FLIGHT MECHANICS OF THE RE-ENTRY FROM MOON AND MARS HUMAN MISSIONS

摘要

The return from exploration missions of either manned or cargo vehicles presents several challenges to the design of the entry vehicle associated to the high energy to be dissipated during the atmospheric flight compared to a Low Eart Orbit (LEO) return. Advanced methods and tools have been developed in the flight mechanics area to provide the mission characterisation required to support the system sizing activities, architecture trade-offs and candidate vehicles selection criteria. This paper presents the results of the entry analyses for two candidate vehicles: a biconic blunt body without active control surfaces and a Lifting body derived from the Klipper unwinged shape. The feasibility of both vehicles to perform direct entry has been evaluated. The analysis starts with the inspection of the aerodynamic performances of the vehicles, followed by the mission scenario characterisation and ends with the identification of technological needs for the Guidance, Navigation and Control (GNC) subsystem. Stability Augmentation Systems based on aerodynamic modifications for the low speed flight have been assessed for both concepts.