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This paper discusses the capabilities of the ABLAT software which has been developed by ERC and Dornier for the European Space Agency. The software provides an ablation modelling capability for the ESATAN thermal analyser and consists of two sections: i. A stand-alone preprocessor allowing specification of the ablation model. This has both an X11/OSF Motif and a command line interface. ii. An integrated solver capability within the ESATAN system, allowing transient analysis of an ablating surface in conjunction with a standard thermal model. After a brief overview of the major aims of the development, the software is discussed from two main points of view, the user interface facilities (how the user defines the model to the system), and the calculation facilities (what can be calculated, and how are these calculations performed).

The ALPHA JET Training System as a single aircraft concept consists of the training management system and Media for the following academics simulators aircraft It meets or exceeds all requirements for timely replacement of obsolete training system components effective and efficient management in the training of individual pilots optimum employment of all components of the training system. It significantly lowers pilot training costs and personnel support requirements through the use of computer assisted instruction and procedure devices the use of training management system a modern high performance training aircraft and latest state of the art simulators.

As a consequence of the continuously increasing complexity of design, development and qualification of modern spacecraft subsystems, computer aided tools become increasingly important for solving the various engineering tasks in these fields. In the framework of development tasks for satellites and space stations, e.g. ERS-I/II, ROSAT, CLUSTER, SOHO, COLUMBUS-ECLSS, and HERMES a software environment has been developed at Dornier GmbH in recent years, which allows thermal analysis, thermal control and space environment control for system simulation as well as for detained component level simulation, monitoring and testdata evaluation. COSITHERM is a modular software package for the prediction of thermal radiation effects. SIMTAS can be used for detailed analysis of single system components as well as for the prediction of system response of arbitrarily connect components.

This paper describes the development, manufacturing and testing of an advanced heat pipe profile possessing separated arteries and small radial grooves for condensate transportation. The objective of the development was to design a heat pipe with improved heat transport capability limited by an outer cross-section of 15 mm square. The concept of the new heat pipe is based on an aluminium extrusion profile with rectangular outer shape. The central vapour core of 9.2 mm diameter is connected via small connection slots with four individual liquid channels located in the corner areas of the profile. So the liquid flow in the four channels is decoupled from vapour flow, both streaming in opposite directions. Decreasing of the pressure drop in the liquid channels and decreasing the entrainment of liquid flow to the vapour flow resulted in improved heat transport capability.

In support of the Columbus ECLSS, a technology development program has been performed on four items: Regenerative CO2 removal Trace Gas Contamination Control Trace Gas Contamination Monitoring Low Noise Variable Speed Fan This paper describes the contents and results of the concluding Subsystem Level Tests and consecutive programme extensions which concentrated on: performance of the Contamination Monitoring Unit noise generation of the Variable Speed Fan lifetime tests of the CO2 removal solid amine closed water loop operation of a solid amine CO2 removal unit

ESABASE/SUNLIGHT is a software tool to calculate illumination, effective illumination, exposure time, incident electromagnetic power, absorbed electromagnetic energy for spacecraft surfaces during planet orbiting missions considering sun and planet irradiation, effects of eclipse and self-shading, multireflections, transmission, pointing and (variable) geometry. Calculation applies a fast Monte Carlo raytracing algorithm and is based on wavelength dependent spectra and material properties. ESABASE/SUNLIGHT is fully integrated in the CAE-frame ESABASE which offers a powerful geometry specification language, orbit generator, pointing facility and advanced libraries as well as gateway, pre-, postprocessing and display tools with the benefits of standardisation and exchange to other analysis tools.

This paper presents some of the important aspects of the development work carried out recently in the Hermes ECLSS (since Ref. 1). For various constituent hardware items of the ECLSS, the paper describes and explains the technical constraints which are at the origin of the development work, discusses the design concepts which have been identified and investigated to fulfill the constraints, and presents the technical solution which has been selected. For some hardware items (e.g. cabin fan, toilet assembly), for which the initial design selection has been supported by breadboard tests, the paper presents the rationale behind such tests and the major test results obtained. The consequences derived from the test experience for the further development work are explained.

Manned space laboratories like the US Space Station Freedom or the european COLUMBUS APM are equipped with so-called racks for subsystem and payload accommodation. An important resource is air for cooling the unit internal heat sources, the avionics air. Each unit inside the rack must be supplied with sufficient amount of air to cool down the unit to the allowable maximum temperature. In the course of the COLUMBUS ECLSS project, a thermohydraulic mathematical model (THMM) of a representative COLUMBUS rack was developed to analyse and optimise the distribution of avionics air inside this rack. A sensitivity and accuracy study was performed to determine the accuracy range of the calculated avionics air flow rate distribution to the units. These calculations were then compared to measurement results gained in a rack airflow distribution test, which was performed with an equipped COLUMBUS subsystem rack to show the pressure distribution inside the rack.