The Active Thermal Control Subsystem of a newly designed spaceplane suggests the adoption of special fluid loop architecture and control, specific high technology equipment, dedicated ground test facilities and new concepts in schedule management.
The design drivers for the Active Thermal Control system imply the need for a high degree of flexibility, in order to accomodate the large range of heat loads with a continuously changing operational and environment conditions.
Fluid loop systems represent a viable concept in overcoming these problems. They offer the possibility of collection, transport and dissipation of significant amounts of thermal power enabling adequate means of close temperature control. Experience gained in the European aerospace programmes (Spacelab, Eureca, Columbus, Hermes, and Technological Demonstrator programmes) at Aeritalia provides a sound basis for implementing the analysis and design activities necessary to identify viable technical solutions, manufacture critical equipment and perform verification tests, at both component and subsystem level. In this context a clear methodology for the design of the Active Thermal Control along with design criteria are presented.