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

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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
Keldysh Institute of Applied MathematicsRussian
Academy of Sciences

• 24th International Symphosium on Space Flight
  Dynamics,
• May 5-9, 2014

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ESA- JUICE MISSION

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ESA- JUICE Mission Debut
Interplanetary part- Ganymede Flyby- JOI- GC-Flyb
y Sequence GOI
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Roskosmos part Ganymede Landing

• Flexible JOI Data
• Flexible GC-Flyby Sequence
• GOI
• Ganymede Circular Orbit
• Landing

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MaiN Problems

• -Min Delta V (ballistic scenarios, if its
  possible)
• -Radiation Doze Accumulation (TILD)
• -Duration
• -Min V-infinity relative Ganymede

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Roscosmos part Ganymede Landing. Resonance
beginning. Typical scenario
Moon Orbital period of SC after the satellite flyby rated to satellites orbital period Number of rounds after a flyby
Ganymede 6 1
Ganymede 5 2
Ganymede 4 1
Ganymede 3 1
Ganymede 2.5 2
Ganymede 2 1
ESTK complex of Keldysh IAM RAS Ballistic
Center Navigation and Ancillary Information
Facility (NAIF) - NASA Refined Flyby Model
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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 action2029/06/03
  092510 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 172035 UTC
• Pericenter altitude 12.5 RJ

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1 GAM (near Ganymede)
Callisto
Europa
IO
Ganymede
Time of minimal distance reaching 2030/04/25 125552
Minimal distance 18.119618 1000 km
Height of pericenter of flyby hyperbola 15.485618 1000 km
Asymptotic velocity 6.794698
Change of velocity relatively to Jupiter -0.040897
Period after flyby of GANYMEDE 42.915096 days
Distance in pericenter rated to Jupiters radius 11.503787
Eccentricity after flyby 0.767555
Velocity in pericenter after flyby 16.511564
Velocity in apocenter after flyby 2.171381
Vx0.000755, Vy 0.005958, Vz0.003207,
V0.006808
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2 GAM
Time of minimal distance reaching 2030/06/07 111806
Minimal distance 13.702676 1000 km
Height of pericenter of flyby hyperbola 11.068676 1000 km
Asymptotic velocity 6.761808
Change of velocity relatively to Jupiter -0.046064
Period after flyby of GANYMEDE 35.762581 days
Distance in pericenter rated to Jupiters radius 11.268810
Eccentricity after flyby 0.742874
Velocity in pericenter after flyby 16.565945
Velocity in apocenter after flyby 2.443969
Vx-0.004218, Vy0.002570, Vz0.001342,
V0.005118
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3 GAM
Time of minimal distance reaching 2030/08/18 002308
Minimal distance 9.464318 1000 km
Height of pericenter of flyby hyperbola 6.830318 1000 km
Asymptotic velocity 6.747614
Change of velocity relatively to Jupiter -0.057707
Period after flyby of GANYMEDE 28.610065 days
Distance in pericenter rated to Jupiters radius 10.908290
Eccentricity after flyby 0.711178
Velocity in pericenter after flyby 16.683664
Velocity in apocenter after flyby 2.815964
Vx-0.014865, Vy0.012230, Vz0.004934,
V0.019872
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4 GAM
Time of minimal distance reaching 2030/09/15 153037
Minimal distance 6.338138 1000 km
Height of pericenter of flyby hyperbola 3.704138 1000 km
Asymptotic velocity 6.724214
Change of velocity relatively to Jupiter -0.078352
Period after flyby of GANYMEDE 21.457549 days
Distance in pericenter rated to Jupiters radius 10.356952
Eccentricity after flyby 0.667801
Velocity in pericenter after flyby 16.903565
Velocity in apocenter after flyby 3.366919
Vx-0.003701, Vy0.003109, Vz0.001477,
V0.005055
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5 GAM
Time of minimal distance reaching 2030/10/07 022505
Minimal distance 8.641858 1000 km
Height of pericenter of flyby hyperbola 6.007858 1000 km
Asymptotic velocity 6.746652
Change of velocity relatively to Jupiter -0.068217
Period after flyby of GANYMEDE 17.881290 days
Distance in pericenter rated to Jupiters radius 9.929413
Eccentricity after flyby 0.640352
Velocity in pericenter after flyby 17.120993
Velocity in apocenter after flyby 3.753786
Vx-0.001707, Vy0.005016, Vz0.002694,
V0.005944
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6 GAM
Time of minimal distance reaching 2030/11/12 042938
Minimal distance 6.051283 1000 km
Height of pericenter of flyby hyperbola 3.417283 1000 km
Asymptotic velocity 6.727114
Change of velocity relatively to Jupiter -0.095345
Period after flyby of GANYMEDE 14.305032 days
Distance in pericenter rated to Jupiters radius 9.273662
Eccentricity after flyby 0.610227
Velocity in pericenter after flyby 17.552545
Velocity in apocenter after flyby 4.248788
Vx-0.006027, Vy0.003142, Vz-0.000433,
V0.006811
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Quasi-Singularity of the Radiation Hazard
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Gravity-assist sequence. Effective Type T1
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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 GANYMEDE 42.9 days
Distance in pericenter rated to Jupiters radius 11.5
Distance in apocenter rated to Jupiters radius 98.0

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Ti (Tisserands Criterion)
Restricted 3 Body ProblemJacobi Integral J
?Tisserands Parameter T (see R.Russel,
S.Campagnola)
Isoinfine (Captivity)
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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 graphfor
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
• GanymedeNot GanymedeGanymede
• Or GCCG

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ReboundsReRebounds (axes Ra-Rp)
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Real Phase Searching(axes Ra-Rp in RJ)

• Rebounds

• Rebounds-ReRebounds

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JUICE by ESA Tisserand-Poincare typical graph
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Research basement

• Orbit correction algorithm preceding spacecrafts
  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 !