Reaction wheels exhibit dominant magnetic field emissions that shall be reduced to allow the reaction wheel use on magnetically susceptible missions without negative impact on scientific objectives. Conventional reaction wheels use brushless DC motors with relatively high magnetic flux densities in large air gaps without any dedicated compensation or 'magnetic balancing' of the motor magnets. The motor external magnetic field together with contributions from further components, (ball bearings), combine to a significant magnetic dipole moment.

The next generation of GNSS is expected to be more demanding in terms of RF power transmission in order to guarantee a proper availability and quality of the service, hence, enhanced interference immunity and indoor positioning could be achieved.The HPA currently under development for this application are targeting power levels in excess of 300 W.

Iodine as a propellant is considered a valid alternative to xenon for electric propulsion application, in particular on Hall effect thrusters. Several advantages when using iodine as opposed to xenon can be enumerated. Iodine and xenon atomic mass and first ionization energy are very close and thruster performances, in terms of thrust density, thrust efficiency and specific impulse, have proved to be almost the same. Iodine is solid at ambient temperature and pressure, with a density about four times the density of xenon stored at 200 bar of pressure and ambient temperature.

Future X-ray astronomy missions have identified a need for large area, optical filters with very high transmission in the soft X-ray portion of the electromagnetic spectrum.

Earth Orientation Parameters (EOP) are of fundamental importance for all ESA missions. Currently, the EOPs are obtained from an external entity the Earth Orientation and Reference Service (IERS). The goal of this activity is the development of ESA capability for the estimation and prediction of Earth Orientation Parameter in order to become independent of external services. Several aspects related to this subject topic need to be investigated and further developed.

Spacecraft electrostatic charging in hot plasma environments leads to the risk of damaging electrostatic discharges and is linked to many serious incidents of anomalies and damage to spacecraft electronics. In principle, the charge can be removed by active emitters (guns) but this adds to the system complexity and cost. A GSP study used theory and simulation to explore the possibility of a passive system in which naturally occurring potential differences on the spacecraft can be used to drive an electron emitter, which safely lowers the spacecraft potential.

Space mixed-signal radiation tolerant front-end performance for sensor and control for instrumentation and AOCS are limited by the supply of disparate analogue and mixed-signal components.

The d.deorbit CDF study identified the robotic gripper mechanism as a key area of technology development. The gripper, which is attached to the tip of the robotic arm, plays a important role in the satellite capture operation as it provides the mechanical and structural interface between the servicer/chaser vehicle and the target satellite during the critical capture and stabilisation operations. Due to the potentially unknown state of the target satellite, the capture operation must be able to handle both cooperative satellites (i.e.