HELLO

1. HELLO SIAMOIS in Dome-C Paris 15-16 may 2006

2. Overall Description • Divided in four sub-systems : • A dedicated Telescope with its Bonnette (telescope guiding and fiber coupling). • An Interferometer and a Camera. • A structure for thermal and mechanical control. • A command/control software system. • Divided in five laboratories : • GIGT from OMP (Observatoire Midi-Pyrennée). • LUAN from OCA (Observatoire Côte d’Azur). • IAS (Institut d’Astrophysique Spatiale). • LESIA from OPM (Observatoire Paris-Meudon). • CSIC from Institutode Astrofisica de Andalusia (in discussion). • One associated private contractor : • SESO (Société Européenne de Systèmes Optiques). Paris 15-16 may 2006

3. Overall Description • Assignment of the tasks : • GIGT : Development of the Bonnette and associated test equipment. • LUAN : Telescope delivery and Antarctic instrumentation expertise. • IAS : Thermal design and support for the environment qualification. • LESIA : Global management, camera, electronics and optical bench deliveries. • CSIC : Command/control sub-system delivery (not confirmed). Paris 15-16 may 2006

4. Overall Description Vacuum pump Dedicated Telescope Bonnette Thermo-mechanical structure. Optical bench. Optical fibers : signal and calibration Interferometer Camera Calibration Command/control system: Acquisition,image processing … Paris 15-16 may 2006

5. The constraints. • Small budget and short planning… • High reability of the instrument : • Observation requirements : 90% of duty cycle. • Very difficult to fix anything at Dome C in Antarctica. • Very easy to use : • Not easy set-up at Dome C in Antarctica (once again :-) ). • Wintering will insure a minimal maintenance. • Rather hard environmental conditions : • Shocks and temperature (level and gradient) during transportation and storage. • Temperature, humidity and pressure during operation. Paris 15-16 may 2006

6. The telescope. • Functions/Specifications : • Collect the light with an effective pupil of 40cm (diameter) in the visible part of the spectrum. • Optimization of the reflectivity in the blue part 400-600nm of the spectrum. • FOV of 6arcs. • Track any target in a TBD*TBD ° in the sky. • Function in a temperature range of -80°C<T<30°C. • Phase A solution : • Classical 16” telescope with an azimutal mounting. • External guiding with a dedicated system. • F/10 numerical aperture. • Customization of the structure and driving motors to sustain low temperature. Paris 15-16 may 2006

7. The Bonnette • Functions/Specifications : • To point a target and maintain the flux inside the optical fiber with a jitter lower than 1arcs and an aperture of F/4. • Used of the science target to realize the fine guiding. • Function in a temperature range of -80°C<T<30°C. • Allow the calibration of the interferometer in the optical bandwidth. • Interface the optical fiber with the telescope. • Phase A solution : • Mechanical and software interfaces with the telescope. • Dichroïc plate to realized the guiding with the red part of the spectrum. • Used of an ADC to correct differential refraction in the air mass. • Used of an calibration system in the place of the science target. • Used of optics to adapt the telescope aperture. Paris 15-16 may 2006

8. The Bonnette and the telescope. Telescope Motors Science signal In the optical fiber Optics Dichroic Control loop Guiding system Paris 15-16 may 2006

9. The optical bench. • Functions/Specifications : • Collect all the flux of the science target in the 400-560nm optical bandwidth. • Carry out a doppler sampling of the signal (over 5 points). • Realize a spectral dispersion of 1000. • Focus the spectra on a 2 dim detector. • Has no moving element. • Carry out a spectral calibration during the observation. • Phase A solution : • Used of a Mach-Zender interferometer. • The interferometer part of the optical path is realized in one block of the same material (Zerodur). • Used of a step mirror (intrinsic path difference). • Used of a delay component to optimize the path difference . • Used of a second optical-fiber coupled to a spectral calibration source. • Used of different dioptric to feed the interferometer and focus on the camera. • Used of segmentary mirrors to separate the spectra. Paris 15-16 may 2006

10. The optical bench. O1 : Interferometer Objective M1 : Plan Mirror O2 : Camera Focus Objective M2 : Steps Mirror (∆l) M4 et M3 : Segmentary Mirror L1 : Beam Splitter L2 : Delay component R1 et R2 : Grating 400mm 320mm O1 L2 L1 O2 Paris 15-16 may 2006

11. Signal on the Camera l nm CCD Rows Science spectra Calibration lines Paris 15-16 may 2006

12. The mechanical structure. • Functions/Specifications : • To ensure positioning of the optics in reference to the interferometer. Dl = 100µm • To ensure positioning of the interferometer inside the optical path. • To maintain a primary vacuum inside the interferometer part (10-4 bar). • To insure stray light baffling. • To allow the change of the delay plate to optimize versus the science target. • To insure the re-positioning of the optical fibers with an accuracy of 50µm. • To isolate the optical bench from vibrations and shocks. • To allow the integrity of the optics during thermal cycling (-40°C/+25°C). • Phase A solution : • Used of a specific structure. • Special design for the lens mounts. Paris 15-16 may 2006

13. The mechanical structure. Interféromètre SIAMOIS JP Amans, GEPI, Obs Paris Paris 15-16 may 2006

14. The thermal control. • Functions/Specifications : • To insure a temperature around 20°C±1K during the operation. • To insure a temperature stability (inside the frequency domain) of the following parts : • Optics except the interferometer : ±1K in temporal with spatial gradient of ±0.5K. • Interferometer except the delay component : ±0.1K in temporal with spatial gradient of ±0.1K. • Delay component : ±50mK in temporal with spatial gradient of ±50mK. • Phase A solution : • Classical thermal control of the room. • Maximal thermal decoupling of the interferometer. • Poor thermal conductibility of the interferometer part. • Structure wrapped in nut shell and thermal inertia to filter the external fluctuations and minimize the convection. • Used of MLI to reduce the radiative exchange. • No internal or variable power source. • Used of an active thermal control if needed at the interferometer interface (filter conductive perturbations). Paris 15-16 may 2006

15. The command/control system. • Functions/Specifications : • Send command to the guiding system to acquire the target. • Send command to the camera (exposure time and windowing). • Send new parameters to the active control systems (if needed). • Acquire the image and the HK of the instrument. • Acquire the active control systems corrections. • Store all the data on hard drive. • Carry out pre-processing of the data. • Allow the users to have a quick-look during operation. • Phase A solution : • Develop a specific software (but use some sub-system’s module). • Use of a RAID hard disk and make periodic back up (DVD). • Use of internet to have a quick-look from Europe (limited bandpass). Paris 15-16 may 2006

16. The command/control system. Guiding system Thermal control system Camera and HK Image HK (T°, P) Exposure, windowing HK : T°,PWM Command : T°, PWM a,t Da, Dt HK Commande/control system Raw storage Backup Pre-processing IHM Quick-Look Data sending Paris 15-16 may 2006

17. Development Philosophy. • Step I : Establish all the requirements of the sub-systems and the interfaces between them. • Step II : Develop the test benches and equipments, write the invitation to tender for the industrial contractors. • Step III : Develop the sub-systems (industries and laboratories) or buy them directly when possible (budget and specifications). • Step IV : Individual acceptance of each sub-systems. • Step V : Environmental qualification. • Step VI : Integration of the sub-systems together up to the instrument level. • Step VII : End-to-end test in laboratory and on the sky, final setup. • Step VIII : After transportation to Dome-C, simple integrity test. • Some revue are foreseen during the project development. • Like “space instrument” development : quality, management of configuration, documentation, revues… with limitations! Paris 15-16 may 2006

18. Development planning Paris 15-16 may 2006

19. Development planning. • In 2006, the main activities are:  Development of a test-bed to validate the optical concept.  Drafting of the Needed Technical Specifications for the different sub-system.  Study of a preliminary design of the optical fiber, the bonnette, the software architecture and the Thermo-Mechanical structure.  Delivery of a commercial camera. • In 2007, the main activities are:  To continue the studies conducted in 2006 to present a PDR in march-april 2007.  Detailed studies of the different sub-system of the instrument.  Launching of the industrial contracts and the achievements in the laboratories (mainly the equipments test). • Implementation of the equipments test and facilities in the different laboratories. • The main objective in 2007 is to achieved a PDR at the beginning of the year and a FDR at the end of the year to be able to launch to industrial contracts. Paris 15-16 may 2006

20. Development planning • In 2008 and 2009, the main activities are:  Validation, test and integration of the different sub-systems.  Integration of the interferometer and environmental qualification.  Implementation of the infrastructure at Dôme C (house, software interface, …).  Integration of the instrument.  End-to-end test on the sky.  Packaging and transport to Dôme C. • In 2010, at the beginning of the year, the instrument is setup in the facilities at Dôme C and ready to work. Paris 15-16 may 2006

21. Integration and Test Philosophy. • Each sub-systems will be tested with its own equipment test at a defined level of representativeness. • Environmental qualification will be performed case-by-case. Acquired qualification will not be performed again (telescope). Requirement is : “to not be destroyed”. • Thermal cycling will be performed. No switch-ON or operations outside the nominal temperature range is foreseen. • At each deliveries and before integration will be performed an acceptance test including documentation. • A test plan will be write for the integrated instrument, for each sub-systems and also for critical components. Levels of accuracy of all the measurements will be established in accordance with the instrument scientist. • A data base will be feed by the results of elementary and end-to-end calibrations. Great, that’s a space instrument! Paris 15-16 may 2006

22. Integration and Test Philosophy • No detailed or reduce mathematical models arerequired. • The insurance quality will be reduced just over the lethal limit. • Except for the Bonnette (if needed in military type) the electronics will be of commercial type. No rad-hard device. • The software development will not be subjected to spatial laws (cold or hot redundancy, correction error code, specific FPGA, …). We accept manual reboot! • No irradiation qualification will be performed. • Mechanical qualification will be performed depending the vibration and shock levels given by the transportation. • Minimal setup may be performed at Dome C, including the interferometer installation (base line). Arrghh, that’s not! Paris 15-16 may 2006

23. Budget and funding. • Total budget of the instrument : 860k€. • Transportation and primary housing dealt with IPEV. • Different sources of funding : • Agence Nationale pour la Recherche : 460k€. Main part. • CSA and Paris Observatory : 110k€ * 2. • PNPS : 40k€. Laboratories : 100k€. • SESO and industrial partner : 40k€. • Distribution of the budget : • Optical bench = 300k€. • Mechanical and thermal control = 200k€ • Telescope and Bonnette = 110k€ • Camera, electronics and software = 45k€. • Mission and test = 90k€. • Miscellaneous and support = 115k€. Paris 15-16 may 2006

24. Budget and funding Paris 15-16 may 2006

25. Buget and funding (the laste one) Paris 15-16 may 2006

26. Participation of the different laboratories • GIGT : 4 * 20% and 3 * 10%. • LUAN : 2-3 *10%, support in Antarctic instrumentation. • IAS : 25%, Integration support, 18 months for external support. • LESIA : 75%, 3 * 50%, Integration support, 1 Phd student, around 3-5 support in expertise (from 5 to 30%). The percentages are smoothed over the 4 years of instrument development… including 2006 where nearly nothing will be done! Paris 15-16 may 2006

27. See you at Dome C ! Paris 15-16 may 2006