earth and moon radiation environment results obtained by ... · scientific objectives of the...

Earth and Moon Radiation Environment Earth and Moon Radiation Environment Results Obtained by RADOM Instrument Results Obtained by RADOM Instrument

on Indian Chandrayyanon Indian Chandrayyan--1 Satellite. 1 Satellite. Comparison with ModelComparison with Model

Ts.P. DachevTs.P. Dachev11, G. De Angelis, G. De Angelis22, B.T. Tomov, B.T. Tomov11, , Yu.NYu.N. Matviichuk. Matviichuk11

Pl.GPl.G. Dimitrov. Dimitrov11, F. Spurny, F. Spurny33, O. Ploc, O. Ploc33

11SolarSolar--Terrestrial Influences Institute, Sofia, Bulgaria, Terrestrial Influences Institute, Sofia, Bulgaria, [email protected]@bas.bg22DLR, Institute of Aerospace Medicine, Cologne, Germany, DLR, Institute of Aerospace Medicine, Cologne, Germany, [email protected]@dlr.de

33Nuclear Physics Institute, Czech Republic, Nuclear Physics Institute, Czech Republic, [email protected]@ujf.cas.cz

mailto:[email protected]



STILSTIL--BASBAS 14th WRMISS Workshop, 14th WRMISS Workshop, Dublin, Ireland, 8Dublin, Ireland, 8--10 Sept. 200910 Sept. 2009 22

OutlookOutlook

IntroductionIntroductionInstrumentationInstrumentationPreliminary results for the Earth radiation Preliminary results for the Earth radiation environmentenvironmentPreliminary results for the Moon radiation environmentConclusionsConclusions


IntroductionIntroduction


STILSTIL--BAS space radiation measurements experiments BAS space radiation measurements experiments since 2000since 2000

1.1. LiulinLiulin--MDU1, June 14, 2000, ESA balloon flight up to 33 km over Gap, FrMDU1, June 14, 2000, ESA balloon flight up to 33 km over Gap, France;ance;2.2. LiulinLiulin--MDUMDU5, 5, more than 100more than 10000 00 flight hours on Czech airlines aircrafts fromflight hours on Czech airlines aircrafts from 2001 2001 till till

2002009;9;3.3. LiulinLiulin--ЕЕ094, 094, MayMay--AugustAugust 2001, 2001, ESAESA--NASA exp. on the International space station NASA exp. on the International space station

(ISS)(ISS);;4.4. 2 2 LiulinLiulin--MDU, June 200MDU, June 20011,, NASA ERNASA ER--2 flights at 20 km altitude in USA2 flights at 20 km altitude in USA;;5.5. R3DR3D--B1, OctoberB1, October 2002, 2002, ESA Foton M1 satellite ESA Foton M1 satellite –– unsuccessful launchunsuccessful launch;;6.6. R3DR3D--BB2, 12, 1--12 12 юниюни 2005, 2005, ESAESA Foton M2 satelliteFoton M2 satellite;;7.7. 3 3 LiulinLiulin--MDU, June 11, 2005, NASA balloon flight up to 40 km over New MexMDU, June 11, 2005, NASA balloon flight up to 40 km over New Mexico, ico,

USA;USA;8.8. LiulinLiulin--ISSISS, , ROSCOSMOS, launched to ISS in September ROSCOSMOS, launched to ISS in September 2005 2005 (active now)(active now);;9.9. LiulinLiulin--6R6R, , since October since October 20020055 working in Internet working in Internet (active now)(active now);;10.10. LiulinLiulin--MussalaMussala, , since June since June 2006 2006 working in Internet working in Internet (active now)(active now);;11.11. LiulinLiulin--5, 5, ROSCOSMOS, since June ROSCOSMOS, since June 2828,, 20072007 working at ISS working at ISS (active now)(active now);;12.12. R3DR3D--BB3, 3, September September 1414--26 2007, 26 2007, ESAESA Foton M3 satelliteFoton M3 satellite;;13.13. LiulinLiulin--6S6S, , since October since October 20020077 working at Jungfrau peak in Internet working at Jungfrau peak in Internet (active now)(active now);;14.14. LiulinLiulin--RR, , January January 3131,, 2008, 2008, ESAESA rocket experiment up to rocket experiment up to 380 380 km from Norwaykm from Norway;;15.15. R3DR3DЕЕ, , since since 20 20 February,February, 2008, 2008, working at ESA Columbus module atworking at ESA Columbus module at ISS ISS (active (active

now)now);;16.16. RADOM, since October 22,RADOM, since October 22, 2008,2008, Moon satelliteMoon satellite ChandrayyanChandrayyan--11 (active now)(active now);;


Participation of STIL-BAS in experiments on theInternational Space Station (ISS)

LiulinLiulin--E094, 2001E094, 2001US Laboratory moduleUS Laboratory module Langmuir probe, Langmuir probe,

20020099--2019, Russian 2019, Russian Segment ISSSegment ISS

LiulinLiulin--5, 20075, 2007--20200099,,Russian Segment ISSRussian Segment ISS

LiulinLiulin--ISS, 2005ISS, 2005--202019, 19, Russian Segment ISSRussian Segment ISS

Planned external look of ISS afterPlanned external look of ISS after 2010 2010

R3DR3DЕЕ, 2008, 2008--2009 2009 ESAESA-- EuTFFEuTFF, Columbus , Columbus

R3DR, 2009R3DR, 2009--2010 2010 Russian Segment ISSRussian Segment ISS

http://www.bas.bg/


STIL-BAS 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;GPS receiver;LiLi--Ion batteries;Ion batteries;

Galvanically ins. 20Galvanically ins. 20--35 V DC 35 V DC 1 GB SD/MMC card.

Spectrometer with GPS receiver Spectrometer with GPS receiver and display for monitoring of and display for monitoring of the space radiation doses by the space radiation doses by

aircraft pilots

More than 4More than 4 days days working time from Liworking time from Li--

Ion accumulatorInternet based Internet based

instrument instrument 1 GB SD/MMC card. Ion accumulator aircraft pilots

Weight:Weight: 470470 g*g*SizeSize:: 110000x10x1000x45 mmx45 mm

11 Liulin type spectrometers during 11 Liulin type spectrometers during calibrations in CERN, October 2006

Weight: Weight: 282800 ggSize: Size: 110110xx8080xx445 mm5 mm

Weight: Weight: 121200 g*g*Size: 95Size: 95x8x855x55 mmx55 mm

Weight: Weight: 111155 g*g*Size: 124Size: 124x40x20 mmx40x20 mm

Altitude above the see level as Altitude above the see level as measured by Liulin type spectrometer measured by Liulin type spectrometer

on the route Sofiaon the route Sofia--St. Zagora townCar route as obtained by GPS receiver Car route as obtained by GPS receiver mounted in Liulin type spectrometer mounted in Liulin type spectrometer

calibrations in CERN, October 2006St. Zagora town


ChandrayaanChandrayaan--1 spacecraft was launched from the 1 spacecraft was launched from the SatishSatishDhawanDhawan Space Centre, SHAR, Space Centre, SHAR, SriharikotaSriharikota by PSLVby PSLV--XL (PSLVXL (PSLV--

C11) on 22 October 2008 at 00:52 UT C11) on 22 October 2008 at 00:52 UT

http://www.isro.org/Chandrayaan/htmls/objective_scientific.htmhttp://www.isro.org/Chandrayaan/htmls/objective_scientific.htm

http://www.isro.org/Chandrayaan/htmls/objective_scientific.htm


Mission profileMission profile


Scientific Objectives of the ChandrayaanScientific Objectives of the Chandrayaan--1 mission1 mission

HighHigh--resolution remote sensing of the moon in visible, near infrared resolution remote sensing of the moon in visible, near infrared (NIR), low energy X(NIR), low energy X--rays and highrays and high--energy Xenergy X--ray regions. ray regions. Specifically the objectives are: Specifically the objectives are: To prepare a threeTo prepare a three--dimensional atlas (with high spatial and dimensional atlas (with high spatial and altitude resolution of 5altitude resolution of 5--10 m) of both near and far side of the 10 m) of both near and far side of the moon;moon;To conduct chemical and mineralogical mapping of the entire To conduct chemical and mineralogical mapping of the entire lunar surface for distribution of mineral and chemical elements;lunar surface for distribution of mineral and chemical elements;To study the Radiation environment of the Moon produced by To study the Radiation environment of the Moon produced by solar radiation and solar and galactic cosmic rays.solar radiation and solar and galactic cosmic rays.

http://www.isro.org/Chandrayaan/htmls/objective_scientific.htmhttp://www.isro.org/Chandrayaan/htmls/objective_scientific.htm

http://www.isro.org/Chandrayaan/htmls/objective_scientific.htm


ChandrayaanChandrayaan--1 satellite1 satellite

ChandrayaanChandrayaan--11

Spacecraft for lunar mission is:Spacecraft for lunar mission is:

•• CuboidCuboid in shape of in shape of approximately 1.5 m side;approximately 1.5 m side;•• Weighing 1380 kg at launch and Weighing 1380 kg at launch and 675 kg at lunar orbit.675 kg at lunar orbit.•• Accommodates eleven science Accommodates eleven science payloads:payloads:

6 from Indian ISRO;6 from Indian ISRO;2 from ESA;2 from ESA;2 from NASA;2 from NASA;1 from STIL1 from STIL--BAS.BAS.

•• 33--axis stabilized spacecraft axis stabilized spacecraft using two star sensors, gyros and using two star sensors, gyros and four reaction wheels.four reaction wheels.


Scientific PayloadScientific Payload

http://upload.wikimedia.org/wikipedia/commons/1/11/Chandrayaan1_as_updated.jpg


Participating agencies and institutionsParticipating agencies and institutions

NASANASA

STILSTIL--BASBAS

ESAESA

ISROISRO


Scientific objectives of RADOM instrument Scientific objectives of RADOM instrument

To measure the particle flux, deposited energy spectrum, accumulTo measure the particle flux, deposited energy spectrum, accumulated ated absorbed dose rates on the way to and in Lunar orbit with high tabsorbed dose rates on the way to and in Lunar orbit with high time ime resolution, and evaluate the respective contributions of protonsresolution, and evaluate the respective contributions of protons, neutrons, , neutrons, electrons, gamma rays and energetic galactic cosmic radiation nuelectrons, gamma rays and energetic galactic cosmic radiation nuclei;clei;

To provide an estimation of the flux/dose map around Moon at difTo provide an estimation of the flux/dose map around Moon at different ferent altitudes;altitudes;

To evaluate the shielding characteristics (if any exists) of theTo evaluate the shielding characteristics (if any exists) of the Moon near Moon near environment towards galactic and solar cosmic radiation during senvironment towards galactic and solar cosmic radiation during solar olar particle events;particle events;

To accumulate information for the Moon radiation environment, whTo accumulate information for the Moon radiation environment, which ich further can be used for estimation of the human and electronics further can be used for estimation of the human and electronics doses doses during the exploration and during the exploration and ““colonizationcolonization”” of the Moon.of the Moon.


InstrumentationInstrumentation


RADOM Flight model external viewRADOM Flight model external view

SizeSize: : 110110x40x20 mm; x40x20 mm; WeightWeight: : 9898 g.; Consumptiong.; Consumption: : 124124 mWmW

The solid state detector of RADOM instrument is behind ~ 0.45 g/The solid state detector of RADOM instrument is behind ~ 0.45 g/cm2 cm2 shielding from front side of 2shielding from front side of 2ππ, which allows direct hits on the detector by , which allows direct hits on the detector by electrons with energies in the range 0.85electrons with energies in the range 0.85--10 MeV. The protons range is 17.510 MeV. The protons range is 17.5--200 MeV. On the back 2200 MeV. On the back 2ππ angle where the satellite is the shielding is larger angle where the satellite is the shielding is larger but not known exactlybut not known exactly


First screenshot of RADOMFirst screenshot of RADOM--FM.exeFM.exe programprogramfor initialization and quick look of the datafor initialization and quick look of the data

Present the data Present the data in Table formin Table form

Dose and flux Dose and flux graphicsgraphics

Spectra TablesSpectra Tables

Spectra graphicsSpectra graphics

3D graphics3D graphics

Fail selectionFail selection

RADOMRADOM--FM.exeFM.exe software is developed by STILsoftware is developed by STIL--BAS and was delivered together BAS and was delivered together with the instrument in middle of September 2007 to ISROwith the instrument in middle of September 2007 to ISRO


Instrument performanceInstrument performance

The solid state detector of RADOM instrument is behind ~ 0.45 The solid state detector of RADOM instrument is behind ~ 0.45 g/cmg/cm22 shielding from front side of 2shielding from front side of 2ππ, which allows direct hits on , which allows direct hits on the detector by electrons with energies in the range 0.85the detector by electrons with energies in the range 0.85--10 MeV. 10 MeV. The protons range is 17.5The protons range is 17.5--200 MeV. On the back 2200 MeV. On the back 2ππ angle where angle where the satellite is the shielding is larger but not known exactly;the satellite is the shielding is larger but not known exactly;RADOM was switched ON about 2 hours after the launch. Since RADOM was switched ON about 2 hours after the launch. Since this moment it works almost permanently. First the resolution wathis moment it works almost permanently. First the resolution was s 10 sec and this was a good decision because no over scaling was 10 sec and this was a good decision because no over scaling was observed in the Earth magnetosphere. Since December 3observed in the Earth magnetosphere. Since December 3thth it it works in 30 sec resolution;works in 30 sec resolution;Inside of the electron radiation belt doses reached 4.10Inside of the electron radiation belt doses reached 4.1044 µµGy.hGy.h--11, , while the fluxes are 1.5.10while the fluxes are 1.5.104 4 cmcm--22.s.s--1 1 ;;Inside of the proton radiation belt doses reached the highest Inside of the proton radiation belt doses reached the highest values of 1.2.10values of 1.2.1055 µµGy.hGy.h--11, while the fluxes are 9.10, while the fluxes are 9.103 3 cmcm--22.s.s--1 1 ;;The galactic cosmic rays (GCR) doses around Earth was about 12 The galactic cosmic rays (GCR) doses around Earth was about 12 µµGy.hGy.h--11. When the satellite was away from the Earth GCR reached . When the satellite was away from the Earth GCR reached 12.2 12.2 µµGy.hGy.h--11. Close to the Moon the doses fall down to about 8.8 . Close to the Moon the doses fall down to about 8.8 µµGy.hGy.h--11;;The total accumulated dose is about 1.3 Gy till 12The total accumulated dose is about 1.3 Gy till 12thth of November of November 2008;2008;


Earth radiation environmentEarth radiation environment


Overview of the near Earth radiation environment Overview of the near Earth radiation environment obtained by obtained by RADOM instrumentRADOM instrument

Chandrayan-1, RADOM, 22 October 2008

18:25 19:25 20:25 21:25 22:25 23:251E-1

1E+0

1E+1

1E+2

1E+3

1E+4

1E+5

1E+6

Dos

e (u

Gy/

h); F

lux

(cm

^-2s

^-1)

D/F

(nG

y.cm

^-2.

p.^-

1)

UTC

020406080100120140160180200220240

Cha

nnel

num

ber

Dose

Flux

D/F

Cou

nts

per c

hann

el

Altitude (km)

Outer (electron)Radiation belt.

Dose = 40000 µGy/hSlot region

Dose = 600 µGy/hPerigee

Dose = 1.2 µGy/h

Inner (proton) Inner (proton) radiation belt. radiation belt.

Dose = = 130000130000 µµGyGy//hh


Variations of the doses, fluxes and spectra shape in near Earth Variations of the doses, fluxes and spectra shape in near Earth spacespace

1.0 10.0Deposited energy (MeV)

1E-3

1E-2

1E-1

1E+0

1E+1

1E+2

1E+3

1E+4

Dep

osite

d D

ose

(uG

y/h)

Chndrayaan-1, RADOM 23 October 2008

000-120

300-360

360-420

420-480

480-500

540-600

600-660

660-720

775-828

835-850

850-856

GCR spectrum

Chandrayan-1, RADOM, 22 October 2008

18:25 18:55 19:25 19:55 20:25 20:55

1E-1

1E+0

1E+1

1E+2

1E+3

1E+4

1E+5

1E+6Dos

e (u

Gy/h)

; Flux (cm

-2s

-1)

D/F (n

Gy.cm

-2.p.-1)

0 180 360 540 720 900Number of measurements

Dose

Flux

D/F

Altitude (km)

UT (hh:mm)

NoiseNoise

The different The different spectra colors spectra colors coded different coded different positions along positions along

the orbitthe orbit

The position of the maximum The position of the maximum along the deposited energy along the deposited energy spectra depends by the type spectra depends by the type and energy of the measured and energy of the measured

dominating particles.dominating particles.

The highest doses of about The highest doses of about 130000 130000 µµGy/h are measured Gy/h are measured

inside of the proton belt, inside of the proton belt, never the less that the never the less that the

highest fluxes are measured highest fluxes are measured inside the electron belt inside the electron belt

As high the area limited by the As high the area limited by the spectrum is, as high the deposited spectrum is, as high the deposited

dose is! dose is!

The red spectrum in the bottom is The red spectrum in the bottom is obtained by GCR particles obtained by GCR particles


The Dose to Flux ratio, (Which is in fact the specific dose The Dose to Flux ratio, (Which is in fact the specific dose per particle.) characterize the type of dominating particlesper particle.) characterize the type of dominating particles

1E-1 1E+0 1E+1 1E+2 1E+3 1E+4Flux (cm^2.s^-1)

1E-1

1E+0

1E+1

1E+2

1E+3

1E+4

1E+5

Dos

e (u

Gu.

h^-1

); D

/F (n

Gy.

cm^2

.p.^

-1)

Dose

D/F

Chandrayaan-1, RADOM 23-26 October 2008

If D/F ratio is above 1 If D/F ratio is above 1 nGy.cmnGy.cm22/part. the dose is /part. the dose is

deposited mainly by protons deposited mainly by protons

Proton belt dosesProton belt doses

Electron belt dosesElectron belt doses

Slot region dosesSlot region doses

If D/F ratio is below 1 If D/F ratio is below 1 nGy.cmnGy.cm22/part. the dose is /part. the dose is

deposited mainly by deposited mainly by electrons*

Perigee GCR dosesPerigee GCR dosesApogee GCR dosesApogee GCR doses

electrons*

*Heffner, 1971.*Heffner, 1971.


Dynamics of the Equivalent dose distribution (H*(10) along Dynamics of the Equivalent dose distribution (H*(10) along the Chandrayaanthe Chandrayaan--1 satellite orbit 1 satellite orbit

1.E-01

1.E+00

1.E+01

1.E+02

1.E+03

1.E+04

1.E+05

1 116 231 346 461 576 691 806 921 1036 1151 1266 1381 1496

Number of measurements

H*(

10);

Hhi

gh; H

low

H*(10) (uSv/h)Hlow (uSv/h)Hhigh (uSv/h)D/F (nGy.cm^2/part.)3 per. Mov. Avg. (Hhigh (uSv/h))3 per. Mov. Avg. (Hlow (uSv/h))3 per. Mov. Avg. (H*(10) (uSv/h))

Elec

tron

bel

t dos

es (H

Elec

tron

bel

t dos

es (H

EB

EB *(

10)

*(10

)

Perig

ee G

CR

dos

esPe

rigee

GC

R d

oses

Begin 26/10/09 01:44:14Begin 26/10/09 01:44:14 End 26/10/09 06:04:14End 26/10/09 06:04:14

Apo

gee

GC

R d

oses

(HA

poge

e G

CR

dos

es (H

CR

B

CR

B *(

10)

*(10

)

Prot

on b

elt d

oses

(HPr

oton

bel

t dos

es (H

PB

PB *(

10)

*(10

)Sl

ot re

gion

dos

esSl

ot re

gion

dos

es

∑∑==

− +=+=256

16

15

2

8 }.5.{10.357.35)10(*i

ii

ihighlowGCR AiAiHHHhighlowPB HHH 3.13.1)10(* +=highlowEB HHH +=)10(*

If D/F ratio is above 1 If D/F ratio is above 1 nGy.cmnGy.cm22/part. the dose is /part. the dose is

deposited mainly by deposited mainly by protons and protons and HHhighhigh have have

major contribution in the major contribution in the equivalent dose H*(10) equivalent dose H*(10)

If D/F ratio is below 1 If D/F ratio is below 1 nGy.cmnGy.cm22/part. the dose is /part. the dose is

deposited mainly by deposited mainly by electrons and electrons and HHlowlow have have

major contribution in the major contribution in the equivalent dose H*(10) equivalent dose H*(10)


Variations of the doses and fluxes in dependence by altitude andVariations of the doses and fluxes in dependence by altitude andby the longitude /UT of the satelliteby the longitude /UT of the satellite

060000

120000

Dose (uGy/h)

010000

20000

Flux (cm^2.s^-1)

456789

2

3

456789

2

3

4

1000

10000

Altit

ude

(km

)

0 2 4 6D/F (nGy.cm^-2/p.)

23/10/2008 03:48:51 - 09:44:55

22

060000

120000

Dose (uGy/h)

010000

20000

Flux (cm^2.s^-1)

456789

2

3

456789

2

3

4

1000

10000

Altit

ude

(km

)

0 2 4 6 8D/F (nGy.cm^-2/p.)

22/10/2008 20:57:30 - 23/10/2008 00:36:57

11

When the magnetic axes is to the right of the When the magnetic axes is to the right of the geographic the satellite is going trough the geographic the satellite is going trough the

center of inner radiation belt

When the magnetic axes is to the left of the When the magnetic axes is to the left of the geographic the satellite is going trough the geographic the satellite is going trough the

periphery of inner radiation belt center of inner radiation belt periphery of inner radiation belt

1 2 3 4 5

-200

201 2 3 4 5

-200

20

Rotational (geographic) axes Rotational (geographic) axes Magnetic axesMagnetic axes

The outer belt doses are practically not affectedThe outer belt doses are practically not affected

Long=Long=--9696°°UT=21:20UT=21:20

Long=156Long=156°°UT=03:50UT=03:50

CRRES dosimeter data 27 Jul 90 to 12 Oct 91. Fennel/Aerospace CoCRRES dosimeter data 27 Jul 90 to 12 Oct 91. Fennel/Aerospace Corp., 2003.rp., 2003.


Explanation of the different doses in proton radiation belt Explanation of the different doses in proton radiation belt on previous slideon previous slide

ChandrayaanChandrayaan--1 orbit1 orbit

Rotational Rotational (geographic) axes(geographic) axes

Magnetic axesMagnetic axes

High dosesHigh doses

Low dosesLow doses

3D picture of the belts is3D picture of the belts iscourtesy of NASAcourtesy of NASA


Comparison of ChandrayaanComparison of Chandrayaan--1 1 -- RADOM spectra withRADOM spectra withISS ISS -- R3DE spectra R3DE spectra

1.0 10.0Deposited energy (MeV)

1E-3

1E-2

1E-1

1E+0

1E+1

1E+2

1E+3

1E+4

Dep

osite

d D

ose

(uG

y/h)

RADOM, PRB

RADOM, ERB

R3DE, ERB

R3DE, PRB

RADOM, GCR

R3DE, GCR

The shape of spectra obtainedThe shape of spectra obtainedby RADOM are same as spectra by RADOM are same as spectra

obtained by R3DE at Int. Space Station obtained by R3DE at Int. Space Station

The RADOM proton radiation belt The RADOM proton radiation belt (PRB)(PRB) spectrum is with same shape as spectrum is with same shape as R3DE spectrum but at about 1.5 order R3DE spectrum but at about 1.5 order of magnitude higher because higher of magnitude higher because higher

flux and respectively dose flux and respectively dose

The RADOM electron radiation belt The RADOM electron radiation belt (ERB)(ERB) spectrum is with same shape as spectrum is with same shape as

R3DE spectrum but about 4 time R3DE spectrum but about 4 time higher level because higher dose higher level because higher dose

The RADOM galactic cosmic rays The RADOM galactic cosmic rays (GCR)(GCR) spectrum practically overlap the spectrum practically overlap the REDE spectrum, because of same flux REDE spectrum, because of same flux

and respectively doses and respectively doses


Moon radiation environmentMoon radiation environment


October 27October 27--28, 2008; Perigee = 348 km28, 2008; Perigee = 348 kmApogee = 164600 km; Period = 73 hoursApogee = 164600 km; Period = 73 hours

AverageAverage GCR Dose = 12.89 mGy/hGCR Dose = 12.89 mGy/h

0

5

10

15

20

25

30

35

40

45

144000 148000 152000 156000 160000 164000

Altitude (km)

Dos

e (u

Gy/

h) Dose (uGy/h)

Flux (cm -2.s -1)

Linear (Dose (uGy/h))

27/10/2008 08:34:14

D (µGy/h)

F (cm-2.s-1)

D/F

H*(10) (µSv/h)

Hlow*(10) (µSv/h)

Hhigh*(10)(µSv/h)

12.89 3.14 1.14 26.48 7.40 19.08

28/10/2008 04:49:26


Comparison of RADOM flux data (10 s. resolution) with Comparison of RADOM flux data (10 s. resolution) with Oulu neutron monitor count rate data (1 min. resolution)Oulu neutron monitor count rate data (1 min. resolution)

Date (dd/dd) UT (hh:mm) 2008

6200

6400

6600

6800

7000

7200

Oul

u ne

utro

n m

onito

r (co

unts

/h)

1.6

2.4

3.2

4.0

4.8

RAD

OM

Flu

x (c

m^-

2.s^

-1)

06/11 11:53 07/11 21:10 09/11 06:24

RADOM flux

Running average fit

Linear fit

Oulu NM counts

Running average fit

Linear fit


Because the increased shielding of the GCR by the Moon body the Because the increased shielding of the GCR by the Moon body the dose and flux levels decrease when Chandrayaandose and flux levels decrease when Chandrayaan--1 satellite 1 satellite

moves closer to the Moon on 9moves closer to the Moon on 9--10.11.200810.11.2008


Comparisons with G. De Angelis model at 1000 km altitudeComparisons with G. De Angelis model at 1000 km altitude

Data Particle Flux = 2.73 cmData Particle Flux = 2.73 cm--22ss--11

Average Data GCR Phys. Dose = 10.02 Average Data GCR Phys. Dose = 10.02 µµGy/hGy/hAverage Data GCR H*(10) Dose = 20.94 Average Data GCR H*(10) Dose = 20.94 µµSv/hSv/h

Model Particle Flux = 3.05 cmModel Particle Flux = 3.05 cm--22ss--11

Average Model GCR Phys. Dose = 11.16 Average Model GCR Phys. Dose = 11.16 µµGy/hGy/hAverage Model GCR H*(10) Dose = 23.36 Average Model GCR H*(10) Dose = 23.36 µµSv/hSv/h


Variations of the RADOM count rate and respectively dose Variations of the RADOM count rate and respectively dose by the altitude above the Moon surfaceby the altitude above the Moon surface

80

90

100

110

120

130

140

150

160

170

180

08/12

/08 15:3

6:0008

/12/08 1

6:48:00

08/12

/08 18:0

0:0008

/12/08 1

9:12:00

08/12

/08 20:2

4:0008

/12/08 2

1:36:00

08/12

/08 22:4

8:0009

/12/08 0

0:00:00

09/12

/08 01:1

2:0009

/12/08 0

2:24:00

09/12

/08 03:3

6:00

Date/Universal Time

(Cou

nts

per 1

0 s.

); (k

m)

CountsAltitude 50 per. Mov. Avg. (Counts)


Comparisons with G. De Angelis model at 100 km altitudeComparisons with G. De Angelis model at 100 km altitude

Data Particle Flux = 2.29 cmData Particle Flux = 2.29 cm--22ss--11

Average Data GCR Phys. Dose = 8.77 Average Data GCR Phys. Dose = 8.77 µµGy/hGy/hAverage Data GCR H*(10) Dose = Average Data GCR H*(10) Dose = 18.5418.54 µµSv/h*Sv/h*

Model Particle Flux = 2.55 cmModel Particle Flux = 2.55 cm--22ss--11

Average Model GCR Phys. Dose = 9.76 Average Model GCR Phys. Dose = 9.76 µµGy/hGy/hAverage Model GCR H*(10) Dose = 20.06 Average Model GCR H*(10) Dose = 20.06 µµSv/hSv/h


ChandrayaanChandrayaan--1 is at 200 km circular orbit since 191 is at 200 km circular orbit since 19thth May 2009 May 2009

Because of smaller shielding from the body of the Moon the dosesBecause of smaller shielding from the body of the Moon the doses rice by rice by more than 2 more than 2 µµGy/h and reach 10.85 Gy/h and reach 10.85 µµGy/hGy/h


The averaged per day RADOM dose around the Moon is The averaged per day RADOM dose around the Moon is rising in linear way in dependence by GCR rising in linear way in dependence by GCR

6650667066906710673067506770679068106830

22/10/2008

01/11/2008

11/11/2008

21/11/2008

01/12/2008

11/12/2008

21/12/2008

31/12/2008

10/01/2009

20/01/2009

30/01/2009

09/02/2009

19/02/2009

01/03/2009

11/03/2009

Date

Ool

u N

M (c

ount

s/m

in.)

CountsLinear (Counts)

8.99

9.19.29.39.49.59.69.79.8

6650 6670 6690 6710 6730 6750 6770

Oulu Neutron Monitor (counts/min.)

RA

DO

M D

ose

( µG

y/h) Dose

Linear (Dose)


Comparison of the R3DE dose rates obtained atComparison of the R3DE dose rates obtained at5.0<L<5.05 with Oulu NM counts/min.5.0<L<5.05 with Oulu NM counts/min.

No No datadata


LongLong--term GCR doses obtained on different satellites term GCR doses obtained on different satellites comparison with Oulu neutron monitor datacomparison with Oulu neutron monitor data

5000

5500

6000

6500

7000

01/01/200001/01/2001

01/01/200201/01/2003

01/01/200401/01/2005

01/01/200601/01/2007

01/01/200801/01/2009

Date (dd/mm/yy)

Oul

u N

M (c

ount

s/m

in)

6.14 6.14 µµGy/hGy/h14.6 14.6 µµSv/hSv/h

7.38 7.38 µµGy/hGy/h16 16 µµSv/hSv/h


12 12 µµGy/hGy/h29.4 29.4 µµSv/hSv/h



Solar minimum GCR doses measured by us in low earth orbit rise tSolar minimum GCR doses measured by us in low earth orbit rise twice wice when the solar activity decline from 2000 to 2009 when the solar activity decline from 2000 to 2009


Comparison of Liulin absorbed dose rates with Oulu neutron monitor count rates


Observations during the first cycle 24 Sun flaresObservations during the first cycle 24 Sun flaresMarch 12March 12--17 200917 2009

Credit: SOHO/MDI

15 March 09 00:58

Daily Sun: 15 Mar 09 Two proto-sunspotsare simmering near the sun's equator

GOES X ray FluxGOES X ray Flux

GOES Electron >2 MeV FluxGOES Electron >2 MeV Flux

GOES Proton FluxGOES Proton Flux

ACE Solar Wind Speed rise from 350 to 540 km/sACE Solar Wind Speed rise from 350 to 540 km/s

GOES Proton and Electron FluxGOES Proton and Electron Flux


Comparison of the RADOM dose/flux data with the GOES10 Comparison of the RADOM dose/flux data with the GOES10 0.50.5-- 4.0 A Xray data4.0 A Xray data

0

5

10

15

20

25

12/03/200900:00:00

13/03/200900:00:00

14/03/200900:00:00

15/03/200900:00:00

16/03/200900:00:00

17/03/200900:00:00

18/03/200900:00:00

Date 2009

Dos

e (u

Gy/

h); F

lux

(#/c

m2 .s)

DoseFlux50 per. Mov. Avg. (Dose)50 per. Mov. Avg. (Flux)

Only the first RADOM Only the first RADOM channel is enhanced, channel is enhanced, which means very low which means very low

energy deposition energy deposition


Comparison of the RADOM dose/flux data with the GOES11 Comparison of the RADOM dose/flux data with the GOES11 >2 MeV Electron flux data>2 MeV Electron flux data

0

5

10

15

20

25

12/03/200900:00:00

13/03/200900:00:00

14/03/200900:00:00

15/03/200900:00:00

16/03/200900:00:00

17/03/200900:00:00

18/03/200900:00:00

Date 2009

Dos

e (u

Gy/

h); F

lux

(#/c

m2 .s

)

DoseFlux50 per. Mov. Avg. (Dose)50 per. Mov. Avg. (Flux)

0

500

1000

1500

2000

2500

3000

3500

4000

2009 03 13 0000 2009 03 14 0000 2009 03 15 0000 2009 03 16 0000Date 2009

GO

ES11

>2

MeV

Ele

ctro

n flu

x(c

ount

s/cm

2.s.

sr)

Only the first RADOM Only the first RADOM channel is enhanced, channel is enhanced, which means very low which means very low

energy deposition energy deposition

Authors thanks to V. Girish who firstAuthors thanks to V. Girish who firstmention the flare data mention the flare data


3 new space experiments are under development3 new space experiments are under development

Liulin Liulin –– Phobos Phobos engineering modelengineering model

LiulinLiulin--PhobosPhobos

Objectives:Objectives: Measurements Measurements during the cruise during the cruise phase, ophase, on Marsn Mars’’s orbits orbit and on the surface of and on the surface of Phobos. Estimation of the radiation doses Phobos. Estimation of the radiation doses received by the spacecraft electronics and received by the spacecraft electronics and assessment the radiation risk to crew of assessment the radiation risk to crew of future exploratory flights to Marsfuture exploratory flights to Mars. .

Cooperation:Cooperation: STIL (Bulgaria), IMBP (Russia), STIL (Bulgaria), IMBP (Russia), NIRS (NIRS (JapanJapan), ), LavochkinLavochkin Space Association, Space Association, RussiaRussia

Phobos Phobos -- SoilSoil samplesample returnreturn apparatusapparatus

Liulin Liulin –– S S engineering modelengineering model

LiulinLiulin--S instrumentS instrumentObjectives:Objectives: Measurements Measurements during the during the descending phase of one descending phase of one ““OrlanOrlan”” type space type space suit suit ““thrownthrown”” from International Space from International Space stationstation..

Cooperation:Cooperation: STIL (Bulgaria), IMBP (Russia), STIL (Bulgaria), IMBP (Russia), LavochkinLavochkin Space Association, RussiaSpace Association, Russia

““OrlanOrlan”” space suitspace suit

BIONBION--M satelliteM satelliteR3DR3D--B3 instrumentB3 instrument

R3DR3D--B3 instrumentB3 instrumentObjectives:Objectives: Measurements Measurements during the about 1 during the about 1 month flight of BIONmonth flight of BION--M satellite around the M satellite around the Earth.Earth.Cooperation:Cooperation: STIL (Bulgaria), IMBP (Russia),STIL (Bulgaria), IMBP (Russia),FAU, Germany,FAU, Germany, LavochkinLavochkin Space Association, Space Association, RussiaRussia


ConclusionsConclusions

RADOM spectrometer proved its availability to characterize the RADOM spectrometer proved its availability to characterize the different radiation fields in the Earth and Moon radiation different radiation fields in the Earth and Moon radiation environment. The proton and electron radiation belts in the Eartenvironment. The proton and electron radiation belts in the Earth h magnetosphere was well recognized. The electron radiation belt magnetosphere was well recognized. The electron radiation belt doses reached 4.104 doses reached 4.104 µµGy/hGy/h, while the fluxes are 15000 #/cm, while the fluxes are 15000 #/cm22.s. .s. The proton radiation belt doses reached the highest values of The proton radiation belt doses reached the highest values of 1.2.105 1.2.105 µµGy/hGy/h, while the fluxes are 9100 #/cm, while the fluxes are 9100 #/cm22.s;.s;

The galactic cosmic rays (GCR) dose rates around Earth was The galactic cosmic rays (GCR) dose rates around Earth was about 12 about 12 µµGy/hGy/h. Away from the Earth GCR reached 13.2 . Away from the Earth GCR reached 13.2 µµGy.hGy.h--11. . At 100 km orbit the doses fall down to about 9.6 At 100 km orbit the doses fall down to about 9.6 µµGy/hGy/h. The rise . The rise of the orbit to 200 km increase the doses to 10.8 of the orbit to 200 km increase the doses to 10.8 µµGy/hGy/h;;

The total accumulated dose during the transfer from Earth to The total accumulated dose during the transfer from Earth to Moon is about 1.3 Gy;Moon is about 1.3 Gy;


AcknowledgementsAcknowledgements

The authors are thankful to all ISRO staff and more specially The authors are thankful to all ISRO staff and more specially to:to:Mr. M. Annadurai, Project Director of ChandrayaanMr. M. Annadurai, Project Director of Chandrayaan--11Prof. J. N. Goswami, Project Scientists of ChandrayaanProf. J. N. Goswami, Project Scientists of Chandrayaan--11Prof. P. Sreekumar, ISRO Space Astron. & Prof. P. Sreekumar, ISRO Space Astron. & InstrumInstrum. Div.. Div.Dr. V. Girish, ISRO Space Astron. & Dr. V. Girish, ISRO Space Astron. & InstrumInstrum. Div.. Div.Eng. V. Sharan, ISRO Space Astron. & Eng. V. Sharan, ISRO Space Astron. & InstrumInstrum. Div.. Div.Dr. J D Rao, ISTRAC/ISRO BangaloreDr. J D Rao, ISTRAC/ISRO Bangalore


Thank youThank you

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