Search Results

For all future space transportation systems the capability for multiple use plays a major role. This fact comprises ascent, on-orbit and re-entry, maintenance and inspection on ground for all major components and subsystems. Beginning with HERMES Europe made great efforts in the re-entry technology development also. This affects e.g. guidance and navigation, aero-thermodynamic and Thermal Protection Systems (TPS). The US Advanced Flexible Reusable Insulation (AFRSI) as TPS was developed for the Space Shuttle and successfully flown since the beginning of its missions. In Europe, there were similar developments performed within the HERMES program. Depending on the temperature levels on the vehicle and the aero-dynamical or mechanical loads different TPS are used.

The backbone of the Attached Pressurized Module (APM) is the water cooling loop, which contributes to an optimized payload operation. Dedicated design means are proposed to allow an efficient use of this resource. In case of a Thermal Control System (TCS) failure a controlled run-down of individual payloads is possible to avoid critical situations like overheating due to heat soak back from a furnace. The TCS is flexible enough to allow short payload power peaks thus optimizing the resource allocation without violation of the thermal requirements regarding the temperature limits. The APM will be verified against generic thermal and environmental control requirements. The test and analytical verification effort on payload side is dependant whether the payload is a facility integrated in an International Standard Payload Rack (ISPR) or a smaller entity like a drawer as subset of a facility or a self-standing experiment.

The paper describes the thermal control and life support design and related system aspects of the COLUMBUS Free-Flyer. The specific requirements for the FreeFlyer thermal control and environmental control and life support are mainly driven by the particular performance to be provided in single mission phases by the overall operational life requirement of 30 years for the whole Free-Flyer flight configuration and the possibility for repair and maintenance in orbit by the different operating modes of the Resource Module as autonomous or composite configuration by the complex and partially different interfaces with HERMES and the Space Station Freedom. During the Resource Module exchange at the Space Station Freedom the Pressurized Module is deactivated and thermally controlled by a heater system supplied with power by the space station. After attachment of the new Resource Module the internal servicing will be performed.