Earth and Moon Radiation Environment Results Obtained by RADOM Instrument on Indian Chandrayyan-1 1 Satellite. Comparison with Model Ts.P. Dachev 1, G. De Angelis 2, B.T. Tomov 1, Yu.N.. Matviichuk 1 Pl.G.. Dimitrov 1, F. Spurny 3, O. Ploc 3 1 Solar-Terrestrial Influences Institute, Sofia, Bulgaria, tdachev@bas.bg 2 DLR, Institute of Aerospace Medicine, Cologne, Germany, Giovanni.Angelis@dlr.de 3 Nuclear Physics Institute, Czech Republic, spurny@ujf.cas.cz
Outlook Introduction Instrumentation Preliminary results for the Earth radiation environment Preliminary results for the Moon radiation environment Conclusions 2
Introduction 3
space radiation measurements experiments since 2000 1. Liulin-MDU1, June 14, 2000, ESA balloon flight up to 33 km over Gap, France; 2. Liulin-MDU MDU5, more than 10000 flight hours on Czech airlines aircrafts from 2001 till 2009; 3. Liulin-Е094, May-August 2001, ESA-NASA exp. on the International space station (ISS); 4. 2 Liulin-MDU, June 2001, NASA ER-2 2 flights at 20 km altitude in USA; 5. R3D-B1, October 2002, ESA Foton M1 satellite unsuccessful launch; 6. R3D-B2, 1-121 12 юни 2005, ESA Foton M2 satellite; 7. 3 Liulin-MDU, June 11, 2005, NASA balloon flight up to 40 km over New Mexico, USA; 8. Liulin-ISS ISS, ROSCOSMOS, launched to ISS in September 2005 (active now); 9. Liulin-6R 6R, since October 2005 working in Internet (active now); 10. Liulin-Mussala Mussala, since June 2006 working in Internet (active now); 11. Liulin-5, ROSCOSMOS, since June 28, 2007 working at ISS (active now); 12. R3D-B3, 3, September 14-26 2007, ESA Foton M3 satellite; 13. Liulin-6S 6S, since October 2007 working at Jungfrau peak in Internet (active now); 14. Liulin-R, January 31, 2008, ESA rocket experiment up to 380 km from Norway; 15. R3DЕ, since 20 February, 2008, working at ESA Columbus module at ISS (active now); 4
Liulin-ISS, 2005-20 2019, Russian Segment ISS Participation of in experiments on the International Space Station (ISS) Liulin-5, 2007-20 2009, Russian Segment ISS Liulin-E094, 2001 US Laboratory module Planned external look of ISS after 2010 Langmuir probe, 2009-2019, 2019, Russian Segment ISS R3DЕ,, 2008-2009 2009 ESA- EuTFF,, Columbus R3DR, 2009-2010 2010 Russian Segment ISS 5
spin-off produced Liulin type spectrometers for measurements of the space radiation on aircrafts are used by scientists from Japan, USA, Germany, France, Canada, Spain, Australia, Poland, Russia, Czech Republic and others GPS receiver; Li-Ion batteries; Galvanically ins. 20-35 V DC 1 GB SD/MMC card. Internet based instrument More than 4 days working time from Li- Ion accumulator Spectrometer with GPS receiver and display for monitoring of the space radiation doses by aircraft pilots Weight: 470 g* Size: 100x100x45 x45 mm Weight: 120 g* Size: 95x8 x85x55 x55 mm Weight: 115 g* Size: 124x40x20 mm Weight: 280 g Size: 110x80 80x455 mm Altitude above the see level as measured by Liulin type spectrometer on the route Sofia-St. St. Zagora town Car route as obtained by GPS receiver mounted in Liulin type spectrometer 11 Liulin type spectrometers during calibrations in CERN, October 2006 6
Chandrayaan-1 1 spacecraft was launched from the Satish Dhawan Space Centre, SHAR, Sriharikota by PSLV-XL (PSLV- C11) on 22 October 2008 at 00:52 UT http://www.isro.org/chandrayaan/htmls/objective_scientific.htm 7
Mission profile 8
Scientific Objectives of the Chandrayaan-1 1 mission High-resolution remote sensing of the moon in visible, near infrared (NIR), low energy X-rays X and high-energy X-ray X regions. Specifically the objectives are: To prepare a three-dimensional atlas (with high spatial and altitude resolution of 5-105 m) of both near and far side of the moon; To conduct chemical and mineralogical mapping of the entire lunar surface for distribution of mineral and chemical elements; To study the Radiation environment of the Moon produced by solar radiation and solar and galactic cosmic rays. http://www.isro.org/chandrayaan/htmls/objective_scientific.htm 9
Chandrayaan-1 1 satellite Spacecraft for lunar mission is: Cuboid in shape of approximately 1.5 m side; Weighing 1380 kg at launch and 675 kg at lunar orbit. Accommodates eleven science payloads: 6 from Indian ISRO; 2 from ESA; 2 from NASA; 1 from. 3-axis stabilized spacecraft using two star sensors, gyros and four reaction wheels. Chandrayaan-1 10
Scientific Payload 11
ISRO Participating agencies and institutions ESA NASA 12
Scientific objectives of RADOM instrument To measure the particle flux, deposited energy spectrum, accumulated ated absorbed dose rates on the way to and in Lunar orbit with high time t resolution, and evaluate the respective contributions of protons,, neutrons, electrons, gamma rays and energetic galactic cosmic radiation nuclei; To provide an estimation of the flux/dose map around Moon at different ferent altitudes; To evaluate the shielding characteristics (if any exists) of the Moon near environment towards galactic and solar cosmic radiation during solar s particle events; To accumulate information for the Moon radiation environment, which further can be used for estimation of the human and electronics doses during the exploration and colonization of the Moon. 13
Instrumentation 14
RADOM Flight model external view Size: 110x40x20 mm; Weight: 98 g.; Consumption: 124 mw The solid state detector of RADOM instrument is behind ~ 0.45 g/cm2 shielding from front side of 2π, 2, which allows direct hits on the detector by electrons with energies in the range 0.85-10 MeV. The protons range is 17.5-200 MeV. On the back 2π2 angle where the satellite is the shielding is larger but not known exactly 15
First screenshot of RADOM-FM.exe program for initialization and quick look of the data Present the data in Table form Spectra Tables Spectra graphics Dose and flux graphics 3D graphics Fail selection RADOM-FM.exe software is developed by and was delivered together with the instrument in middle of September 2007 to ISRO 16
Instrument performance The solid state detector of RADOM instrument is behind ~ 0.45 g/cm 2 shielding from front side of 2π, 2, which allows direct hits on the detector by electrons with energies in the range 0.85-10 MeV. The protons range is 17.5-200 MeV. On the back 2π2 angle where the satellite is the shielding is larger but not known exactly; RADOM was switched ON about 2 hours after the launch. Since this moment it works almost permanently. First the resolution was 10 sec and this was a good decision because no over scaling was observed in the Earth magnetosphere. Since December 3 th it works in 30 sec resolution; Inside of the electron radiation belt doses reached 4.10 4 µgy.h - 1, while the fluxes are 1.5.10 4 cm - 2.s -1 ; Inside of the proton radiation belt doses reached the highest values of 1.2.10 5 µgy.h - 1, while the fluxes are 9.10 3 cm - 2.s -1 ; The galactic cosmic rays (GCR) doses around Earth was about 12 µgy.h - 1. When the satellite was away from the Earth GCR reached 12.2 µgy.h - 1. Close to the Moon the doses fall down to about 8.8 µgy.h - 1 ; The total accumulated dose is about 1.3 Gy till 12 th of November 2008; 17
Earth radiation environment 18
Overview of the near Earth radiation environment obtained by RADOM instrument Dose (ugy/h); Flux (cm^-2s^-1) D/F (ngy.cm^-2.p.^-1) 1E+6 1E+5 1E+4 1E+3 1E+2 1E+1 1E+0 1E-1 Outer (electron) Radiation belt. Dose = 40000 µgy/h Chandrayan-1, RADOM, 22 October 2008 Dose Flux D/F 18:25 19:25 20:25 21:25 22:25 23:25 Slot region Dose = 600 µgy/h UTC Altitude (km) 240 220 200 180 160 140 120 100 80 60 40 20 Inner (proton) Perigee radiation belt. Dose = 1.2 µgy/h Dose = 130000 µgy/h 0 Channel number Counts per channel 19
Dose (ugy/h); Flux (cm^-2s^-1) D/F (ngy.cm^-2.p.^-1) Variations of the doses, fluxes and spectra shape in near Earth space 1E+6 1E+5 1E+4 1E+3 1E+2 1E+1 1E+0 1E-1 1E+4 Chandrayan-1, RADOM, 22 October 2008 Dose Flux D/F Noise 0 180 360 540 720 900 Number of measurements Chndrayaan-1, RADOM 23 October UT 2008 (hh:mm) Altitude (km) 18:25 18:55 19:25 19:55 20:25 20:55 000-120 The highest doses of about 130000 µgy/h are measured inside of the proton belt, never the less that the highest fluxes are measured inside the electron belt The different spectra colors coded different positions along the orbit Deposited Dose (ugy/h) 1E+3 1E+2 1E+1 1E+0 1E-1 1E-2 1E-3 1.0 10.0 Deposited energy (MeV) 300-360 360-420 420-480 480-500 540-600 600-660 660-720 775-828 835-850 850-856 GCR spectrum The position of the maximum along the deposited energy spectra depends by the type and energy of the measured dominating particles. As high the area limited by the spectrum is, as high the deposited dose is! The red spectrum in the bottom is obtained by GCR particles 20
Dose (ugu.h^-1); D/F (ngy.cm^2.p.^-1) The Dose to Flux ratio, (Which is in fact the specific dose per particle.) characterize the type of dominating particles Chandrayaan-1, RADOM 23-26 October 2008 1E+5 Electron belt doses Dose 1E+4 D/F Slot region doses 1E+3 Apogee GCR doses 1E+2 Perigee GCR doses If D/F ratio is above 1 ngy.cm2/part. the dose is deposited mainly by protons 1E+1 1E+0 1E-1 1E-1 1E+0 1E+1 1E+2 Flux (cm^2.s^-1) STIL Proton belt doses 1E+3 1E+4 If D/F ratio is below 1 ngy.cm2/part. the dose is deposited mainly by electrons* *Heffner, 1971. Dublin, Ireland, 88-10 21
H GCR Dynamics of the Equivalent dose distribution (H*(10) along the Chandrayaan-1 1 satellite orbit *(10) = H low + 5H high = 3.357.10 8 { 15 i= 2 i. A i + 5 Begin 26/10/09 01:44:14 End 26/10/09 06:04:14 256 i= 16 i. A } i H *(10) = H + H EB low high H *(10) = 1.3H + 1. 3H PB low high H*(10); Hhigh; Hlow 1.E+05 1.E+04 1.E+03 1.E+02 1.E+01 1.E+00 1.E-01 Perigee GCR doses Proton belt doses (H PB *(10) Slot region doses Electron belt doses (H EB *(10) H*(10) (usv/h) Hlow (usv/h) Hhigh (usv/h) D/F (ngy.cm^2/part.) 1 116 231 346 461 576 691 806 921 1036 1151 1266 1381 1496 Number of measurements 3 per. Mov. Avg. (Hhigh (usv/h)) 3 per. Mov. Avg. (Hlow (usv/h)) 3 per. Mov. Avg. (H*(10) (usv/h)) Apogee GCR doses (H CRB *(10) If D/F ratio is above 1 ngy.cm 2 /part. the dose is deposited mainly by protons and H high have major contribution in the equivalent dose H*(10) If D/F ratio is below 1 ngy.cm 2 /part. the dose is deposited mainly by electrons and H low have major contribution in the equivalent dose H*(10) 22
Variations of the doses and fluxes in dependence by altitude and by the longitude /UT of the satellite 1 When the magnetic axes is to the right of the geographic the satellite is going trough the center of inner radiation belt 4 3 2 22/10/2008 20:57:30-23/10/2008 00:36:57 2 When the magnetic axes is to the left of the geographic the satellite is going trough the periphery of inner radiation belt 4 3 2 23/10/2008 03:48:51-09:44:55 Altitude (km) 10000 9 8 7 6 5 4 3 2 Altitude (km) 10000 9 8 7 6 5 4 3 2 1000 9 8 7 6 5 4 0 10000 Flux (cm^2.s^-1) 20000 0 60000 120000 Dose (ugy/h) 0 2 4 6 8 D/F (ngy.cm^-2/p.) 1000 9 8 7 6 5 4 0 10000 Flux (cm^2.s^-1) 20000 0 60000 120000 Dose (ugy/h) 0 2 4 6 D/F (ngy.cm^-2/p.) Rotational (geographic) axes Magnetic axes The outer belt doses are practically not affected Long=-96 96 UT=21:20 Long=156 UT=03:50 20 0-20 1 2 3 4 5 20 0-20 1 2 3 4 5 CRRES dosimeter data 27 Jul 90 to 12 Oct 91. Fennel/Aerospace Corp., 2003. 23
Explanation of the different doses in proton radiation belt on previous slide Rotational (geographic) axes Magnetic axes Low doses High doses Chandrayaan-1 1 orbit 3D picture of the belts is courtesy of NASA 24
Comparison of Chandrayaan-1 - RADOM spectra with ISS - R3DE spectra RADOM, PRB RADOM, ERB R3DE, ERB The shape of spectra obtained by RADOM are same as spectra obtained by R3DE at Int. Space Station 1E+4 1E+3 R3DE, PRB RADOM, GCR R3DE, GCR The RADOM proton radiation belt (PRB) spectrum is with same shape as R3DE spectrum but at about 1.5 order of magnitude higher because higher flux and respectively dose Deposited Dose (ugy/h) 1E+2 1E+1 1E+0 1E-1 1E-2 The RADOM electron radiation belt (ERB) spectrum is with same shape as R3DE spectrum but about 4 time higher level because higher dose The RADOM galactic cosmic rays (GCR) spectrum practically overlap the REDE spectrum, because of same flux and respectively doses 1E-3 1.0 10.0 Deposited energy (MeV) 25
Moon radiation environment 26
October 27-28, 28, 2008; Perigee = 348 km Apogee = 164600 km; Period = 73 hours Average GCR Dose = 12.89 mgy/h 45 40 D F D/F H*(10) H low *(10) H high *(10) (µgy/h) (cm -2.s -1 ) (µsv/h) (µsv/h) (µsv/h) 12.89 3.14 1.14 26.48 7.40 19.08 35 Dose (ugy/h) 30 25 20 15 Dose (ugy/h) Flux (cm^-2.s^-1) Linear (Dose (ugy/h)) 10 5 0 144000 148000 152000 156000 160000 164000 28/10/2008 04:49:26 Altitude (km) 27/10/2008 08:34:14 27
Oulu neutron monitor (counts/h) RADOM Flux (cm^-2.s^-1) Comparison of RADOM flux data (10 s. resolution) with Oulu neutron monitor count rate data (1 min. resolution) STIL 4.8 4.0 RADOM flux Running average fit Linear fit 3.2 2.4 1.6 7200 7000 Oulu NM counts Running average fit Linear fit 6800 6600 6400 6200 06/11 11:53 07/11 21:10 09/11 06:24 Date (dd/dd) UT (hh:mm) 2008 Dublin, Ireland, 88-10 28
Because the increased shielding of the GCR by the Moon body the dose and flux levels decrease when Chandrayaan-1 1 satellite moves closer to the Moon on 9-10.11.20089 29
Comparisons with G. De Angelis model at 1000 km altitude Data Particle Flux = 2.73 cm - 2 s -1 Average Data GCR Phys. Dose = 10.02 µgy/h Average Data GCR H*(10) Dose = 20.94 µsv/h Model Particle Flux = 3.05 cm - 2 s -1 Average Model GCR Phys. Dose = 11.16 µgy/h Average Model GCR H*(10) Dose = 23.36 µsv/h 30
Variations of the RADOM count rate and respectively dose by the altitude above the Moon surface 180 170 160 Counts Altitude 50 per. Mov. Avg. (Counts) 150 140 130 120 110 100 90 80 Dublin, Ireland, 8-10 8 31 (Counts per 10 s.); (km) 08/12/08 15:36:00 08/12/08 16:48:00 08/12/08 18:00:00 08/12/08 19:12:00 08/12/08 20:24:00 08/12/08 21:36:00 08/12/08 22:48:00 09/12/08 00:00:00 09/12/08 01:12:00 09/12/08 02:24:00 09/12/08 03:36:00 Date/Universal Time
Comparisons with G. De Angelis model at 100 km altitude Data Particle Flux = 2.29 cm - 2 s -1 Average Data GCR Phys. Dose = 8.77 µgy/h Average Data GCR H*(10) Dose = 18.54 µsv/h* Model Particle Flux = 2.55 cm - 2 s -1 Average Model GCR Phys. Dose = 9.76 µgy/h Average Model GCR H*(10) Dose = 20.06 µsv/h 32
Chandrayaan-1 1 is at 200 km circular orbit since 19 th May 2009 Because of smaller shielding from the body of the Moon the doses rice by more than 2 µgy/h and reach 10.85 µgy/h 33
The averaged per day RADOM dose around the Moon is rising in linear way in dependence by GCR Oolu NM (counts/min.) 6830 6810 6790 6770 6750 6730 6710 6690 6670 6650 Counts Linear (Counts) 01/12/2008 21/11/2008 11/11/2008 01/11/2008 22/10/2008 11/12/2008 21/12/2008 31/12/2008 09/02/2009 30/01/2009 20/01/2009 10/01/2009 19/02/2009 01/03/2009 11/03/2009 Date RADOM Dose (µgy/h) 9.8 9.7 9.6 Dose Linear (Dose) 9.5 9.4 9.3 9.2 9.1 9 8.9 6650 6670 6690 6710 6730 6750 6770 Oulu Neutron Monitor (counts/min.) 34
Comparison of the R3DE dose rates obtained at 5.0<L<5.05 with Oulu NM counts/min. No data 35
Long-term GCR doses obtained on different satellites comparison with Oulu neutron monitor data 7000 14.1 µgy/h 45.1 µsv/h Oulu NM (counts/min) 6500 6000 5500 6.14 µgy/h 14.6 µsv/h 5000 01/01/2004 01/01/2003 01/01/2002 01/01/2001 01/01/2000 7.38 µgy/h 16 µsv/h 12.89 µgy/h 35.4 µsv/h 12 µgy/h 29.4 µsv/h 10.3 µgy/h 27.2 µsv/h Date (dd/mm/yy) 01/01/2009 01/01/2008 01/01/2007 01/01/2006 01/01/2005 Solar minimum GCR doses measured by us in low earth orbit rise twice t when the solar activity decline from 2000 to 2009 36
Comparison of Liulin absorbed dose rates with Oulu neutron monitor count rates 37
Observations during the first cycle 24 Sun flares March 12-17 17 2009 Credit: SOHO/MDI 15 March 09 00:58 Daily Sun: 15 Mar 09 Two proto-sunspots are simmering near the sun's equator GOES X ray Flux GOES Proton Flux GOES Electron >2 MeV Flux ACE Solar Wind Speed rise from 350 to 540 km/s GOES Proton and Electron Flux 38
Comparison of the RADOM dose/flux data with the GOES10 0.5-4.0 A Xray data 25 20 Dose Flux 50 per. Mov. Avg. (Dose) 50 per. Mov. Avg. (Flux) Dose (ugy/h); Flux (#/cm 2.s) 15 10 5 0 12/03/2009 00:00:00 13/03/2009 00:00:00 14/03/2009 00:00:00 15/03/2009 00:00:00 Date 2009 16/03/2009 00:00:00 17/03/2009 00:00:00 18/03/2009 00:00:00 Only the first RADOM channel is enhanced, which means very low energy deposition 39
Dose (ugy/h); Flux (#/cm 2.s) Comparison of the RADOM dose/flux data with the GOES11 >2 MeV Electron flux data 25 20 15 10 5 0 12/03/2009 00:00:00 Dose Flux 50 per. Mov. Avg. (Dose) 50 per. Mov. Avg. (Flux) 13/03/2009 00:00:00 14/03/2009 00:00:00 15/03/2009 00:00:00 Date 2009 16/03/2009 00:00:00 17/03/2009 00:00:00 18/03/2009 00:00:00 Only the first RADOM channel is enhanced, which means very low energy deposition 4000 GOES11 >2 MeV Electron flux (counts/cm2.s.sr) 3500 3000 2500 2000 1500 1000 500 0 2009 03 13 0000 2009 03 14 0000 2009 03 15 0000 2009 03 16 0000 Date 2009 Authors thanks to V. Girish who first mention the flare data 40
3 new space experiments are under development Liulin Phobos engineering model Liulin-Phobos Objectives: Measurements during the cruise phase, on Mars s s orbit and on the surface of Phobos. Estimation of the radiation doses received by the spacecraft electronics and assessment the radiation risk to crew of future exploratory flights to Mars. Cooperation: STIL (Bulgaria), IMBP (Russia), NIRS (Japan( Japan), Lavochkin Space Association, Russia Phobos - Soil sample return apparatus Liulin S engineering model Liulin-S S instrument Objectives: Measurements during the descending phase of one Orlan type space suit thrown from International Space station. Cooperation: STIL (Bulgaria), IMBP (Russia), Lavochkin Space Association, Russia Orlan space suit R3D-B3 instrument R3D-B3 instrument Objectives: Measurements during the about 1 month flight of BION-M M satellite around the Earth. Cooperation: STIL (Bulgaria), IMBP (Russia), FAU, Germany, Lavochkin Space Association, Russia BION-M M satellite 41
Conclusions RADOM spectrometer proved its availability to characterize the different radiation fields in the Earth and Moon radiation environment. The proton and electron radiation belts in the Earth magnetosphere was well recognized. The electron radiation belt doses reached 4.104 µgy/h,, while the fluxes are 15000 #/cm 2.s. The proton radiation belt doses reached the highest values of 1.2.105 µgy/h,, while the fluxes are 9100 #/cm 2.s; The galactic cosmic rays (GCR) dose rates around Earth was about 12 µgy/h.. Away from the Earth GCR reached 13.2 µgy.h - 1. At 100 km orbit the doses fall down to about 9.6 µgy/h.. The rise of the orbit to 200 km increase the doses to 10.8 µgy/h; The total accumulated dose during the transfer from Earth to Moon is about 1.3 Gy; 42
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Acknowledgements The authors are thankful to all ISRO staff and more specially to: Mr. M. Annadurai, Project Director of Chandrayaan-1 Prof. J. N. Goswami, Project Scientists of Chandrayaan-1 Prof. P. Sreekumar, ISRO Space Astron. & Instrum.. Div. Dr. V. Girish, ISRO Space Astron. & Instrum.. Div. Eng. V. Sharan, ISRO Space Astron. & Instrum.. Div. Dr. J D Rao, ISTRAC/ISRO Bangalore 44
Thank you 45