In order to pro-actively counter the risk of a non-availability of a 240N thru

Iodine has been recognised as interesting propellant for electric propulsion applications since it allows to significantly reduce the cost and complexity of the propulsion system due to the fact that it is solid at room temperature and sublimates directly to gas at moderate temperatures. While iodine propellant has many advantages, there are also some challenges to overcome due to the fact that iodine is highly reactive.

The increased need for accurate knowledge of amplitude and phase antenna patterns for a very broad frequency range and over a large thermal range is a reality for a multitude of space applications. Among them are the high accuracy Radio Science Experiments for ranging and radio occultation that require accurate knowledge of the phase information. This enable the characterisation of the thermo-elastic effects provided that test techniques are developed in a temperature range down to -140C.

In order to support the European leadership in the field of Star Trackers, the development of a new detector supporting the high-end is required.Rather than engaging the design of a new image sensor, it is considered more efficient to characterize existing developments, either to engage directly a qualification or to identify needs in terms of delta functionality or performance.State-of-the-art Star Trackers are using today 1 mega-pixel detectors. A detector with 16 mega-pixels will aim at reducing by a factor 4 the angular resolution of one pixel.

Achievements and status: ​

Achievements and status: ​

• TRL = 6 achieved for three different type of hoses (for different ranges of movement)​
• Pressure drop preliminary measured​
• Resistive torque characterized in various conditions (temperatures, pressure)​
• Tested in relevant mechanical environment (vibration): test permits to highlight the need of some system level design improvements (i.e. retaining system for the hoses during launch) ​

Benefits: ​

Based on the heat release of dedicated electronic boxes, a complete design, manufacturing and integration cycle will be performed for two different mass-efficient heat accumulators using phase change material avoiding overheat of specific electronic boxes on-board a launch vehicle.This includes also dedicated thermal, vibrational and structural analysis to withstand the complete flight mission with mounted electronic boxes.