ESA Open Invitation to Tender AO8752
Open Date: 13/10/2017
Closing Date: 08/12/2017 13:00:00

Status: ISSUED
Reference Nr.: 16.1QM.08
Prog. Ref.: TRP
Budget Ref.: E/0901-01 – TRP
Special Prov.: BE+DK+FR+DE+IT+NL+ES+SE+CH+GB+IE+AT+NO+FI+PT+GR+LU+CZ+RO+PL+EE+HU
Tender Type: C
Price Range: 200-500 KEURO
Products: Satellites & Probes / Materials / Non-metallic
Launchers / Materials / Composite Materials / Reinforcement Material: Others
Techology Domains: Materials and Processes / Novel Materials and Materials Technology Includes materials not yet used in space but presenting potential interest. / Material Assessment
Materials and Processes / Novel Materials and Materials Technology Includes materials not yet used in space but presenting potential interest. / Nanotechnology
Materials and Processes / Materials Processes / Joining
Materials and Processes / Space Environmental Effects on Materials and Processes / Interaction of Materials with the Space Environment
Establishment: ESTEC
Directorate: Directorate of Tech, Eng. & Quality
Department: Product Assurance and Safety Department
Division: Materials & Components Technology Divisi
Contract Officer: Magne-Lie, Karine
Industrial Policy Measure: N/A – Not apply
Last Update Date: 13/10/2017
Update Reason: Tender issue

One important constraint in the sizing process of an ablative TPS for atmospheric entry vehicles is the temperature limit of the supporting heatshield structure and of the bonding material used to attach the TPS. This temperature limit is typically in the range of 150-180degC. For the CFRP the limiting factor is typically the resin. New resin materials (like cyanate ester or bismaleimide) have commercially become available in recent years and relevant CFRP materials been qualified towards higher temperature limits for other space applications (like solar arrays or antenna reflectors). Such increased limits would allow to reduce the required TPS thickness and therefore to reduce the mass of the TPS. The objective of the activity shall be achieved through the following steps: – Perform a market research of advanced CFRP based on relevant new resin materials as well as bonding materials for the attachment of theTPS suited for increased temperatures – Perform a trade-off (including relevant screening tests) – Develop and test a selected CFRPmaterial as well as a TPS bonding material to achieve an operational temperature of at least 250degC, while meeting atmospheric entry vehicle requirements.

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