ESA Open Invitation to Tender AO9532
Open Date: 11/09/2018
Closing Date: 06/11/2018 13:00:00

Status: ISSUED
Reference Nr.: 18.123.05
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: Launchers / Propulsion / Liquid propulsion systems – BB / Propellant Tanks *See Structures / Launchers / Propulsion / Liquid propulsion systems / Launchers / Propulsion / Liquid propulsion systems – BB / Feeding system devices (feed lines, filters, valves, ¿)
Techology Domains: Propulsion / Chemical Propulsion Technologies / Liquid Propulsion Systems
Establishment: ESTEC
Directorate: Directorate of Tech, Eng. & Quality
Department: Mechanical Engineering Department
Division: Propulsion & Aerothermodynamics Division
Contract Officer: Reinsoo, Anna
Industrial Policy Measure: C2 – Activities in open competition, significant partecipat…
Last Update Date: 11/09/2018
Update Reason: Tender issue

‘The advanced porous injection system on its own is showing a different spray vaporization effect than standardized coaxial injection systems. The main difference is that the spray is vaporized more due to the acceleration of the hot gases within thechamber. Therefore, this injection system is showing good throttleability without a big influence on the performance itself.Together with an expansion deflection nozzle in a reversed flow configuration, the nozzle throat of the engine can be adapted by moving the nozzle in relation to chamber. Therefore, this engine could show a good throttleability due to the injector and the nozzle throat change and could therefore lead to the possibility of having one engine for an enorm thrust range.This activity is concentrating on1.) Assess the possibility of using MMH/NTO within the advanced porous injection system and test corresponding throttleable range2.) Simulate by means of numerical calculations the possibility of using reversed expansion deflection nozzle for spacecraft applications3.) Build a breadboard unit for testing under ambient conditions and analyse the throttleability by moving the nozzle and varying the pressure within the chamber.The main target would be a thruster in the range of 400N. Additionally, the influence of weight shall be assessed by means of analysis.’Procurement Policy: C(2) = A relevant participation (in terms of quality and quantity) of non-primes (incl. SMEs) is required. For additional information please go to EMITS news “Industrial Policy measures for non-primes, SMEs and RD entities in ESA programmes”.

If you wish to access the documents related to the Invitation to Tender, you have to log in to the ESA Portal.