ЭКСПЕРИМЕНТАЛЬНОЕ ПОДТВЕРЖДЕНИЕ РАБОТОСПОСОБНОСТИ КАПИЛЛЯРНОГО ЗАБОРНОГО УСТРОЙСТВА (СЕТЧАТОГО РАЗДЕЛИТЕЛЯ) ПРИ ПРОГРАММНОМ РАЗВОРОТЕ

One of the problems of providing a group launch of spacecraft is to ensure the re-launch of the propulsion engine for the transition to another orbit, after the separation of the first vehicle. When the spacecraft is separated into a stage, an acceleration is applied directed toward the bottom of the tank and leading to an outflow of the fuel component from the mesh separator. This, in turn, leads to the denudation of the mesh separator and the penetration of gas under it, which can lead to a breakdown of the launch of the engine. In viewof the complexity of the hydrodynamic processes taking place in the tanks, experimental confirmation of the mesh separators chosen during the design is required.In this paper, we describe the methods for determining the model conditions (the choice of the scale of the experimental design, the type of the model fluid, the magnitude of the accelerations, etc.), a description of the stand designed specifically for the test data, and the results of the experimental confirmation of the capillary sampling device performance in the separation of the spacecraft. The results of the performed works confirm the correctness of the decisions made in the development of capillary sampling devices.