6, November 2017

ESA Open Invitation to Tender AO8297
Open Date: 31/10/2017
Closing Date: 12/12/2017 13:00:00

Status: ISSUED
Reference Nr.: 15.129.05
Prog. Ref.: TRP
Budget Ref.: E/0901-01 – TRP
Tender Type: C
Price Range: > 500 KEURO
Products: Satellites & Probes / Mechanisms / Mechanisms / Deployment (SADM, SADE, …)
Satellites & Probes / Payloads / Instruments / Optical Instruments / Optical Telescopes
Satellites & Probes / Materials / Composite Materials / Matrix Structure: Epoxy
Satellites & Probes / Materials / Composite Materials / Matrix Structure: Cyanate Ester
Launchers / Avionics / On-Board Computers / *See Software
Techology Domains: System Design & Verification / Mission and System Specification / Specification Methods and Tools
System Design & Verification / Collaborative and Concurrent Engineering / Concurrent Design
Mechanisms / Mechanism Core Technologies / Actuator Technologies
Optics / Optical System Engineering / Overall Optical System Definition, Design and Engineering
Establishment: ESTEC
Directorate: Directorate of Tech, Eng. & Quality
Department: Mechanical Engineering Department
Division: Mechatronics and Optics Division
Contract Officer: Strzelecki, Patryk Michal
Industrial Policy Measure: N/A – Not apply
Last Update Date: 03/11/2017
Update Reason: Loaded a new Clarification(English version)

Currently the size limit for primary mirrors of large telescopes is – due to the available Ariane-5 fairing – typically at 3.5m (Herschel). Future science (and most likely also Earth observation missions) will call for larger telescope sizes due to more demandingrequirements on the light collecting efficiency and angular resolution.Different possibilities can be envisaged to increase the size of telescopes:- maximising the diameter of the rotational symmetric monolithic primary mirror compatible with the dimension ofexisting launcher fairings;- maximising the size of an off-axis elliptical primary mirror by making best use of existing launcher fairing volumes most likely in combination with an unfoldable secondary mirror;- introducing a segmented primary mirror that will be deployed in-orbit (like JWST) using existing fairings;- increasing the size of a monolithic mirror assuming a larger fairing (diameter 8m) will be available.System designs shall be established and traded-off to identify the most suitable design and approach for extending the light collection efficiency and angular resolution of large space telescopes. The trade-off shall include design complexity, risk and manufacturing cost. The primary mirror of the selected concept shall be designed in line with typical environmental and performance requirements. Roadmaps for all feasible implementation solutions shall be established for the development of such a mirror. Development needs for manufacturing and testing facilities shall beidentified.Two parallel studies shall be implemented. Multi-disciplinary cooperation with support from mechanisms and structure experts will be implemented for the execution of this activity.

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