19, March 2019

ESA Open Invitation to Tender AO9600
Open Date: 11/03/2019
Closing Date: 15/04/2019 13:00:00

Status: ISSUED
Reference Nr.: 18.123.08
Prog. Ref.: Technology Developme
Budget Ref.: E/0901-01 – Technology Developme
Tender Type: C
Price Range: 100-200 KEURO
Products: Satellites & Probes / Parts / Mechanical, Optical and Magnetic parts / Connecting parts (nuts, bolts, etc), Separating parts (springs, cutters, etc), Spacing Parts, Bearing Parts, Control Parts (gears), ¿ / Orbital Transportation & Re-entry Systems / Descent & Recovery / Descent / Parachutes / Orbital Transportation & Re-entry Systems / Descent & Recovery / Recovery / Homing Beacon, …
Techology Domains: Aerothermodynamics / Numerical Methods / Computational Fluid Dynamics (CFD) / Aerothermodynamics / Numerical Methods / Engineering Techniques / Aerothermodynamics / Numerical Methods / Multidisciplinary Techniques / Aerothermodynamics / Sensors and Measurement Techniques / Intrusive Measurements / Aerothermodynamics / Flight Databases / Informatics Environment
Establishment: ESTEC
Directorate: Directorate of Tech, Eng. & Quality
Department: Mechanical Engineering Department
Division: Propulsion & Aerothermodynamics Division
Contract Officer: Anastasiia Bezulenko
Industrial Policy Measure: N/A – Not apply
Last Update Date: 11/03/2019
Update Reason: Tender issue

Within the present ITT the contractor shall perform a feasibility study (phase A) for a Hyper-velocity Earth Re-entry technology Demonstration mission to be possibly undertaken in the coming few years.The objectives of this activity comprise the following aspects: Selection of one (or more) baseline mission(s) to be trade-off among a sample return mission from the Moon, Mars, the moon of Mars – Phobos, or possibly an asteroid, to define a reference entry scenario. Definition of required representativeness of the demonstration mission (w.r.t selected baseline one) in term of at least entry velocity, Flight Path Angle (FPA), heat flux, heat load and dynamic pressure. Trade-off of different mission architectures (ranging from the use of a light launcher with an additionalpropulsion stage to a more complex option where the system is piggy back on the Orion Mission, EM-2) in order to reproduce the relevant re-entry environment Re-entry vehicle preliminary design State of the art of relevant key technologies and assessment of the level of maturity for the demonstration mission Development roadmap identifying the major required elements of further technological development up to the in-flight demonstration Development cost and risk

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