Description
*On Delegation Request (formerly called Priority 2)
The objective is to develop a thermally conductive structural link using advanced metallic alloys (e.g. metal matrix composites) to produce a highly efficient design with integrated structural and thermal functionality.
Targeted Improvements:
To produce a highly efficient design combining thermal and structural functions (e.g. integrated design combining a highly conductive and optimized support boom with a deployable radiator).
To reduce the complexity as compared to separate structural and thermal hardware.
To reduce mass (up to 50% saving).
To enable highly conductive thermal links witha greatermaximum operating temperature (> 200 deg. C) than heat pipes (maximum 130 deg. C).
To increase thermal stability comparedwith aluminium based solutions (<15 ppm/K).
Description:
Traditionally, the multiple functions such are structural and thermal areindividuallyincorporated into spacecraft design. This can result in inefficiencies in the overall mass, complexity, cost, and Assembly Integration and Test effort needed.
Metal Matrix Composites (MMCs) are materials composed of at least two constituent parts, with at least one of the materials being metal. For example, a common type includes a ceramic material inserted into an aluminium matrix, resultingin a material with the equivalent strength of Titanium, but only 60% of the density. The materials have the significant advantage of being able to tailor the mechanical, electrical and thermal properties to suit a particular application. It is possible to achievevery high structural efficiency and outstanding thermal properties e.g. high thermal conductivity. MMCs offer potential for improved performance, lower weight and true multi-functionality. They are highly dimensionally stable and not prone to some ofthe negativeaspects of using CFRP (Carbon Fibre Reinforced Polymer) such as micro-cracking and outgassing effects.
MMCs have been developed over a number of decades, and are now reaching the developmental stage where they can be considered for more widespread applications.
Theactivity shall conduct a review of MMC materials available within The ESA Member States, including continuous fibre,reinforced and discontinuous (particle and short fibres) reinforced types. An assessment of the current uses of MMCs on spacecraft shall be made.The activity will consider telecom satellites and examine the opportunities for expanding the use of MMCS. At least the following areas will be considered within the screening:
- Primary Thermal management: highly conductive thermal paths, links including radiator panels, battery mountings & thermal hardware.
- Structural components: including brackets, struts, plates, cylinders, booms, honeycomb & core materials. May also be applicable for electronics packaging (including aspects such as radiation shielding, microwave modules, power semiconductor packages, PCB heat sinks, etc.).
For each identified application, the potential benefits ofemploying an MMC solution shall be considered. A detailed trade-off will be made assessing the potential systems impact of each solution includingmanufacturing and affordability.
The application(s) with the highest impact will be designed, manufactured and breadboard tested. The testing will verify that required performances are met.
*On Delegation Request (formerly called Priority 2) activities will onlybe initiated on the explicit request of at least one National Delegation.
Procurement Policy: C(1) = Activity restricted to non-prime contractors (incl. SMEs). For additional information please go to EMITS news "Industrial Policy measures for non-primes, SMEs and R&D entities in ESA programmes".