2. Galactic Cosmic Rays Galactic Cosmic Rays low flux but highly penetrating Solar Particle Events sporadic, intense & dangerous Radiation Belts high radiation dose 2 Supernova in Crab nebula seen in X-ray by the Chandra mission

3. 3 GCR

4. 4 Inner belt (700-10000 km) Inner belt (700-10000 km) dominated by protons dominated by protons CRAND = Cosmic Ray Albedo Neutron Decay ~static E~100’s MeV E~100’s MeV Outer belt ( ~20000-70000 km) Outer belt ( ~20000-70000 km) dominated by electrons Controlled by “storms” Very dynamic E~ MeV Slot Slot low intensities of MeV electrons occasional injections of more particles

5. 5 Protons Based on data from 1960-1970 Based on data from 1960-1970 Long term averages Long term averages but : outer belt is very stormy ongoing work to update models ongoing work to update models Electrons ISSNavGEO

6. 6

7. 7 Callisto Ganymede Europa Moon Mars

8. 8 Atmospheric depth and composition Atmospheric depth and composition > 95% CO 2, 0.01 Earth’s atmospheric depth Localized crustal magnetic fields Localized crustal magnetic fields (umbrellas) Radiation environment Radiation environment SEP and GCR @ ~1.5 AU Albedo neutrons (modulated by soil composition) No radiation belts “umbrella” electrons and low energy protons

9. 9 soil atmosphere LIP developed dMEREM, a Geant4 based model for the radiation environment on Mars, Phobos and Deimos, including local treatment of surface topography and composition, atmospheric composition and density (including diurnal + annual variations) and local magnetic fields. Most SEPs are degraded in the atmosphere and do not reach the surface! Higher energy GCR reach the surface and originate albedo neutrons, increasing the ambient dose values – need mitigation strategies for longer periods on the surface.

10. The most dangerous mission phase from the point of view of human spaceflight is the interplanetary space travel ! The biggest danger is the possibility of a SEP reaching the mission. Mitigation Strategies are under development: Shelters inside water compartments or other Faster propulsion systems SEP Forecasting tools and alarms 10

11. No Atmosphere No Atmosphere Very weak localized crustal magnetic field Very weak localized crustal magnetic field Radiation environment Radiation environment SEP and GCR @ 1AU SEP and GCR @ 1AU Albedo neutrons (modulated by H2O) Albedo neutrons (modulated by H2O) No radiation belts No radiation belts Measured Neutron spectra (Lunar Prospector) Radiation environment: similar to Mars

12. Europa Ganymede Callisto Io Jupiter 12

13. 13 Synchrotron emission observations & data from Voyagers,PioneerGalileo

14. 14 Jun 2022 Jan 2030 Sep 2032 Jun 2033 11 months 1 month 9 months 11 months 9 months Launch Ariane-5 Jupiter orbit insertion Transfer to Callisto Europa phase: 2 Europa + 2 Callisto flybys Jupiter High Latitude Phase Transfer to Callisto Ganymede Orbit insertion Ganymede tour: Orbits at several altitudes: High altitude 500 km 200km End of nominal mission Next Class-L (Large) ESA Mission Current JUICE mission plan

15. 15 Worst case integral electron flux spectra for worst averaged over 24 h and 20 min. Earth - GEO Jupiter - JUICE Electron Flux #/(cm 2.sr.s) 0.2 MeV5 MeV Jupiter -JUICE~5 x E+7~5 x E+5 Earth - GEO1 x E+7 /4π1 x E+1 /4π

16. 16 Phase A RADEM Model (PSI)

17. 17 eg.Components testing for SEE ASIC TID rad-hard for PT (GAMMA-MEDICA)

18. 18 Proton Telescope 8 Si layers, 8mm Copper shielding) Electron Spectrometer permanent magnet Credits to Wojtec Hadjas & Laurent Desorgher (PSI) @ ESA Space Radiation Workshop, May 2012

19. 19

20. 20 LIP is participating in an european collaboration between scientific institutes (PSI & LIP) and the industry (RUAG, Gamma-medica, EFACEC) in the construction of a proto-flight model of RADEM – a radiation hard monitor to operate in the complex Jovian System.

21. 21

22. 22

23. 23

24. 24 Work sponsored by the ESA Technology Research Programme (http://reat.space.qinetiq.com/marsrem) concluded in 2009http://reat.space.qinetiq.com/marsrem interfaced to SPEs, GCR (p, , ions) and X-rays input flux models to be used by mission designers and planners and by radiation experts web-based and interfaced with existing radiation shielding and effects simulation tools dMEREM : detailed Mars Energetic Radiation Environment Model dMEREM : detailed Mars Energetic Radiation Environment Model eMEREM : engeneering Mars Energetic Radiation Environment Model eMEREM : engeneering Mars Energetic Radiation Environment Model LIP developed dMEREM, a Geant4 based model for the radiation environment on Mars, Phobos and Deimos, including local treatment of surface topology and composition, atmospheric composition and density (including diurnal + annual variations) and local magnetic fields.

25. 25

26. 26 Possible configuration for Scientific Payload accomodation

27. “Depending on their use and their performance, radiation monitoring devices can be classified into 2 general classes and 4 categories. Devices designed for providing in-situ environment data to the host spacecraft: 1.Coarse radiation housekeeping 2.Alert and safeguarding function 3.Support to platform and payload systems Devices designed for providing data usable for engineering models improvement or for general space weather services: 4.Future mission preparation and provision of science data Categories (3) and (4) have quite similar specifications…” The ESCC/CTB Radiation Working Group requirements 27

28. 28

29. 29

30. 30

31. 31 Interaction of Titan's ionosphere with Saturn's magnetosphere. Coates AJCoates AJ. Source Mullard Space Science Laboratory, University College London, Holmbury St Mary, Dorking RH5 6NT, UK. ajc@mssl.ucl.ac.uk Abstract Titan is the only Moon in the Solar System with a significant permanent atmosphere. Within this nitrogen-methane atmosphere, an ionosphere forms. Titan has no significant magnetic dipole moment, and is usually located inside Saturn's magnetosphere. Atmospheric particles are ionized both by sunlight and by particles from Saturn's magnetosphere, mainly electrons, which reach the top of the atmosphere. So far, the Cassini spacecraft has made over 45 close flybys of Titan, allowing measurements in the ionosphere and the surrounding magnetosphere under different conditions. Here we review how Titan's ionosphere and Saturn's magnetosphere interact, using measurements from Cassini low-energy particle detectors. In particular, we discuss ionization processes and ionospheric photoelectrons, including their effect on ion escape from the ionosphere. We also discuss one of the unexpected discoveries in Titan's ionosphere, the existence of extremely heavy negative ions up to 10000amu at 950km altitude

32. 32 PlanetMass (Earths) Rotation (hours) Magnetic Moment (Earths) Axial Tilt and polarity Group Mercury0.0658.6 days1/2500 th ?Terrestrial Venus0.82243 days1/25000 th n/aTerrestrial Earth1.024.01+ 11.3ºTerrestrial Mars0.1124.61/8000 th n/aTerrestrial Jupiter317.809.820000- 9.6ºLarge Gas Giant Saturn95.1610.2600+ 0.1ºLarge Gas Giant Uranus14.5317.250- 58.6ºIcy Giant 17.1516.125- 47.0ºIcy Giant Pluto0.0026.4 days??Terrestrial?

33. 33 AtmosphereMagnetosphere Mercuryresidualyes Venusyesno Earth yes MarsYes ( CO2, depth~15- 20g/cm2) no JupiterGas giantyes

34. 34 Technology Readiness Levels in the European Space Agency (ESA)[4] Technology Readiness Level Description TRL 1.Basic principles observed and reported TRL 2.Technology concept and/or application formulated TRL 3. Analytical & experimental critical function and/or characteristic proof-of- concept TRL 4.Component and/or breadboard validation in laboratory environment TRL 5.Component and/or breadboard validation in relevant environment TRL 6. System/subsystem model or prototype demonstration in a relevant environment (ground or space) TRL 7.System prototype demonstration in a space environment TRL 8. Actual system completed and "Flight qualified" through test and demonstration (ground or space) TRL 9.Actual system "Flight proven" through successful mission operations

35. 35

36. 36 Pre-Phase A, Conceptual Study Phase A, Preliminary Analysis Phase B, Definition Phase C/D, Design and Development Phase E, Operations Phase E1: Launch and Commissionin

37. 37 Models The NASA Galileo Mission data Three models are currently available, see Figure I‐8: The Divine and Garett model which is constructed using data from Pioneer 10 and 11 and which extends to 10 jovian radii RJ for protons and more than 100 RJ for electrons [RD.20]. GIRE (Galileo Interim Electron Environment) based on Galileo and Pioneer electron data between 8 to 16 RJ [RD.83] and developed at ONERA [RN.17] using a physical model. This model has been validated by comparing calculated synchroton radiation with that measured from the ground by the VLA telescope and extends to 10 RJ. JOSE Galileo data and validated with all relevant data measured by spacecraft having flown by or orbited Jupiter, in order to obtain an easy- to-use engineering model for Jupiter's environment. This model has been developed for protons and electrons from several tens of keV to several hundreds of MeV.