24 th international symphosium on space flight dynamics, may 5-9, 2014
DESCRIPTION
To the adaptive multibody gravity assists tours design in Jovian system for the Ganymede Landing. Grushevskii A. 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. - PowerPoint PPT PresentationTRANSCRIPT
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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
24th International Symphosium on Space Flight Dynamics,May 5-9, 2014
Keldysh Institute of Applied MathematicsRussian 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 SequenceGOI
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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 CenterNavigation and Ancillary Information Facility (NAIF) - NASARefined Flyby Model
Moon Orbital period of SC after the satellite flyby rated to satellite’s orbital period
Number of rounds after a flyby
Ganymede 6 1Ganymede 5 2Ganymede 4 1Ganymede 3 1Ganymede 2.5 2Ganymede 2 1
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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 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 reaching 2030/04/25 12:55:52Minimal distance 18.119618 1000 kmHeight of pericenter of flyby hyperbola 15.485618 1000 kmAsymptotic velocity 6.794698Change of velocity relatively to Jupiter -0.040897Period after flyby of GANYMEDE 42.915096 daysDistance in pericenter rated to Jupiter’s radius 11.503787Eccentricity after flyby 0.767555Velocity in pericenter after flyby 16.511564Velocity in apocenter after flyby 2.171381
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 reaching 2030/06/07 11:18:06Minimal distance 13.702676 1000 kmHeight of pericenter of flyby hyperbola 11.068676 1000 kmAsymptotic velocity 6.761808Change of velocity relatively to Jupiter -0.046064Period after flyby of GANYMEDE 35.762581 daysDistance in pericenter rated to Jupiter’s radius 11.268810Eccentricity after flyby 0.742874Velocity in pericenter after flyby 16.565945Velocity in apocenter after flyby 2.443969
Vx-0.004218, Vy=0.002570, Vz=0.001342, |V|=0.005118
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3 GAM
Time of minimal distance reaching 2030/08/18 00:23:08Minimal distance 9.464318 1000 kmHeight of pericenter of flyby hyperbola 6.830318 1000 kmAsymptotic velocity 6.747614Change of velocity relatively to Jupiter -0.057707Period after flyby of GANYMEDE 28.610065 daysDistance in pericenter rated to Jupiter’s radius 10.908290Eccentricity after flyby 0.711178Velocity in pericenter after flyby 16.683664Velocity in apocenter after flyby 2.815964
Vx=-0.014865, Vy=0.012230, Vz=0.004934, |V|=0.019872
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Time of minimal distance reaching 2030/09/15 15:30:37Minimal distance 6.338138 1000 kmHeight of pericenter of flyby hyperbola 3.704138 1000 kmAsymptotic velocity 6.724214Change of velocity relatively to Jupiter -0.078352Period after flyby of GANYMEDE 21.457549 daysDistance in pericenter rated to Jupiter’s radius 10.356952Eccentricity after flyby 0.667801Velocity in pericenter after flyby 16.903565Velocity in apocenter after flyby 3.366919
Vx=-0.003701, Vy=0.003109, Vz=0.001477, |V|=0.005055
4 GAM
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5 GAM
Time of minimal distance reaching 2030/10/07 02:25:05Minimal distance 8.641858 1000 kmHeight of pericenter of flyby hyperbola 6.007858 1000 kmAsymptotic velocity 6.746652Change of velocity relatively to Jupiter -0.068217Period after flyby of GANYMEDE 17.881290 daysDistance in pericenter rated to Jupiter’s radius 9.929413Eccentricity after flyby 0.640352Velocity in pericenter after flyby 17.120993Velocity in apocenter after flyby 3.753786
Vx=-0.001707, Vy=0.005016, Vz=0.002694, |V|=0.005944
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6 GAM
Time of minimal distance reaching 2030/11/12 04:29:38Minimal distance 6.051283 1000 kmHeight of pericenter of flyby hyperbola 3.417283 1000 kmAsymptotic velocity 6.727114Change of velocity relatively to Jupiter -0.095345Period after flyby of GANYMEDE 14.305032 daysDistance in pericenter rated to Jupiter’s radius 9.273662Eccentricity after flyby 0.610227Velocity in pericenter after flyby 17.552545Velocity in apocenter after flyby 4.248788
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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2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34103
104
105
106
107
108
109
L, RJ
f e, 1/(
cм2
c)
> 0.5 MэB
> 2
> 5
2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34100
101
102
103
104
105
106
L, RJ
Дo
зa, p
aд
/cyт
ки
1 г/cм2
2.2
5
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 GANYMEDE 42.9 daysDistance in pericenter rated to Jupiter’s radius 11.5Distance in apocenter rated to Jupiter’s radius 98.0
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Ti (Tisserand’s Criterion)
212 (1 ) cosJ a e i T
a
Restricted 3 Body ProblemJacobi Integral J Tisserands Parameter T (see R.Russel, S.Campagnola)
2 23(1 ) 3J T v v
“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 ShuttingCGB-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: “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)
Rebounds Rebounds-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 !