ESA Open Invitation To Tender AO8804
Open Date: 13/10/2016
Closing Date: 15/12/2016 13:00:00

Status: ISSUED
Reference Nr.: 16.123.05
Prog. Ref.: GSTP Period 6 E1 PRJ
Budget Ref.: E/0904-611 – GSTP Period 6 E1 PRJ
Special Prov.: PL
Tender Type: C
Price Range: 200-500 KEURO
Products: Orbital Transportation & Re-entry Systems / Propulsion and Reboost / Chemical Propulsion / Propulsion System
Techology Domains: Propulsion / Chemical Propulsion Technologies / Solid Propulsion Systems
Establishment: ESTEC
Directorate: Directorate of Technical & Quality Manag
Department: Mechanical Engineering Department
Division: Propulsion & Aerothermodynamics Division
Contract Officer: van Hilten, Linda
Industrial Policy Measure: N/A – Not apply
Last Update Date: 13/10/2016
Update Reason: Tender issue

Solid Propellant Rocket Motors meet the need for controlled de-orbiting of satellites to a pre-designated uninhabited area of the planet (e.g. south Pacific Ocean) that are within the scope of the ESA/ADMIN/IPOL(2014)2, the Space Debris Mitigation Policy for Agency Projects.Many studies have been performed already regarding this topic and large experience exists in Europe already with solid propellants. The specific application however, reduces the TRL of the propellant, because the propellant required to be altered. This has been investigated already in a TRP contract (T719-310MP) and therefore qualification of such propellant is the next step.The proposed work within this activity is the following:- Consolidation of a relevant subset of the (mission) requirements and product functional specification (in close consultation with ESA);- Development of an Aluminium free solid propellant that meets the requirements defined above.- Assessment and testing of storability and aging in flight of the propellant. This regards topics as for example: thermal cycling, radiation, etc. To be supported by dedicated accelerated ageing test (storability in flight > 10 years to 15 years in various orbits) and rheological properties determination;- Testing of the propellant in relevant conditions and environment including testing in a breadboard demonstrator.- Reporting on results and recommendations for future phases including planning (where applicable) for a follow-in solid propellant demonstrator engine to qualify the propellant.As a reference; the complete development roadmap includes:- Propellant design and pre-qualification- Design and manufacturing of 3 x Engineering Model motors and testing to bring the motor up to CDR level / Pre-Qualification level.- Design iteration and 3 x Qualification Model motor manufacturing and testing to achieve qualification level.- Flight Model motor manufacturing and implementation in spacecraft

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