quantified the effects of geometry and viscosity. It was shown that the theoretical wave patterns on the BFS geometry can be used to systematically analyze the transient, 2D, viscous flows on the SP geometry. This work also highlighted the importance and the role of oscillating shock and expansion waves in the development of these unsteady flows. The potential for both upstream and downstream flow induction was addressed. Positive upstream flow induction was not found in this study due to the persistent formation of an upstream-moving shock wave. Enhanced mixing was addressed by examining the evolution of the unsteady shear layer, its instability, and their effects on the flow field. The instability always appeared after the reflected shock interaction, and was exacerbated in the laminar cases and damped out in the turbulent cases. This research provided new understanding of the long-term evolution of these confined flows. Lastly, the turbulent work is one of the few turbulent studies on these flows.

Le schéma d'allumage par choc représente une alternative aux schémas d'allumage classiques en Fusion par Confinement Inertiel. Sa singularité repose sur la relaxation des contraintes sur la phase de compression et l'atteinte des conditions d'allumage par l'envoi d'une impulsion laser brève (~500 ps) et très puissante (~300 TW) sur le combustible en fin d'implosion.Au cours de ce travail de thèse, il a été établi que ce procédé induit une configuration non-isobare du combustible au moment de l'allumage, modifiant ainsi les critères d'inflammation du Deutérium-Tritium (DT) par rapport aux schémas conventionnels d'allumage. Un modèle de gain pour la combustion est ensuite développé et des courbes de gain pour l'allumage par choc sont alors obtenues puis validées numériquement. La modélisation hydrodynamique présentée a démontré qu'il est ainsi possible d'obtenir de hauts gains à plus faibles énergies laser que l'allumage conventionnel du fait de la haute pression du point chaud au moment de l'allumage résultante de la propagation du choc d'allumage.Le code d'hydrodynamique radiative CHIC du CELIA a été utilisé afin de développer des dépendances paramétriques définissant les conditions optimales en termes de paramètres de dimensionnement de cibles pour l'atteinte des conditions d'ignition. Ces études numériques ont mis en lumière le potentiel du procédé d'allumage par choc en termes d'économie d'énergie laser, de hauts gains mais aussi de marges de sécurité et de robustesse pour l'allumage. Enfin, les résultats des premières campagnes expérimentales d'allumage par choc en symétrie sphérique effectuées sur l'installation laser OMEGA (NY, USA) sont présentés. Une interprétation des résultats est proposée à partir de simulations hydrodynamiques mono et bidimensionnelles. Différentes pistes sont alors explorées afin d'expliquer les différences observées et des solutions potentielles pour l'amélioration des performances à l'échelle de l'installation OMEGA sont proposées. / The Shock Ignition (SI) scheme is an alternative to classical ignition schemes in Inertial Confinement Fusion. Its singularity relies on the relaxation of constraints during the compression phase and fulfilment of ignition conditions by launching a short and intense laser pulse (~500 ps, ~300 TW) on the preassembled fuel at the end of the implosion.In this thesis, it has been established that the SI process leads to a non-isobaric fuel configuration at the ignition time thus modifying the ignition criteria of Deuterium-Tritium (DT) against the conventional schemes. A gain model has been developed and gain curves have been infered and numerically validated. This hydrodynamical modeling has demonstrated that the SI process allows higher gain and lower ignition energy threshold than conventional ignition due to the high hot spot pressure at ignition time resulting from the ignitor shock propagation.The radiative hydrodynamic CHIC code developed at the CELIA laboratory has been used to determine parametric dependences describing the optimal conditions for target design leading to ignition. These numerical studies have enlightened the potential of SI with regards to saving up laser energy, obtain high gains but also to safety margins and ignition robustness.Finally, the results of the first SI experiments performed in spherical geometry on the OMEGA laser facility (NY, USA) are presented. An interpretation of the experimental data is proposed from mono and bidimensional hydrodynamic simulations. Then, different trails are explored to account for the differences observed between experimental and numerical data and alternative solutions to improve performances are suggested.

The particular study case in this thesis is the shock test performed on the LISA Pathfinder satellite conducted in a laboratory environment on a dedicated test bed: Vega Shock Test Apparatus (VESTA). This test is considered fully representative to study shock levels produced by fairing jettisoning event at Vega Launcher Vehicle, which induces high shock loads towards the satellite. In the frame of this thesis, some transient response analyses have been conducted in MSC Nastran, and a shock simulation tool for the VESTA test configuration has been developed. The simulation tool is based on Nastran Direct Transient Response Analysis solver (SOL 109), and is representative of the upper composite of Vega with the LISA Pathfinder coupled to it. Post-processing routines of transient response signals were conducted in Dynaworks which served to calculate Shock Response Spectra (SRS). The simulation tool is a model of forcing function parameters for transient analysis which adequately correlates with the shock real test data, in order to understand how the effect of shock generated by the launcher is seen in the satellite and its sub-systems. Since available computation resources are limited the parameters for analysis were optimised for computation time, file size, memory capacity,  and model complexity. The forcing function represents a release of the HSS clamp band which is responsible for fairing jettisoning, thus the parameters which were studied are mostly concerning the modelling of this event. Among many investigated, those which visibly improved SRS correlation are radial forcing function shape, implementation of axial impulse, clamp band loading geometry and refined loading scheme. Integration time step duration and analysis duration were also studied and found to improve correlation.  From each analysis, the qualifying shock environment was then derived by linear scaling in proportion of the applied preload, and considering a qualification margin of 3dB. Consecutive tracking of structural responses along shock propagation path exposed gradual changes in responses pattern and revealed an important property that a breathing mode (n = 0) at the base of a conical Adapter translates into an axial input to the spacecraft. The parametrisation itself was based on responses registered at interfaces located in near-field (where the clamp band is located and forcing function is applied) and medium-field with respect to the shock event location. Following shock propagation path, the final step was the analysis of shock responses inside the satellite located in a far-field region, which still revealed a very good correlation of results. Thus, it can be said that parametrisation process was adequate, and the developed shock simulation tool can be qualified. However, due to the nature of shock, the tool cannot fully replace VESTA laboratory test, but can support shock assessment process and preparation to such test. In the last part of the thesis, the implementation of some finite element model improvements is investigated. Majority of the panels in spacecraft interior exhibited shock over-prediction due to finite element model limitation. Equipment units modelled as lump masses rigidly attached with RBE2 elements to the panel surface are a source of such local over-predictions. Thus, some of the units were remodelled and transient responses were reinvestigated. It was found that remodelling with either solid elements, or lump mass connected to RBE3 element and reinforced by RBE2 element, can significantly improve local transient responses. This conclusion is in line with conclusions found in ECSS Shock Handbook.