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To the adaptive multibody gravity assists tours design in Jovian system for the Ganymede Landing. Grushevskii A.

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Grushevskii A.V., Golubev Yu.F, Koryanov V.V., Tuchin A.G. To the adaptive multibody gravity assist tours design in Jovian system for the Ganymede Landing 24 th International Symphosium on Space Flight Dynamics, May 5-9, 2014 Keldysh Institute of Applied Mathematics Russian Academy of Sciences

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ESA- JUICE MISSION

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ESA- JUICE Mission Debut Interplanetary part- Ganymede Flyby- JOI- G&C-Flyby Sequence GOI

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Roskosmos part: +Ganymede Landing Flexible JOI Data Flexible G&C-Flyby Sequence GOI Ganymede Circular Orbit Landing

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MAIN PROBLEMS

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Roscosmos part: Ganymede Landing. Resonance beginning. Typical scenario ESTK complex of Keldysh IAM RAS Ballistic Center Navigation and Ancillary Information Facility (NAIF) - NASA Refined Flyby Model MoonOrbital period of SC after the satellite flyby rated to satellite’s orbital period Number of rounds after a flyby Ganymede61 52 41 31 2.52.52 21

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Quasi-Singularity of the Radiation Hazard

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Joining to Jovian System After Interplanetary Part Time of Jovian sphere of action 2029/06/03 09:25:10 UTC Flyby hyperbola ( J2000) Semimajor axe, km 5252.572592 Eccentricity 1.163115 Inclination 23.44 grad V-Infinity, km/s 4.91 Pericenter Time 2029/08/29 17:20:35 UTC Pericenter altitude 12.5 RJ

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1 GAM (near Ganymede) Time of minimal distance reaching2030/04/25 12:55:52 Minimal distance18.119618 1000 km Height of pericenter of flyby hyperbola15.485618 1000 km Asymptotic velocity6.794698 Change of velocity relatively to Jupiter-0.040897 Period after flyby of GANYMEDE42.915096 days Distance in pericenter rated to Jupiter’s radius11.503787 Eccentricity after flyby0.767555 Velocity in pericenter after flyby16.511564 Velocity in apocenter after flyby2.171381 Vx=0.000755, Vy= 0.005958, Vz=0.003207, |V|=0.006808 IO Europa Ganymede Callisto

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2 GAM Time of minimal distance reaching2030/06/07 11:18:06 Minimal distance13.702676 1000 km Height of pericenter of flyby hyperbola11.068676 1000 km Asymptotic velocity6.761808 Change of velocity relatively to Jupiter-0.046064 Period after flyby of GANYMEDE35.762581 days Distance in pericenter rated to Jupiter’s radius11.268810 Eccentricity after flyby0.742874 Velocity in pericenter after flyby16.565945 Velocity in apocenter after flyby2.443969 Vx-0.004218, Vy=0.002570, Vz=0.001342, |V|=0.005118

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3 GAM Time of minimal distance reaching2030/08/18 00:23:08 Minimal distance9.464318 1000 km Height of pericenter of flyby hyperbola6.830318 1000 km Asymptotic velocity6.747614 Change of velocity relatively to Jupiter-0.057707 Period after flyby of GANYMEDE28.610065 days Distance in pericenter rated to Jupiter’s radius10.908290 Eccentricity after flyby0.711178 Velocity in pericenter after flyby16.683664 Velocity in apocenter after flyby2.815964 Vx=-0.014865, Vy=0.012230, Vz=0.004934, |V|=0.019872

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Time of minimal distance reaching2030/09/15 15:30:37 Minimal distance6.338138 1000 km Height of pericenter of flyby hyperbola3.704138 1000 km Asymptotic velocity6.724214 Change of velocity relatively to Jupiter-0.078352 Period after flyby of GANYMEDE21.457549 days Distance in pericenter rated to Jupiter’s radius10.356952 Eccentricity after flyby0.667801 Velocity in pericenter after flyby16.903565 Velocity in apocenter after flyby3.366919 Vx=-0.003701, Vy=0.003109, Vz=0.001477, |V|=0.005055 4 GAM

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5 GAM Time of minimal distance reaching2030/10/07 02:25:05 Minimal distance8.641858 1000 km Height of pericenter of flyby hyperbola6.007858 1000 km Asymptotic velocity6.746652 Change of velocity relatively to Jupiter-0.068217 Period after flyby of GANYMEDE17.881290 days Distance in pericenter rated to Jupiter’s radius9.929413 Eccentricity after flyby0.640352 Velocity in pericenter after flyby17.120993 Velocity in apocenter after flyby3.753786 Vx=-0.001707, Vy=0.005016, Vz=0.002694, |V|=0.005944

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6 GAM Time of minimal distance reaching2030/11/12 04:29:38 Minimal distance6.051283 1000 km Height of pericenter of flyby hyperbola3.417283 1000 km Asymptotic velocity6.727114 Change of velocity relatively to Jupiter-0.095345 Period after flyby of GANYMEDE14.305032 days Distance in pericenter rated to Jupiter’s radius9.273662 Eccentricity after flyby0.610227 Velocity in pericenter after flyby17.552545 Velocity in apocenter after flyby4.248788 Vx=-0.006027, Vy=0.003142, Vz=-0.000433, |V|=0.006811

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Quasi-Singularity of the Radiation Hazard

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Gravity-assist sequence. Effective Type T1

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RADIATION HAZARD PROBLEM (M. Podzolko e.a., SINP MSU Data)

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Typical radiation hazard analysis on the ENDGAME phase Dynamics of the radiation accumulation

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Typical radiation hazard analysis on the ENDGAME phase Dynamics of the radiation accumulation- zoom scale

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Dynamics of the radiation accumulation- on one orbit. Quasi-singularity Period after flyby of GANYMEDE42.9 days Distance in pericenter rated to Jupiter’s radius11.5 Distance in apocenter rated to Jupiter’s radius98.098.0

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Ti (Tisserand’s Criterion) Restricted 3 Body Problem Jacobi Integral J Tisserands Parameter T ( see R.Russel, S.Campagnola) “Isoinfine” (“C aptivity”)

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Tisserand-Poincare graph ( N.Strange, J.Sims, K.Kloster, J.Longuski axes Rp-T (A.Labunskii, O.Papkov, K.Sukhanov axes Ra-Rp- the same )

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TP-strategy(axes Ra-Rp in RJ )

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CB-Classic Billiard Duplex Shutting CGB-Classic Gravitational Billiard

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Using PHASE BEAM method of Gravity Assists Sequences Determination

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Previous front trees of Tisserand graph for Russian “Laplace” mission

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Previous Tisserand Graph for the Roscosmos “Laplace” mission

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Phase Selection We need the criterion of selection of encounters for V-infinity reduction The “Magic” code is: “Ganymede”+”Not Ganymede”+”Ganymede” Or “G”^”C”^…^”C”^”G”

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Rebounds+ReRebounds (axes Ra-Rp)

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Real Phase Searching (axes Ra-Rp in RJ) ReboundsRebounds-ReRebounds

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“JUICE” by ESA Tisserand-Poincare typical graph

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Research basement Orbit correction algorithm preceding spacecraft’s Jovian moons gravity assists Gravity assists refined model ESTK KIAM RAS Ballistic centre complex Navigation and Ancillary Information Facility (NAIF) - NASA ephemeris — will be refined during JUICE by ESA

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Fly-by sequence selection strategy Lambert problem solution; The phase-beams method; Delta V minimizations; Gravity-assist parameters permanent corrections; Simulations results are presented.

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Gravity-assist sequence. Effective Type T1

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Part II of radiation-comfortable tour

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Low-radiation sequence type T2

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Type: Hyper-low-radiation, Expensive Delta V T3

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«Endgame» (S.Campagnola, R.Russel, 2011)

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Virtual Trajectories Splitting After Swing-by

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Applications for Another Kinds of Flybys

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Callisto & Ganymede Tour design problem lends itself well to optimization schemes Callisto & Ganymede assists us to minimize fuel requirements

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THANK YOU FOR YOUR ATTENTION !

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