Earth and Moon Radiation Environment Results Obtained by RADOM Instrument on Indian Chandrayyan-1 1 Satellite. Comparison with Model

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1 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

2 Outlook Introduction Instrumentation Preliminary results for the Earth radiation environment Preliminary results for the Moon radiation environment Conclusions 2

3 Introduction 3

4 space radiation measurements experiments since Liulin-MDU1, June 14, 2000, ESA balloon flight up to 33 km over Gap, France; 2. Liulin-MDU MDU5, more than 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, 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 , 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

5 Liulin-ISS, , Russian Segment ISS Participation of in experiments on the International Space Station (ISS) Liulin-5, , Russian Segment ISS Liulin-E094, 2001 US Laboratory module Planned external look of ISS after 2010 Langmuir probe, , 2019, Russian Segment ISS R3DЕ,, ESA- EuTFF,, Columbus R3DR, Russian Segment ISS 5

spin-off produced Liulin type spectrometers for measurements of the space

France, Canada, Spain, Australia, Poland, Russia, Czech Republic and

accumulator Spectrometer with GPS receiver and display for monitoring of

100x100x45 x45 mm Weight: 120 g* Size: 95x8 x85x55 x55 mm Weight: 115 g*

see level as measured by Liulin type spectrometer on the route Sofia-St.

6 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 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

7 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 7

8 Mission profile 8

9 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 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. 9

Accommodates eleven science payloads: 6 from Indian ISRO; 2 from ESA; 2 from NASA; 1

10 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

11 Scientific Payload 11

12 ISRO Participating agencies and institutions ESA NASA 12

13 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

14 Instrumentation 14

15 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 MeV. The protons range is MeV. On the back 2π2 angle where the satellite is the shielding is larger but not known exactly 15

16 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

17 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 MeV. The protons range is 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 µgy.h - 1, while the fluxes are cm - 2.s -1 ; Inside of the proton radiation belt doses reached the highest values of µgy.h - 1, while the fluxes are 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

18 Earth radiation environment 18

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

19 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 = 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) Inner (proton) Perigee radiation belt. Dose = 1.2 µgy/h Dose = µgy/h 0 Channel number Counts per channel 19

20 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 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: The highest doses of about 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 Deposited energy (MeV) 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

21 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 October E+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, Dublin, Ireland,

22 H GCR Dynamics of the Equivalent dose distribution (H*(10) along the Chandrayaan-1 1 satellite orbit *(10) = H low + 5H high = { 15 i= 2 i. A i + 5 Begin 26/10/09 01:44:14 End 26/10/09 06:04: i= 16 i. A } i H *(10) = H + H EB low high H *(10) = 1.3H H 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.) 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

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.

23 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 /10/ :57:30-23/10/ :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 /10/ :48:51-09:44:55 Altitude (km) Altitude (km) Flux (cm^2.s^-1) Dose (ugy/h) D/F (ngy.cm^-2/p.) Flux (cm^2.s^-1) Dose (ugy/h) D/F (ngy.cm^-2/p.) Rotational (geographic) axes Magnetic axes The outer belt doses are practically not affected Long= UT=21:20 Long=156 UT=03: CRRES dosimeter data 27 Jul 90 to 12 Oct 91. Fennel/Aerospace Corp.,

24 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

25 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 Deposited energy (MeV) 25

26 Moon radiation environment 26

27 October 27-28, 28, 2008; Perigee = 348 km Apogee = km; Period = 73 hours Average GCR Dose = mgy/h D F D/F H*(10) H low *(10) H high *(10) (µgy/h) (cm -2.s -1 ) (µsv/h) (µsv/h) (µsv/h) Dose (ugy/h) Dose (ugy/h) Flux (cm^-2.s^-1) Linear (Dose (ugy/h)) /10/ :49:26 Altitude (km) 27/10/ :34:14 27

28 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 RADOM flux Running average fit Linear fit Oulu NM counts Running average fit Linear fit /11 11:53 07/11 21:10 09/11 06:24 Date (dd/dd) UT (hh:mm) 2008 Dublin, Ireland,

29 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

30 Comparisons with G. De Angelis model at 1000 km altitude Data Particle Flux = 2.73 cm - 2 s -1 Average Data GCR Phys. Dose = µgy/h Average Data GCR H*(10) Dose = µsv/h Model Particle Flux = 3.05 cm - 2 s -1 Average Model GCR Phys. Dose = µgy/h Average Model GCR H*(10) Dose = µsv/h 30

31 Variations of the RADOM count rate and respectively dose by the altitude above the Moon surface Counts Altitude 50 per. Mov. Avg. (Counts) Dublin, Ireland, (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

32 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 = 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 = µsv/h 32

33 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 µgy/h 33

34 The averaged per day RADOM dose around the Moon is rising in linear way in dependence by GCR Oolu NM (counts/min.) Counts Linear (Counts) 01/12/ /11/ /11/ /11/ /10/ /12/ /12/ /12/ /02/ /01/ /01/ /01/ /02/ /03/ /03/2009 Date RADOM Dose (µgy/h) Dose Linear (Dose) Oulu Neutron Monitor (counts/min.) 34

35 Comparison of the R3DE dose rates obtained at 5.0<L<5.05 with Oulu NM counts/min. No data 35

36 Long-term GCR doses obtained on different satellites comparison with Oulu neutron monitor data µgy/h 45.1 µsv/h Oulu NM (counts/min) µgy/h 14.6 µsv/h /01/ /01/ /01/ /01/ /01/ µgy/h 16 µsv/h 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/ /01/ /01/ /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

37 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:

simmering near the sun's equator GOES X ray Flux GOES Proton Flux GOES Electron

38 Observations during the first cycle 24 Sun flares March 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.

39 Comparison of the RADOM dose/flux data with the GOES A Xray data Dose Flux 50 per. Mov. Avg. (Dose) 50 per. Mov. Avg. (Flux) Dose (ugy/h); Flux (#/cm 2.s) /03/ :00:00 13/03/ :00:00 14/03/ :00:00 15/03/ :00:00 Date /03/ :00:00 17/03/ :00:00 18/03/ :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.

40 Dose (ugy/h); Flux (#/cm 2.s) Comparison of the RADOM dose/flux data with the GOES11 >2 MeV Electron flux data /03/ :00:00 Dose Flux 50 per. Mov. Avg. (Dose) 50 per. Mov. Avg. (Flux) 13/03/ :00:00 14/03/ :00:00 15/03/ :00:00 Date /03/ :00:00 17/03/ :00:00 18/03/ :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) 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

assessment the radiation risk to crew of future exploratory flights to Mars.

Association, Russia Phobos - Soil sample return apparatus Liulin S engineering

one Orlan type space suit thrown from International Space station.

Orlan space suit R3D-B3 instrument R3D-B3 instrument Objectives: Measurements

41 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

42 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 µgy/h,, while the fluxes are #/cm 2.s. The proton radiation belt doses reached the highest values of 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

43 43

44 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

45 Thank you 45

Simultaneous Investigation of Galactic Cosmic Rays on Aircrafts and on International Space Station

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