The feasibility study of an active removal mission of multiple large abandoned objects from Low Earth Orbit region is presented. A chaser spacecraft, powered by a hybrid rocket engine, achieves contact with two Cosmos-3M second stages and provides for their de-orbiting by means of a hybrid propulsion module. Critical mission aspects and related technologies are investigated, such as an innovative electro-adhesive system for target capture, mechanical systems for the hard docking before the disposal. Deorbiting trajectory simulations and preliminary sizing and mass budget of chaser spacecraft and hybrid rocket engines were performed.
Multi-active removal of large abandoned rocket bodies by hybrid propulsion module / P., Tadini; U., Tancredi; Grassi, Michele; L., Anselmo; C., Pardini; F., Branz; A., Francesconi; F., Maggi; M., Lavagna; L. T., De Luca; N., Viola; S., Chiesa; V., Trushlyakov; T., Shimada. - (2013), pp. 188-189. (Intervento presentato al convegno ICFD 2013 - Tenth International Conference on Flow Dynamics tenutosi a Sendai, Japan nel 25-27 November 2013).
Multi-active removal of large abandoned rocket bodies by hybrid propulsion module
GRASSI, MICHELE;
2013
Abstract
The feasibility study of an active removal mission of multiple large abandoned objects from Low Earth Orbit region is presented. A chaser spacecraft, powered by a hybrid rocket engine, achieves contact with two Cosmos-3M second stages and provides for their de-orbiting by means of a hybrid propulsion module. Critical mission aspects and related technologies are investigated, such as an innovative electro-adhesive system for target capture, mechanical systems for the hard docking before the disposal. Deorbiting trajectory simulations and preliminary sizing and mass budget of chaser spacecraft and hybrid rocket engines were performed.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
