CALCULATION OF THE OPTIMAL DIAMETER OF THE AIR INTAKE OF THE PROPULSION SYSTEM FOR SMALL SPACECRAFT

Abstract

Background. In connection with the increasing interest in the Russian Federation in programs for the development of near-Earth spacecraft, studies have been carried out on the optimal diameter of the grid channel of the air intake of the propulsion system of a small spacecraft operating on outboard air. Materials and methods. It is shown that the use of a class of electrodeless motors based on a helicon discharge is relevant. Experimental graphs of the dependence of the efficiency of the air intake on its diameter are obtained, and the dependences of the mass flow rate of particles m on the diameter of the air intake are also presented. An analysis of the environmental friendliness of the creation of a propulsion system using the Environmental Input-Output method (Models of input-output) is given. Results and conclusions. An assessment of the harmfulness of the impact of the apparatus on the environment during its operation was carried out. A regularity has been established: the flow rate to the engine does not change at a constant ratio of the length of the air intake to the grid pitch, which indicates that the ratio of the grid pitch to the length of the air intake is the main parameter that determines its efficiency. The safety of testing the above-described installation in laboratory conditions is noted. This creates a significant carbon footprint from the use of this equipment.

Keywords

• space vehicles
• propulsion systems
• working fluid
• erosion of elements
• electrodeless engine
• inputoutput models