Design for Demise is the intentional design of spacecraft hardware such that the spacecraft will completely ablate (demise) upon uncontrolled atmospheric re-entry during post-mission disposal, or even during unexpected re-entry due to critical system failure.Demisability has been identified as needed to reduce the risk of human causality and damage to property on Earth, and guarantee safety from satellite and spacecraft atmospheric re-entries.

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There is an increasing need for ever smaller pulse-tube coolers. These coolers have the characteristics necessary for space applications because the absence of moving parts in the cold finger makes them extremely reliable and any induced vibrations are typically smaller and easier to control.

But these types of cooler are less efficient and have a lower power density. Typically, this is resolved by increasing their drive frequency, to reduce amplitudes and displacements, which means that the coolers are smaller

Experience shows that shock specifications for release systems provided by suppliers rely on different test methods and test setups. As a consequence the specified SRS are not comparable and compliance statements given in proposal phases can still impose some risk. The selection of the release system thus strongly depends on individual experience and heritage.The objective is the definition of a standardised test setup for release systems, are the generation of a shock test database which includes most used releases systems (pyro and non-pyro).

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Within this study, it is proposed to perform a system study for a concept for manufacturing hardware where time is not the driving parameter and initial available resources are very limited. In the frame of exploration missions, complex trade-off will have to be made to find out the best balance between the ISRU (In Situ Resources Utilisation) and the resources brought from Earth. The first ones will have to be further processed to become useful while the cost of the later will be tremendous.