FIELD: astronautics.
SUBSTANCE: invention relates to aerospace engineering. Method and a device for simulating the process of gasification of residual liquid propellant component in the tanks of the spent stage (SS) of the carrier rocket based on the introduction into the experimental modeling installation (EMI) of the coolant, provision of interaction conditions in the contact area of the coolant with the surface of the liquid gasified component of the rocket fuel, performing temperature measurements, measuring pressure in various points of the EMI, discharge of the vapor-gas mixture (VGM) into the vacuum chamber through the drainage line (DL) and the drainage electropneumatic valve (DEPV), the coolant supply to the EMI together with the pressurizing gas to ensure the specified parameters of the partial pressure of the liquid vapor corresponding to the specified second mass of evaporation of the liquid at a given initial pressurizing, and the total pressure corresponds to the beginning of the VGM discharge into the vacuum chamber, the VGM discharge from the EMI via the DL and the DEPV to the vacuum chamber at different time intervals corresponding to different intervals of the operation of the nozzles of the gas-jet orientation and stabilization system of the SS, and determining the range of the coolant parameters, the temperature of the DL, the DEPV, the duration of the time intervals for the VGM discharge, at which condensate appears on the inner surface of the DL, DEPV and its crystallization, the implementation of an additional supply of heat to the DL, the DEPV, the minimum value of which is determined from the condition of preventing the crystallization of liquid vapors in the DL and the DEPV. Device for implementing the method includes the EMI, the DL, the DEPV, a vacuum chamber, a gas analyzer, a condensate appearance and crystallization detection equipment, an electric heater for the DL and the DEPV, in addition, the EMI, the DL and the DEPV are made from a material corresponding to the real design of the tested fuel tank of the carrier rocket.
EFFECT: invention provides the ability to simulate the gasification process, the appearance of condensate and its crystallization in the convective process of supplying the coolant to the tank with fuel residues.
2 cl, 1 dwg
