Explosive Propelling Device for Testing a Debris Protection of Missiles and Spacecraft in Ground-Based Conditions

摘要

The implementation of ground-based modelling of high-speed interaction between objects when conducting studies of the behaviour of materials and structures under high-intensity exposure to various particles of natural and artificial origin is one of the urgent tasks in the development of spacecrafts nowadays. One of the methods for producing high-speed compact elements (HSCE) for subsequent modelling of meteorite impact is the use of explosive throwing devices in the form of high-explosive anti-tank shell (HEAT) with a combined hemisphere-cylinder lining (HC-lining). The purpose of this study was to carry out calculations and experiments to identify the most effective options for combined HC-facing, providing the formation of metal HSCE of the required mass and velocity. Based on numerical simulation, within the framework of the two-dimensional axisymmetric problem of continuum mechanics, the influence of the radius and thickness of the hemispherical part of the HC-lining on the parameters of the formed HSCE was studied. To increase the velocity of the HSCE, it is proposed to use the hemispherical part of the degressive (decreasing from the top to the base of the hemisphere) thickness. Short-circuit variants with similar HC-linings have been developed, which make possible to form steel compact elements of gram-weightes with speeds in the range of 7.5 ... 10 km / s. Comparative experimental studies were carried out with the determination of the parameters of the HSCE by the X-ray method and with the use of electrical contact pin.