Abstract
In order to determine directions for improving the energy characteristics of spacecraft propulsion systems due to the combined of cold gas and electric thrusters, the authors analyzed the design schemes and energy characteristics of cold gas thruster used on spacecraft. Propellant sharing in a combined propulsion system, as well as a single engine design combining cold gas and electric thrusters, is a promising technology. At the same time, it is emphasized that at the current time the main tasks in the development of combined propulsion systems are to ensure the compatibility of the operation of an electric rocket engine with the propulsion of a cold gas thruster
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