An ESA study is starting considering the system aspects of the use of the multi-core for our applications, and this study will define the final technical solutions. However, the trend seems to be towards the use of a hypervisor. If this is confirmed, there could be a convergence between the various hypervisors used for partitioning, for security and for multi-core. An environment for hypervisor could therefore be reused, which is the focus of the the proposed activity.

The Integrated Modular Avionics for Space (IMA-SP) concept introduces the role of System Architect to the spacecraft avionics domain. The System Architect has the key responsibility for negotiating the avionics resource allocation with the hosted application suppliers and then performing a system-level verification to ensure that the configured system is capable to host the applications and meet the system requirements. The allocation of the platform resources is an iterative process between the Architect and the application suppliers.

The activity will focus on two specific modes which are under review for general or legal purposes: safe mode and deorbitation mode.In order to maximize commonality and reuse across all future platforms, a generic safe mode appears an interesting option combining magnetic actuators and the propulsion system. It performs similarly on any orbit with any spacecraft, making the most of the advantages of both technologies.

This study proposal addresses the issue of compatibility between the CCSDS SMC and SOIS standards and the ECSS PUS standard. Each of these standards bring an added value and represent a useful reference for the definition and implementation of Monitoring and Control (MC) kernels on ground. However, they are unfortunately defined independently from each other and show significant overlaps (especially between SMC and PUS) and/or contradictions.

•Burn recession tests of ablators using oxy-acetylene flame and plasma-jet show that the ReWiG sensor is able to provide a distinguishable signal as the recession proceeds
•The use of a grid/foil combination can offer reliable temperature compensation enabling better definition of the recession signal

The activity shall review current estimation techniques employed in space industry and make a analysis in the face of improvement, new demands and functionalities related to space applications in the view of high accuracy control demands ranging from science missions, exploration and vision based control to space transportation guidance navigation and control applications. The study shall execute the robust and high performance estimation and filtering techniques for accurate state reconstruction for hybrid integrated navigation purposes including vision based hybridisation.

Missions require more and more stringent stability performances, for which the performances of the reaction wheels become drivers.A recurrent issue is the wheel friction instability, resulting in fast variations of the wheel response, which adversely affects the pointing stability.This activity will:- examine the little understood effects of the lubrication system and environment on the stability and consistency of the delivered torque- characterise the impact of wheel instabilities on the pointing and stability- investigate solutions (at AOCS level, at wheel level, at system level, at HW o

Address the open points raised in COrDeT2: i) open points in final report, ii) integrate OBCP building block interface specification from parallel GSTP5 element 2 activities, iii) define unique meta-model of component model and add semantic description, iv) incorporate feedback from OBSW reference architecture consolidation activities (GSTP5 element 2 activities).Harmonize the OBSW reference architecture specification with the outcomes from IMA-SP activity by implementing the recommendations from SISTORA activity.

Gratings are frequently used in optical instruments, e.g. spectrometers. Various production methods are available like etching using a hologram and ruling on high precision latches.

The SpaceWire physical layer as defined in ECSS-E-50-12A is a point to point cable connection. This is most suitable for the data link between equipment's. With the success of SpaceWire it is also used more and more to connect different boards within the same box. For this type of use typically a connection via the backplane would be used. So far there is no standardised solution for SpaceWire connections over the backplane defined. In this activity the different possible architectures of active and passive backplanes shall be traded-off.