To the adaptive multibody gravity assists tours design
To the adaptive multibody gravity assists tours design in Jovian system for the Ganymede Landing. Grushevskii A.
Keldysh Institute of Applied Mathematics Russian Academy of Sciences 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
ESA- JUICE MISSION
ESA- JUICE Mission Debut Interplanetary part. Ganymede Flyby. JOIG&C-Flyby Sequence GOI
Roskosmos part: +Ganymede Landing S Flexible JOI Data S Flexible G&C-Flyby Sequence S GOI S Ganymede Circular Orbit S Landing
MAIN PROBLEMS -Min Delta V (ballistic scenarios, if it’s possible) -Radiation Doze Accumulation (TILD) -Duration -Min V-infinity relative Ganymede
Roscosmos part: Ganymede Landing. Resonance beginning. Typical scenario Moon Ganymede Ganymede Orbital period of SC after the satellite flyby rated to satellite’s orbital period 6 5 4 3 2. 5 2 Number of rounds after a flyby 1 2 1 ESTK complex of Keldysh IAM RAS Ballistic Center Navigation and Ancillary Information Facility (NAIF) - NASA Refined Flyby Model
Quasi-Singularity of the Radiation Hazard
Joining to Jovian System After Interplanetary Part S Time of Jovian sphere of action 2029/06/03 09: 25: 10 UTC S Flyby hyperbola ( J 2000) S Semimajor axe, km 5252. 572592 S Eccentricity 1. 163115 S Inclination 23. 44 grad S V-Infinity, km/s 4. 91 S Pericenter Time 2029/08/29 17: 20: 35 UTC S Pericenter altitude 12. 5 RJ
1 GAM (near Ganymede) Callisto Europa IO Ganymede Time of minimal distance reaching Minimal distance Height of pericenter of flyby hyperbola Asymptotic velocity Change of velocity relatively to Jupiter Period after flyby of GANYMEDE Distance in pericenter rated to Jupiter’s radius Eccentricity after flyby Velocity in pericenter after flyby Velocity in apocenter after flyby 2030/04/25 12: 55: 52 18. 119618 1000 km 15. 485618 1000 km 6. 794698 -0. 040897 42. 915096 days 11. 503787 0. 767555 16. 511564 2. 171381 Vx=0. 000755, Vy= 0. 005958, Vz=0. 003207, |V|=0. 006808
2 GAM Time of minimal distance reaching Minimal distance Height of pericenter of flyby hyperbola Asymptotic velocity Change of velocity relatively to Jupiter Period after flyby of GANYMEDE Distance in pericenter rated to Jupiter’s radius Eccentricity after flyby Velocity in pericenter after flyby Velocity in apocenter after flyby 2030/06/07 11: 18: 06 13. 702676 1000 km 11. 068676 1000 km 6. 761808 -0. 046064 35. 762581 days 11. 268810 0. 742874 16. 565945 2. 443969 Vx-0. 004218, Vy=0. 002570, Vz=0. 001342, |V|=0. 005118
3 GAM Time of minimal distance reaching Minimal distance Height of pericenter of flyby hyperbola Asymptotic velocity Change of velocity relatively to Jupiter Period after flyby of GANYMEDE Distance in pericenter rated to Jupiter’s radius Eccentricity after flyby Velocity in pericenter after flyby Velocity in apocenter after flyby 2030/08/18 00: 23: 08 9. 464318 1000 km 6. 830318 1000 km 6. 747614 -0. 057707 28. 610065 days 10. 908290 0. 711178 16. 683664 2. 815964 Vx=-0. 014865, Vy=0. 012230, Vz=0. 004934, |V|=0. 019872
4 GAM Time of minimal distance reaching Minimal distance Height of pericenter of flyby hyperbola Asymptotic velocity Change of velocity relatively to Jupiter Period after flyby of GANYMEDE Distance in pericenter rated to Jupiter’s radius Eccentricity after flyby Velocity in pericenter after flyby Velocity in apocenter after flyby 2030/09/15 15: 30: 37 6. 338138 1000 km 3. 704138 1000 km 6. 724214 -0. 078352 21. 457549 days 10. 356952 0. 667801 16. 903565 3. 366919 Vx=-0. 003701, Vy=0. 003109, Vz=0. 001477, |V|=0. 005055
5 GAM Time of minimal distance reaching Minimal distance Height of pericenter of flyby hyperbola Asymptotic velocity Change of velocity relatively to Jupiter Period after flyby of GANYMEDE Distance in pericenter rated to Jupiter’s radius Eccentricity after flyby Velocity in pericenter after flyby Velocity in apocenter after flyby 2030/10/07 02: 25: 05 8. 641858 1000 km 6. 007858 1000 km 6. 746652 -0. 068217 17. 881290 days 9. 929413 0. 640352 17. 120993 3. 753786 Vx=-0. 001707, Vy=0. 005016, Vz=0. 002694, |V|=0. 005944
6 GAM Time of minimal distance reaching Minimal distance Height of pericenter of flyby hyperbola Asymptotic velocity Change of velocity relatively to Jupiter Period after flyby of GANYMEDE Distance in pericenter rated to Jupiter’s radius Eccentricity after flyby Velocity in pericenter after flyby Velocity in apocenter after flyby 2030/11/12 04: 29: 38 6. 051283 1000 km 3. 417283 1000 km 6. 727114 -0. 095345 14. 305032 days 9. 273662 0. 610227 17. 552545 4. 248788 Vx=-0. 006027, Vy=0. 003142, Vz=-0. 000433, |V|=0. 006811
Quasi-Singularity of the Radiation Hazard
Gravity-assist sequence. Effective Type T 1
RADIATION HAZARD PROBLEM (M. Podzolko e. a. , SINP MSU Data)
Typical radiation hazard analysis on the ENDGAME phase Dynamics of the radiation accumulation
Typical radiation hazard analysis on the ENDGAME phase Dynamics of the radiation accumulation- zoom scale
Dynamics of the radiation accumulation- on one orbit. Quasi-singularity Period after flyby of GANYMEDE Distance in pericenter rated to Jupiter’s radius Distance in apocenter rated to Jupiter’s radius 42. 9 days 11. 5 98. 0
Ti (Tisserand’s Criterion) Restricted 3 Body Problem Jacobi Integral J Tisserands Parameter T (see R. Russel, S. Campagnola) “Isoinfine” (“Captivity”)
Tisserand-Poincare graph Rp-T (A. Labunskii, O. Papkov, K. Sukhanov axes Ra-Rp- the same) (N. Strange, J. Sims, K. Kloster, J. Longuski axes
TP-strategy(axes Ra-Rp in RJ )
CB-Classic Billiard Duplex Shutting CGB-Classic Gravitational Billiard
Using PHASE BEAM method of Gravity Assists Sequences Determination
Previous front trees of Tisserand graph for Russian “Laplace” mission
Previous Tisserand Graph for the Roscosmos “Laplace” mission
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”
Rebounds+Re. Rebounds (axes Ra-Rp)
Real Phase Searching(axes Ra-Rp in RJ) Rebounds-Re. Rebounds
“JUICE” by ESA Tisserand-Poincare typical graph
Research basement S Orbit correction algorithm preceding spacecraft’s Jovian moons gravity assists S Gravity assists refined model S ESTK KIAM RAS Ballistic centre complex S Navigation and Ancillary Information Facility (NAIF) - NASA ephemeris — will be refined during JUICE by ESA
Fly-by sequence selection strategy S Lambert problem solution; S The phase-beams method; S Delta V minimizations; S Gravity-assist parameters permanent corrections; S Simulations results are presented.
Gravity-assist sequence. Effective Type T 1
Part II of radiation-comfortable tour
Low-radiation sequence type T 2
Type: Hyper-low-radiation, Expensive Delta V • T 3
«Endgame» (S. Campagnola, R. Russel, 2011)
Virtual Trajectories Splitting After Swing-by
Applications for Another Kinds of Flybys
Callisto & Ganymede S Tour design problem lends itself well to optimization schemes Callisto & Ganymede assists us to minimize fuel requirements
THANK YOU FOR YOUR ATTENTION !
- Slides: 45