The increase of the number of space debris, particularly in LEO, has become a menace for space missions, and Space Agencies such as CNES (French Space Agency) are worried about this phenomenon. Because high pressure vessels are critical components onboard satellites, it is important to know their behaviour under hypervelocity impact induced by space debris. The aim of the study supported by CNES is to establish the different possible regimes (penetration, rupture, explosion, fragmentation) of the tank as a function of the critical parameters. The pressure vessel considered for this study is an over-wrapped carbon fibre on a titanium liner. The gas (xenon or helium) is stored under high pressure (15 or 31 MPa). The menace is characterised by an aluminium sphere, from 0.1 to 5 mm in diameter, and with a 5 up to 20 km·s{sup}(-1) velocity. Our theoretical approach is a 2D and 3D simulation using the SPH (Smooth Particle Hydrodynamic) technique coupling the gas and the tank. The mechanical part of the code has been calibrated on experimental results available in the literature. Our model allows exploring a wide range of parameters which are not accessible to ground experimental simulations. We have identified three main potential causes for a possible tank explosion: (1) the growth of a shock wave in the gas; (2) the effect of the compressive waves in the gas on the composite and of the direct high amplitude mechanical waves within the composite; (3) the degradation of the back wall by the flying debris which can then rupture under the residual solicitation by the gas. A larger gas pressure, a smaller tank and replacing helium by xenon makes the scenarios (1) and (2) more dangerous. The scenario (3) appears to be also important to consider. Our results will be extended and validated by direct comparison with experimental tests on pressure vessels.
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