ESA Open Invitation to Tender AO10432
Open Date: 15/07/2020
Closing Date: 09/09/2020 13:00:00

Status: ISSUED
Reference Nr.: 20.123.06
Prog. Ref.: Technology Developme
Budget Ref.: E/0901-01 – Technology Developme
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 / Propulsion / Chemical Propulsion / Propellants
Technology Domains: Propulsion / Supporting Propulsion Technologies and Tools / Propellants
Establishment: ESTEC
Directorate: Directorate of Tech, Eng. & Quality
Department: Mechanical Department
Division: Propulsion & Aerothermodynamics Division
Contract Officer: Garre, Maximilian
Industrial Policy Measure: C1 – Activities in open competition limited to the non-Larg…
Last Update Date: 15/07/2020
Update Reason: Tender issue

To validate, through simulation and experiment, new design criteria defined to limit the occurrence of detonation during spacecraft operation. Various classical or green propellants can decompose during transient operations in the propulsion system, e.g. priming. During this operation, harsh conditions occur due to a sudden compression of the fuel vapour or pressurant in the line. This leadsto high temperatures resulting in an exothermic decomposition of the propellant such as H2O2, hydrazine derivatives etc… This goes along with sudden pressure rises which result in catastrophic failures of propulsion components. This decomposition is not fully understood and characterized along with a lack of an experimental database in Europe. Hence, during the design of the propulsion system there are no clear evaluation criteria available to avoid the occurrence of an explosion on board of a spacecraft. The present activity aims to characterize clearly the occurrence of adiabatic decomposition and the related pressure rise for at least one classical propellant (e.g. Hydrazine) and one green propellant (e.g. H2O2). This shall lead to the definition of design criteria which shall then be implemented in simulation tools for validation and verification. This activity encompasses the following tasks:1. Design or upgrade a water hammer test facility representative for a propulsion system able to cope with the occurrence of detonation.2. Creation of an experimental database for at least 2 propellants (one green, one presently used on s/c) and one inert fluid (e.g. Water). Pressurant gases to be considered are nitrogen and helium for a limited set of parametric geometries (e.g. Diameter, lengths…).The experiments shall provide at least the simultaneous pressure and temperature evolution at the location of possible detonation.3. Design criteria to quantify the detonation parameters based on the experimental database and chemical kinetics4. Validation and sensitivity analysis of existing European standard propulsion simulation tools (i.e. ESPSS: European Space Propulsion System Simulation) to correctly reproduce the conditions of the detonation criteria. Procurement Policy: C(1) = Activity restricted to non-prime contractors (incl. SMEs). For additional information please go to EMITS news (dated 05/02/2001) “Industrial Policy measures for non-primes, SMEs and RD entities in ESA programmes”.