12th european solar physics meeting 8 - 12 september 2008...

12th European Solar Physics Meeting 8 - 12 September 2008

Freiburg, Germany

Electronic proceedings

For further information on the meeting, for all abstracts of talks and posters

as well as other articles of these proceedings, please visit the following web site:

http://espm.kis.uni-freiburg.de

edited by Hardi Peter Kiepenheuer-Institut für Sonnenphysik Freiburg, Germany [email protected]

Friday 11:05-11:20

The ADAHELI Solar Mission Berrilli, F.1; Velli, M.2; Roselli, L.3; Bigazzi, A.4; Moretti, P.F.5; Romoli, M.2; Orsini, S.6; Cavallini, F7; Greco, V.8;

Carbone, V.9; Consolini, G.6; Di Mauro, M.P.10; Ermolli, I.11; Pietropaolo, E.12; Romano, P.13; Ventura, P.11; White, S.M.14; Zuccarello, F.15; Cauzzi, G.16; Valdettaro, L.17

1Dip. di Fisica, UniversitÃ di Roma Tor Vergata; 2Dip. di Astronomia e Scienza dello Spazio, Universita di Firenze; 3Dip. di Ingegneria Elettronica e dell'Informazione, Universita di Perugia; 4Altran Italia; 5Headquarter of National Research Council, Piazzale Aldo Moro; 6INAF Istituto di Fisica dello Spazio Interplanetario; 7INAF Osservatorio

Astronomico di Arcetri; 8CNR - Istituto Nazionale di Ottica Applicata, Astrofisica; 9Dip. di Fisica, Universita della Calabria; 10INAF Istituto di Astrofisica Spaziale e Fisica Cosmica; 11INAF Osservatorio Astronomico di Roma;

12Dip. di Fisica, Universita della Aquila; 13INAF Osservatorio Astrofisico di Catania; 14Dept. of Astronomy, University of Maryland; 15Dipartimento di Fisica e Astronomia, Sezione Astrofisica; 16INAF - Osservatorio Astronomico di Arcetri;

17Dip. Matematica, Politecnico di Milano

ADAHELI (Advanced Astronomy for HELIOphysics) is an Italian Space project for the investigation of solar photospheric and chromospheric dynamics, via high-resolution spectro-polarimetric observations in the near-infrared spectral range. The mission has been financed for phase A study in the framework of ASI Italian Space Agency Small Missions Program call of September 2007.

Four fields have been selected to highlight the specific benefits of ADAHELI scientific payload: 1) Photospheric and chromospheric dynamics and structure, 2) Emergence and evolution of solar active regions and solar irradiance, 3) Chromospheric and corona heating and turbulence, 4) Solar flares in the millimeter wavelength region.

The principal science instrument, ISODY, is a 50 cm solar telescope equipped with an innovative Focal Plane Suite composed of a spectro-polarimetric imager, based upon two Fabry-Perot interferometers operating in the NIR regions around 845nm and 1083nm, a broad band imager, and a correlation tracker used as image stabilization system.

Designed Mission Profiles for ADAHELI intend to achieve continuous high-spectral and spatial resolution observations of the Sun for a routine duration of 4 hours with a goal to be extended to 24 hours.

ADAHELI also carries MIOS, a millimeter wavelengths radiometer operating at around 90 GHz for flare detection.

The ADAHELI payload's instrument suite integrates and complements, without overlap, the present major objectives of ESA, NASA and the International Living with a Star program, in particular Solar Dynamics Observatory, PICARD, Solar Orbiter, and the Solar Probe missions.

Proposals for optional instruments are also under evaluation: DIMMI-2h, a double channel MOF based full disk imager operating at 589nm and 770nm, allowing high temporal resolution velocity and magnetic field measurements; EISR a two channel spectrometer operating in the 50-130 nm wavelength range, and NPA, an in-situ Neutral Particle Analyzer to detect Energetic Neutral Atoms (ENA). Science objectives related to optional instruments include: solar high and low-degree p modes oscillations, EUV solar structures and variability, solar gravitational red-shift measurement, detection of ENA originating from the plasma region in the Earth's magnetosphere and undergoing reflection from the Earth's atmosphere.

The ADAHELI Solar MissionBerrilli, F., Velli, M., Roselli, L., A. Bigazzi and ADAHELI Team

F. BerrilliRome ToV University

"The dream of yesterday is the hope of today and the reality of tomorrow" -- R H Goddard

Adaheli

NANI GIGANTUM HUMERIS INSIDENTES

AdaheliFrom Wikipedia

Ad h li th ifi ti f th i th th l f th O i i fAdaheli was the personification of the sun in the mythology of the Orinoco region of South America. He was troubled by the fact that there were no people on Earth, and so he descended to earth to created themearth to created them. All of the original women were quite beautiful. However, some of the men were so ugly that the others found them to be literally intolerable. This led to the separation of the original people with the ugly men going to the east with their wives and the others goingoriginal people, with the ugly men going to the east with their wives and the others going to the west with their wives.


ProloguePrologue


ADAHELI i It li S A (ASI) j t d f Ph A

ADAHELI, an ASI Small Mission

ADAHELI is an Italian Space Agency (ASI) project, approved for Phase-A, feasibility study within ASI’s “Small Missions” 2007 call (5 SM selected out of 26 competing projects).

ADAHELI is a mini-satellite-class Mission, around 400Kg and a budget of50 MEuros + launch

After Phase A (Dec 2008), ASI will select two Missions, out of the five competing projects to proceed on to design manufacturing and launchcompeting projects, to proceed on to design, manufacturing and launch, with no further selection.

Th t l t d Mi i l d t b l h d b 2012 d 2014The two selected Missions are planned to be launched by 2012 and 2014, respectively.


ADAHELI TeamADAHELI Team


Adaheli’s Prime Contractor - Experience & Core Competences

Carlo Gavazzi Space, is a leading italian satellite manufacturer, Carlo Gavazzi Space, is a leading italian satellite manufacturer, providing Low-Earth Orbit platforms from 35 to 800 Kg forscientific & commercial missions.

MITA - Microsatellite Italiano a Tecnologia Avanzata

PRISMA – Missione Ottica per Osservazione terrestre

MIOSAT - Missione Ottica basata su microSATelltite

AGILE - Astrorivelatore Gamma ad Immagini LeggeroAGILE - Astrorivelatore Gamma ad Immagini Leggero(last ASI small mission)


Adaheli’s Phase-A Industrial Team


Scientific staff

ADAHELI Associated Scientists

• A. Egidi, D. Del Moro, S. Cantarano, V. Penza, B. Viticchie’, M. Stangalini,L.Biferale Università di Roma Tor Vergata

• K. Reardon, INAF-Arcetri• S. Criscuoli, M. Centrone, F. Giorgi - INAF – OAR• F. Giammaria - Università degli Studi dell'Aquila• D. Cardini, A.Chieffi - INAF-IASF Roma• F. Alimenti, V. Palazzari - DIEI - Università degli Studi di Perugia• A. Vecchio, F.Lepreti, L.Sorriso-Valvo - Università della Calabria• L. Contarino, S. Guglielmino - Università di Catania• A. Milillo, A. Mura, E. De Angelis, V. Mangano INAF – IFSI Roma


ScienceScience


ADAHELI's main science objectivesScience

ADAHELI s main science objectives1. Photospheric and chromospheric dynamics and structure2 Emergence evolution and cancellation of solar magnetic features2. Emergence, evolution and cancellation of solar magnetic features

and solar irradiance3. Chromospheric and corona heating and turbulence4 S l fl i th illi t l th i4. Solar flares in the millimeter wavelength region

Augmented Science Objectives (Optional Instruments):g j ( p )1. Helioseismology2. Basic physics: solar gravitational red-shift3 EUV ariabilit of different solar feat res on the S n and diagnostics3. EUV variability of different solar features on the Sun and diagnostics

of the extended solar corona.4. Origin of ENA between terrestrial magnetosphere and geocorona


Important questionsScience

Important questions

1. What is the role of photospheric dynamics in the formation and evolution f h h ?of chromosphere?

2. How is the solar magnetic field generated?

3. How is the corona heated?4. How is plasma turbulence

generated and dissipated?generated and dissipated?


Mission Objectives for ADAHELI intend to achieve continuous high-spectral

Core instruments

j g pand spatial resolution observations of the Sun for a routine duration of 4 hours with a goal to be extended to 24 hours.

Science instrument of ADAHELI Mission are:1. ISODY a VIS-NIR telescope equipped with an innovative focal plane

suite composed of a monochromatic imager based upon two FPsuite composed of a monochromatic imager, based upon two FP interferometers, a broad band channel, and a correlation tracker used as image stabilization system.

2 MIOS a radiometer observing the sun in the millimetric wave band2. MIOS a radiometer observing the sun in the millimetric wave band

And optionally:1 M i l f ll di k i1. Magneto optical full disk imager2. Extreme Ultraviolet imager3. Neutral Particle (ENA) Analyzer


ISODY HeritageISODY Heritage


ISODY heritage

IPM@THEMIS, Cavallini et al, 1993

1-20μm spectrometer@TIRGO Berrilli et al., 1987IBIS@DST, Cavallini et al, 1999


ISODY heritage

IBIS Data: 630nm continuum and total polarization imagesViticchiè, Del Moro, Berrilli - Università degli Studi di Roma Tor Vergata


ISODY (Interferometer for SOlar DYnamics)ISODY (Interferometer for SOlar DYnamics)


Telescope type: Gregorian with al lli id i i d

ISODY Telescope

prolate ellipsoid primary mirror andwith a collimation lens.Field of view: 120 arcsec (diameter)Wavelength range: 390 – 1100 nmWavelength range: 390 1100 nm

Entrance Pupil (EP): outer diameter (clearaperture) 500 mmExit Pupil (EXP): clear diameter 30 mmM1 + M2: effective focal length and f number ofM1 + M2: effective focal length and f-number oftelescope without collimation lens are 4526 mmand f/9.M1 + M2 + CLU: angular magnification for thetelescope (collimation lens is now included) is50/3.Telescope length: 2200 mmM1 (Primary Mirror): concave prolate ellipsoid.FS1 (First Field Stop): heat dump mirrorM2 (Secondary Mirror): concave prolate ellipsoid.( y ) p pFS2 (Second Field Stop): mirror.CLU (Collimation Lens Unit).PMU (Polarization Modulator Unit).TTP (Tip Tilt Mirror).


NBI ISODY Spectral RangesIDOSY NBI shall be able to scan the following spectral regions (TBC) corresponding to

Narrow Band & Broad Band ISODY Spectral requirements

IDOSY NBI shall be able to scan the following spectral regions (TBC) corresponding to three different interferential pre-filters:1: Ca II 854.2 nm (0.7nm FWHM)2: Fe I 852.67 nm (0.7nm FWHM)2: Fe I 852.67 nm (0.7nm FWHM)3: Si I 1082.7 nm and He triplet at 1083.0 nm (1.2nm FWHM)

NBI ISODY spectral resolutionpISODY NBI spectral resolution R=λ/Δλ, shall be better than 200000 at 1090 nm and 230000 at 850 nm.

BBI ISODY Spectral rangesISODY BBI shall provide images in the following spectral bands (TBC) corresponding to three different broad-band filters.:1: Ca K : 393.3 ± 0.15 nm 2: G band: 430.5 ± 0.8 nm3: Green: 532 ± 0.4 nm


ISODY preliminary optical scheme


ADAHELI ConfigurationADAHELI Configuration


Inside VEGA fairing

ISODY Telescope

MIOS A t F i i E l

ISODY SPF

MIOS Antenna Fairing Envelope

X-Band Antenna

D biti M Th tStart Tracker


Deorbiting Manouver ThrustersStart Tracker

ISODY Telescope


M1 and M2 mirrors of a space telescope

ISODY Telescope

p pmust be extremely light weight and have to be stiff (i.e., honeycomb mirror of silicon carbide (SiC) or beryllium and ultra thin glass)

Rear surface of M1 showing flexure mechanical coupling


g p g

ISODY Telescope

Thermal conductor is made of copper and, possibly, carbon nanotubes powders that are compressed together Tip-Tilt assembly

Heat Radiator

Heat rejectorHeat rejectortoward ISODY focal plane instruments


MIOS and ADAHELI’s Optional Science instrumentsMIOS and ADAHELI s Optional Science instruments


MIOS

MIOS, a millimeter-wave (90 GHz) radiometer, will measure the flux spectral density variations due to solar flares with high timevariations due to solar flares with high time-on-target, high temporal resolution (100ms), and good sensitivity (10sfu).

A space-based solar radio-telescope with a sensitivity of 10sfu in 0.1s and 3sfu in 1s is expected to detect at least one order of magnitude more events than ground-based telescopestelescopes, which immediately makes the instrument attractive. (S. White)


ADAHELI’s Optional Science instruments

DIMMI-2h: a double channel magneto-optical filter (MOF) b d f ll di k i ti t 589 d 770 ll ibased full disk imager operating at 589 and 770 nm, allowing high temporal resolution velocity and magnetic field measurements at two different heights in the solar atmosphereatmosphere.

• NPA, a Neutral Particle Analyzer able to detect Energetic Neutral Atoms (ENA) radiating from two different directions.

0.02nm

• EISR, an EUV imaging and spectro-radiometry instrument.

0.02nm


Mission analysis and trade offsMission analysis and trade offs


Mission Analysis and Trade Offs

According to the requirements, the total amount of the doppler shift shall be less than 4 km/s with the goal to have 2 km/s for a duration as long as possible. To this purpose three classes of orbits are considered in the analysis:purpose, three classes of orbits are considered in the analysis:

1. Sun-Synchronous Circular Orbits

2. Sun-Synchronous Elliptical Orbits2. Sun Synchronous Elliptical Orbits

3. Elliptical Orbits

The orbital propagator takes into account: 21X21 harmonics of the Earth p p ggravitational model, the lunisolar gravitational attractions, the solar-radiation pressure and the atmospheric drag (Jacchia model 1970). The analysis is conducted for the satellite mass of 400 kg , cross-section of 1.65 m 2 and CD=2.2.


• Two Observation Indicators have been introduced (these indicators take into account the required doppler shift and the umbra time):


)– PCOD: Percentage of time of Continuous Observation for at least 4 hours each Day over 365

days;– PCOM: Percentage of time of Continuous Observation for at least 24 hours each mean Month

over 12 mean months where a mean month is 30 417 daysover 12 mean months, where a mean month is 30.417 days.• The following orbit classes, which may accomplish to the desired characteristics, have been analyzed:

Orbit class Orbit

600 K f l i d

Sun-Synchronous Circular Orbit (dawn-dusk)(SSCO)

600 Km of altitude

800 Km of altitude

1000 Km of altitude

1200 Km of altitude

1410 Km of altitude

Sun-Synchronous Frozen Ellipitcal Orbit (SSFEO)

0.1 of eccentricity

0.2 of eccentricity

0.3 of eccentricity

Ellipitcal Frozen Orbit (EFO)

8 hours of orbit period

12 hours of orbit period

44.5 hours of orbit period


• Sun-Synchronous Circular Orbit class of orbits presents the best trade off among


y p gobservation requirements and mission constraints (reliability, cost and mission complexity)


Mission Analysis, Trade Offs

The trade off analysis has led to select, as ADAHELI baseline orbit, the Sun-Synchronous Circular Orbit at 800 Km of altitude.


Space to ground x-band interface analysis and trade offs

Different options, relevant to different X-band ground stations, have been analyzed inDifferent options, relevant to different X band ground stations, have been analyzed in order to select the optimal solution, according to the ADAHELI average data volume to be downloaded each day (this value depends on the P/L memory and Tx data rate).

Three Ground Stations have been considered: Kiruna Oulu and SvalbardThree Ground Stations have been considered: Kiruna, Oulu and Svalbard.

The choice of Ground Station is realized by considering the link budget, the average daily data rate in order to select the optimal solution, according to the ADAHELI average data volume to be downloaded each day.

Although Svalbard average daily data rate is higher, it isn’t the best choice because the analysis has highlighted a strong variability of the contacts time and the average dailyanalysis has highlighted a strong variability of the contacts time and the average daily data rate. So the selected location of ground station has been Kiruna because the average daily data rate is better than the Oulu average daily data rate.


SummarySummary


• ADAHELI is an ASI low-budget, high-performance solar Mission based

Summary

g , g pon a proven Small-Satellite class platform (such as CGS’s AGILE).

• ADAHELI is the first ASI project fully devoted to Heliophysics• ADAHELI is the first ASI project fully devoted to Heliophysics.

• ADAHELI will be the first mission to carry on-board a spectro l i t i i i i t t b d d bl F b P tpolarimetric imaging instrument based on a double Fabry-Perot

interferometer, exploiting a new technology for future space imagers.

• ADAHELI’s instrument suite integrates and complements – without overlap - the present major objectives of ESA, NASA, JAXA and the International Living with a Star program.g p g


Principal Investigator

Contacts

Francesco Berrilli, University of Rome Tor Vergata (IT)[email protected] Marco Velli, University of Florence (IT)[email protected] Roselli, University of Perugia (IT)

lli@di i i [email protected]

Program Manager:Paolo Sabatini Director Satellite Division Carlo Gavazzi SpacePaolo Sabatini. Director, Satellite Division, Carlo Gavazzi [email protected]

Science Program Manager:Science Program Manager:Alberto Bigazzi, Altran [email protected]


12th european solar physics meeting 8 - 12 september 2008...

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