Besides the standard application of ion thrusters for the Near-Earth space exploration and cruise missions, there is a problem of removing man-made space debris objects from the Near-Earth space by a weakly diverging ion beam, i.e. by a contactless impact. However, for stable operation of the ion-extraction system of both the ion thruster and the ion source, it is necessary to predict and take into account the thermal deformations of electrodes of the ion-extraction system. The increase in the number of man-made space debris objects in the Near-Earth space hinders the long-term sustainable development of space activities. Many different methods have been proposed for removing large objects into disposal orbits or into low orbits for their further destruction in the dense layers of the Earths atmosphere. To remove space debris, a service spacecraft can be used, which could approach the space debris to be removed and tow it to the disposal region by a contactless impact. A radio-frequency ion source forming a weakly diverging ion beam, under the influence of which the space debris objects would move in the direction of the disposal orbit, can be used as an onboard device designed for this purpose. Such radio-frequency ion source is in fact a radio-frequency ion thruster. The development of thermal and thermomechanical models of ion thruster and ion source taking into account the requirements for the reliable operation and integration of ion source with service spacecraft systems to provide contactless space debris transportation in space and integrations of ion thruster with onboard systems to provide attitude control or ensure cruise missions is one of the problematic scientific and technical issues. In terms of design, the ion-extraction system of ion thruster and ion source is the most complex unit. When developing the ion-extraction system design, it is necessary to take into account the peculiarities of electrode operation.
Mogulkin et al. (Wed,) studied this question.