Speaker
Description
Design for Demise has become an increasingly important subject over the last years. Primarily to achieve compliant uncontrolled re-entries but with the updated regulations potentially also for future controlled re-entries.
Several recent projects have shown that one important method to improve the demise behaviour can be an early fragmentation of the spacecraft structure or an active separation of units from the structure. By separating/opening items, inner parts can be exposed earlier to the aerothermal heat fluxes increasing the overall demised mass.
This presentation will show the current status of the Airbus development of generic separation technologies derived from the successful implementation of separation brackets for the Sentinel 1 radar antenna.
Besides the current maturity and development roadmap, an insight into the expected performance, the design, modelling and validation methods for implementation and the flexible inclusion in an overall satellite development and AIT flow will be presented.
Next to the advantages of the technology, potential limitations and compatibility with other Design for Demise/Containment strategies will also be elaborated.
