Numerical modeling has been conducted with the commercial code AUTODYN 2D, using the Lagrange and Smooth Particle Hydrodynamics (SPH) processors. The numerical results are compared and discussed with the corresponding experimental results from the standpoint of assessing the protection of satellites against M/OD hypervelocity impacts. The material models used in the numerical simulation are also discussed, as well as a wide range of impact velocities, including shock-induced vaporization. The projectiles used to simulate M/OD consist of 100 μm to 1 mm diameter alumina with impact velocities of 2–15 km/s.

In order to assess the structural integrity of unmanned spacecraft subjected to the threat of hypervelocity impact by space debris, the numerical method was proposed mainly from the standpoint of material modeling suitable for extremely severe physical conditions such as high pressure, high temperature, high strain, and high strain rate, sometimes accompanied by shock-induced vaporization.

The numerical results adopting these material models were compared with the corresponding hypervelocity impact tests by using the two-stage light-gas gun at ISAS/JAXA. Although examples of the impacts on the aluminum honeycomb can be shown, it has been demonstrated that the numerical analysis can effectively simulate the overall corresponding experimental results.

We show the response of an aluminum honeycomb as derived from analysis of hypervelocity impact at 2 km/s to 15 km/s using the Lagrange and SPH processors. We also verified that the ballistic limit curve of an aluminum honeycomb panel is shown as a downward line using both processors, which is unlike the up and down ballistic limit curve of a Whipple shield.

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