METHOD FOR DISPOSING OF RADIOACTIVE WASTE IN OUTER SPACE AND SPACECRAFT FOR IMPLEMENTING SAME

摘要

The invention relates to the field of space engineering, specifically to methods for disposing of radioactive waste in space and to spacecrafts with an electric propulsion engine for the transport of radioactive waste (RAW) to disposal orbits in outer space. The problem is significantly increasing the mass of transported radioactive waste by increasing the thrust of the electric propulsion engine and decreasing the mass of the propellant thereof. The technical result is achieved in that the heat transfer agent of a first circuit and the propellant are the same, part of the heat transfer agent of the first circuit being used as the propellant, and the flow rate of the heat transfer agent being determined by a mathematical formula; ;wherein a is a koefficient depending on heat capacity of the heat transfer agent, terms of heat removal (flow regime, heat transfer coefficient), Q₀^RAW is an initial heat of radioactive waste, t is operation time of the electric propulsion engine, T_1/2 is a half-life period of radioactive waste isotopes. The first circuit of the heat transfer agent is equipped with a thermal throttle and an electric valve and branches out at the outlet from the container, wherein the first outlet of the branching is connected to the inlet of a heat reservoir, the outlet of the first circuit is connected to the inlet of the electric valve, the outlet of the electric valve is connected to the inlet of the thermal throttle, and the outlet of the thermal throttle is connected to the outlet of a vessel for the electric propulsion engine propellant.