24 th International Symphosium on Space Flight Dynamics, May 5-9, 2014
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Transcript of 24 th International Symphosium on Space Flight Dynamics, May 5-9, 2014
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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
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109
L, RJ
f e, 1/(
cм2
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> 0.5 MэB
> 2
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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
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1 г/cм2
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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 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 !