1. PLATO Phase A/B1 Status TOU Meeting Catania 28 Feb 2011 PLAnetary Transits and Oscillation of stars

2. 2 Mission Requirements (1/2) Launch from French Guiana by a Soyuz 2-1b launch vehicle Max launch mass: 2100 Kg plus adapter (GAIA baseline). Operations in a large orbit around the Earth-Sun Lagrange Point 2 (L2) Nominal mission duration of 6 years after commissioning Spacecraft sized for 8 years Long observation runs above +60 degree and below -60 degree ecliptic latitude Step-and-Stare Phase with observation at any ecliptic latitude and longitude subject to Sun in favourable direction Quarterly 90deg rotation around the mean Line of Sight of the Spacecraft

3. 3 Mission Requirements (1/2) Three days autonomy without ground contact Seven days in Survival Mode Communication with S/C via X band Use of 15 m antenna in Kourou Use of 35 m antenna in Cebreros and New Norcia 24 hours coverage during LEOP During science operations up/downlink is time-limited 4 hours per day coverage during nominal operations  3.5 hrs / day for data downlink  0.5 hrs / day for setup / ranging

4. 4 Project Schedule Program Milestones Assessment Phase in 2008- Aug 2009 (Completed) ESA internal review: Sep – Oct 2009 (Completed) First down-selection of M-class missions to enter the Definition Phase (A/B1): Feb 2010 (Completed) Definition Phase (A/B1) K.O.: 01 July 2010 (Done)  Second down-selection for M1/M2: October 2011  Completion of the Definition Phase (A/B1): 31 December 2011  Final adoption for the Implementation Phase (B2/C/D/E1): before Feb 2012  Start of the Implementation Phase: by July 2012  Launch: by end 2018

5. 5 Industrial Activities (1/2)  PLATO is in the Definition phase (A/B1) which is conducted according to the following plan  Two parallel and competitive studies are performed  The studies are conducted by EADS Astrium (SAS) and Thales Alenia Space which were selected as result of the tenders evaluation  Both studies are progressing nominally.

6. 6 Industrial Activities (2/2)  The Preliminary Configuration Definition Review (PCDR) was successfully completed in week 42 (18-22 Oct) for both Contractors with identified criticalities and recommendations  Spacecraft Configurations capable of accommodating the payload and consistent with the established mission requirements have been identified  Preliminary analyses have demonstrated consistency of the design with the established ESA requirements  Go-ahead has been given to initiate the post PCDR tasks i.e. detailed system design, programmatic aspects and costs evaluation  All Phase A activities shall be completed by May 15, 2011 and will be subject to the planned PRR.

7. 7 Technology DevelopmentPLATO CCD development activity Development of dedicated PLATO CCDs  For each telescope: 4 CCDs of 4510 2 pixels  18μm pixel pitch; 15 arcse/pixel plate scale  136 CCDs in total; FPA size: 164mm 2  Temperature: Nominal -70  C  Normal telescopes (32):  full frame operation  25 sec observation cycle  magnitude range: 8 – 11 m V  Fast telescopes (2):  frame transfer operation; also for AOCS information  2.5 sec observation cycle  magnitude range: 4 – 8 m V

8. 8 Spacecraft and Payload Configuration Payload Electrical Configuration

9. 9 Technology Development Development of dedicated PLATO CCDs  For each telescope: 4 CCDs of 4510 2 pixels  18μm pixel pitch; 15 arcse/pixel plate scale  136 CCDs in total; FPA size: 164mm 2  Temperature: Nominal -70  C  Normal telescopes (32):  full frame operation  25 sec observation cycle  magnitude range: 8 – 11 m V  Fast telescopes (2):  frame transfer operation; also for AOCS information  2.5 sec observation cycle  magnitude range: 4 – 8 m V

10. 10 Spacecraft and Payload Configuration SVM Electrical Configuration (option)

11. 11 Spacecraft and Payload Configuration

12. 12 Spacecraft and Payload Configuration

13. 13 Spacecraft and Payload Configuration Units accommodation in the SVM

14. 14 Spacecraft and Payload Configuration Spacecraft alternative configuration

15. 15 Spacecraft and Payload Configuration Spacecraft alternative configuration

16. 16 Mission Timeline 1.Commissioning starts during Transfer, and ends no later than 2 months after arrival in L2 (goal: ends upon arrival) 2.Nominal Science Ops = 6 years 3.Extended Science Ops = 2 years 4.TOTAL LIFETIME= 8 years Spacecraft and Mission Description

17. 17 Roll around LOS 1.Problem: body-mounted solar arrays must be occasionally re-pointed towards Sun 2.Strategy: rotate around LOS by 90° every 3 months  LOS stays fixed on the field 3.Maximum solar aspect angle  45° in azimuth  30° in elevation Spacecraft and Mission Description

18. 18  Operational Orbit

19. 19 Conclusions All PLATO activities are progressing nominally No show-stoppers have been identified To come:  Spacecraft detailed design (on going)  AO intermediate review: in March  Issue of the updated AO: in April  Spacecraft PRR and Consortium PIRR (from mid May)  Phase A conclusion: end June  Updated AO response and evaluation: in Jul  Decision for implementation: October 2011

20. 20 Thank You