No abstract

In the first mission of the ISS supply ship ATV (Automated Transfer Vehicle) an unexpected power request by the thermal control system was detected, when some thermal blankets were partially detached from the structure. An investigation was carried out, followed by a complete review of the MLI detail design relevant to the venting phenomenon. The process was completed with the qualification of an enhanced MLI design, suitable to resist to all the environmental loads and to provide future ATV modules with the capability to withstand any mission condition with respect to thermal and venting issues. This paper is focused on the thermal development and qualification campaign and on the relevant lessons learnt. NomenclatureATV = Automated Transfer Vehicle CDR = Critical Design Review DAK = Double Aluminized Kapton EADS = European Aeronautic Defence and Space company ICC = Integrated Cargo Carrier JK = Johannes Kepler JV = Jules Verne MDPS = Micrometeoroid and orbital Debris Protection System MPLM = Multi-Purpose Logistics Module MLI = Multi-Layer Insulation OTMM = Overall Thermal Mathematical Model QR = Qualification Review RCF = ReClosable Fastener ST = Space Transportation TAS-I = Thales Alenia Space -Italia