O. Piersanti Athens 0 7 / 0 2 / 2 0 1 4 ESA UNCLASSI FI ED For - PowerPoint PPT Presentation

Euclid Mission Industry Space Day in Greece O. Piersanti Athens 0 7 / 0 2 / 2 0 1 4 ESA UNCLASSI FI ED – For Official Use

Cosm ic Vision 2 0 1 5 -2 0 2 5 ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 2 ESA UNCLASSI FI ED – For Official Use

Science Program s Under Developm ent (Launched) ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 3 ESA UNCLASSI FI ED – For Official Use

The Euclid Mission ( 1 )  Euclid is a science mission of ESA in the field of cosmology.  The Euclid mission was approved by ESA and delegated bodies for a planned launch in 2020 in the frame of the Cosmic Vision 2015-2025 ESA Science Program.  Euclid is an optical/near-infrared survey mission designed to understand the origin of the accelerating expansion of the Universe.  Need to consider two gravitational forces generated by: • Dark Energy which causes the matter to separate • Dark Matter which causes the matter to agglomerate  About 95% of the energy in the universe must be in those two forces that were never detected directly  Euclid will searches the signatures of the dark energy and matter  Euclid will investigate and characterize the nature of dark energy, dark matter and gravity making use cosmological probes. ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 4 ESA UNCLASSI FI ED – For Official Use

The Euclid Mission ( 2 ) Dark matter and Dark Energy in the Universe ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 5 ESA UNCLASSI FI ED – For Official Use

The Euclid Mission ( 3 ) The dark m atter and energy can be studied by looking at: 1 . The geom etry of the universe a. Measure of position of galaxies as a function of redshift 2 . Grow th of density perturbations a. Evolution of structure as a function of cosmic time, growth rate 3 . Galaxy im age distortion caused by dark m atter bending light Dark Matter ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 6 ESA UNCLASSI FI ED – For Official Use

Space Segm ent - Spacecraft • Mass: ~ 2 1 0 0 Kg • Pow er: ~ 1 7 0 0 W • Data: ~ 8 5 0 Gbit/ day • X-band up/ dow n link for com m and and control • K-band for dow nlink HBR ( ~ 7 5 Mbit/ sec) • Tw o I nstrum ents: Visible I m ager ( VI S) and Near-I nfrared Spectrom eter and Photom eter ( NI SP) • Korsch Telescope w ith SiC technology • Launcher Soyuz from French Guyana w ith Fregat upper stage • Operational orbit around the Lagrange point L2 • Nom inal m ission of 6 .2 5 years • Spacecraft sized for 7 years • Observation of > 1 5 0 0 0 Deg^ 2 of the extra-galactic sky at a galactic latitude > 3 0 Deg and < -3 0 Deg ( Goal 2 0 0 0 0 deg^ 2 ) • Deployable and steerable K-band HGA ( 2 DoF) • Telecom m unication period: 4 hrs per day • Ground station w ill be either Malargue or Cebreros ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 7 ESA UNCLASSI FI ED – For Official Use

Space Segm ent - Payload • Optical configuration: 3-mirrors anastigmatic Korsch • Field of view: 0.763×0.709 deg2, 0.45deg off-axis • Free aperture: 1.2 m2 • VIS-CU and M2 mechanism for calibration • Silicon Carbide SiC-100 technologies • Dichroic at the exit pupil transmit IR light to NISP and reflects visible light to VIS • A visible imager (VIS) • A near-IR instrument (NISP) • Instruments VIS et NISP at cryogenic temperature (150 K et 95 K ) • Image quality requiring high stability with related constraints on the spacecraft PSF • Attitude control with feedback from FGS, Gyros and STR ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 8 ESA UNCLASSI FI ED – For Official Use

Space Segm ent – VI S & NI SP • Visible Imaging in the wavelength range 550-900 nm; • Near Infrared Photometric Imaging in the range 920-2000 nm; • Near Infrared Spectroscopy in the range 1100-2000 nm; ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 9 ESA UNCLASSI FI ED – For Official Use

Space Segm ent - Observation Strategy • Wide Survey to cover 15000 deg2 of extragalactic sky at a galactic latitude > 30 deg and < -30 deg • Deep Survey to cover 40 deg2 • Nominal survey requires field steps slews (< 1.2 deg). • Four dithers per field ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 10 ESA UNCLASSI FI ED – For Official Use

Ground Segm ent ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 11 ESA UNCLASSI FI ED – For Official Use

Launcher • Soyuz 2.1B with Fregate upper stage with direct insertion without parking orbit • Launch from French Guyana ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 12 ESA UNCLASSI FI ED – For Official Use

Orbit • Operational Orbit around L2 with direct injection by the launcher • Ideal to make observation of the sky • Stable thermal environment • No eclipse • Require Orbit correction maneuvers • Constraints on the launch-able mass ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 13 ESA UNCLASSI FI ED – For Official Use

Spacecraft Developm ent The development of Euclid is based on 3 spacecraft models: • Structure and Thermal Model (STM). • Avionic Model (AVM). • Flight Model (FM). Note: Similar models are envisaged on the PLM. Spacecraft STM Spacecraft AVM Spacecraft FM • Qualification of the mechanical Verification of the Spacecraft Verification of the electrical design. design. electrical design by test. Verification of the system and • Qualification of the primary and Verification of all electrical and subsystems functionalities and secondary structure by test. software interfaces. performances. • Verification of the mechanisms Verification of the subsystem Verification of alignment, leakage function by test (TBC). electrical performances in the and mass properties. • Validation of the structural integrated electrical environment. Spacecraft verification in mathematical models. Verification of the Instruments mechanical and thermal • Derivation of the design and electrical compatibility in the environment. mechanical loads for the Spacecraft integrated electrical environment. Verification of Ground Segment and its components. Validation of the on-board software. compatibility. • Fit check for the L/ V and internal Validation of the electrical test Verification of the Spacecraft EMC interfaces. procedures and related applications. and RFC. • Qualification of the thermal design. Optical Verification. • Validation of the thermal mathematical models. • Verification of the thermo-elastic stability. ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 14 ESA UNCLASSI FI ED – For Official Use

Product Tree SVM Prime TAS-I ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 15 ESA UNCLASSI FI ED – For Official Use

Spacecraft & GS planning ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 16 ESA UNCLASSI FI ED – For Official Use

Euclid Procurem ent approach ( 1 / 2 )  Euclid procurement approved by IPC ESA/ IPC(2012)1, add.41 in Paris, 27 June 2012  Euclid industrial work is to be procured in two steps:  first, a procurement action covering the Payload Module (PLM), released in July 2012 and placed in December 2012; ✔  second a procurement action covering the Euclid Spacecraft and Prime contractor activities, including the Service Module (SVM), released in December 2012; ✔  A Contract Proposal was presented to June 2013 IPC for the full Prime Contract (incl. SVM and subsumed PLM) ✔  All activities to be subcontracted will be procured following the ESA Code of Best Practices (ESA/ IPC(2012)65,rev.2); ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 17 ESA UNCLASSI FI ED – For Official Use

Euclid Procurem ent approach ( 2 / 2 )  In principle, two steps:  firstly the Prime Contractor will select the subsystems responsible, including allocations for the units belonging to it;  secondly the selected subsystem contractors will issue ITT for the units procurements.  The procurement plan is regularly reviewed and adapted in order to achieve the GR return requirements;  In doing so, preferential clause, limitations, restricted competition or direct negotiation may be used;  Items may be grouped or, further broken down, to better suit the project needs and/ or help achieving GR;  For stringent technical and programmatic reasons, the competition may be enlarged to non-Member States. ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 18 ESA UNCLASSI FI ED – For Official Use

Geo-Return Requirem ents 1. Payload Module contract only: (D, F, I, UK) 60% , all others 40% ; 2. For the entire Euclid Industrial contract, i.e. PLM+ SVM = > ESA Presentation | O. Piersanti | Athens | 07/ 02/ 2014 | Slide 19 ESA UNCLASSI FI ED – For Official Use