Experimental studies of thermal and aerodynamic impacts on polymer composite material

The experimental results on thermal destruction processes during pyrolysis and the degree of fragmentation caused by pulsed aerodynamic impact on a demonstration sample (DS) simulating a separable structural element of the Soyuz-2 launch vehicle at the launch site have been obtained. A polymer based on aramid fibers and epoxy binder is used as the structural material of the DS. The process of pyrolysis and subsequent thermal destruction occur due to heating the DS with an electric heater. A pulsed aerodynamic impact takes place in a vacuum chamber due to a gas-dynamic blow of compressed air with an assessment of the fragmentation degree. An experimental program and a corresponding test rig with the metrological support have been developed. Based on the obtained results, a further direction of research on thermal destruction and aerodynamic fragmentation of DS has been mapped out.