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INTEGRATED THROTTLEABLE VALVE AND ENGINE DEVELOPMENT FOR MARS LANDINGS

ESA Open Invitation To Tender AO8722
Open Date: 15/08/2016
Closing Date: 14/10/2016 13:00:00


Status: ISSUED
Reference Nr.: 16.123.02
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: > 500 KEURO
Products: Orbital Transportation & Re-entry Systems / Propulsion and Reboost / Chemical Propulsion Systems ¿ BB / Flow control and distribution devices (pipes, valves, actuators, filters, pressure transducers, pressure regulators)
Technology Domains: Propulsion / Chemical Propulsion Technologies / Liquid Propulsion Systems
Establishment: ESTEC
Directorate: Directorate of Technical & Quality Management
Department: Mechanical Engineering Department
Division: Propulsion & Aerothermodynamics Division
Contract Officer: van Hilten, Linda
Industrial Policy Measure: C2 - Activities in open competition, significant participation
Last Update Date: 15/08/2016
Update Reason: Tender issue

The MSR mission (and any proposed landing on the Martian surface with a large payload) requires a soft landing. The precision of this landing is also of increasing importance as site selection becomes a driver for science. Automatic hazard avoidance also becomes desirable. Both these requirements are best met with a propulsion system with a capacity for thrust modulation. Any exploration robotic missions requiring a soft landing such as MSR and its precursors will require dedicated engines that represent a clear case for European independence. In general, throttleable mono-propellant solutions are required due to landing site contamination considerations. Further, the relative simplicity of the mono-propellant solutions leads to a more mass efficient propulsion subsystem. A running activity on throttlable valve development shows promise that this capability can be acquired within Europe. This testing under the TRP program is to be limited to flow path development of the valve and obtaining metrics for flow quality and repeatability on a development model. Only simulants are to be used and the valve will not be coupled with an engine (though the contractor has been asked to consider thermal and structural constraints in the development).The activity proposed herein is to take the previous work at valve level and examine the issues of coupling the valve to a flight engine. The activity scope is to include:- Further development of the development model (DM) valve to include a flight like interface. - Design development and manufacture of throttle valve elegant breadboard DM - Design and manufacture of valve driver electronics elegant breadboard DM - Demonstration of combined valve and controller in conjunction with battleship/existing chamber and catalyst bed.- Valve development and verification based on existing mono-propellant hardware- Verification of engine thermo-mechanical behaviour and catalyst performance in throttled conditions- Preliminary requirements definition on a throttleable engine of 2.5-3.0kN rated thrust with a deep throttling capability- Preliminary design definition and justification of a mission specific chamber and catalyst bedA European product development in this area can be based on initial know-how built in the past by European industry and needs to be front loaded to cover throttle valve development which is an essential component of the overall engine design. Engine chamber technology already exists at a stand alone TRL of 5, however, the combined TRL is at best 3.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".

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