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

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

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

Keldysh Institute of Applied MathematicsRussian Academy of Sciences

ESA- JUICE MISSION

ESA- JUICE Mission Debut

Interplanetary part-Ganymede Flyby-JOI-G&C-Flyby SequenceGOI

Roskosmos part: +Ganymede Landing

Flexible JOI Data Flexible G&C-Flyby Sequence GOI Ganymede Circular Orbit Landing

MAIN PROBLEMS

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

Quasi-Singularity of the Radiation Hazard

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

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

2 GAM


Vx-0.004218, Vy=0.002570, Vz=0.001342, |V|=0.005118

3 GAM


Vx=-0.014865, Vy=0.012230, Vz=0.004934, |V|=0.019872


Vx=-0.003701, Vy=0.003109, Vz=0.001477, |V|=0.005055

4 GAM

5 GAM


Vx=-0.001707, Vy=0.005016, Vz=0.002694, |V|=0.005944

6 GAM


Vx=-0.006027, Vy=0.003142, Vz=-0.000433, |V|=0.006811

Quasi-Singularity of the Radiation Hazard

Gravity-assist sequence. Effective Type T1

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)

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 42.9 daysDistance in pericenter rated to Jupiter’s radius 11.5Distance in apocenter rated to Jupiter’s radius 98.0

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”)

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)

TP-strategy(axes Ra-Rp in RJ)

CB-Classic Billiard

Duplex ShuttingCGB-Classic Gravitational Billiard

Using PHASE BEAM method of Gravity Assists Sequences Determination

Previous front trees of Tisserand graphfor 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+ReRebounds (axes Ra-Rp)

Real Phase Searching(axes Ra-Rp in RJ)

Rebounds Rebounds-ReRebounds

“JUICE” by ESA Tisserand-Poincare typical graph

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

Fly-by sequence selection strategy

Lambert problem solution; The phase-beams method; Delta V minimizations; Gravity-assist parameters permanent

corrections; Simulations results are presented.

Gravity-assist sequence. Effective Type T1

Part II of radiation-comfortable tour

Low-radiation sequence type T2

Type: Hyper-low-radiation,Expensive Delta V

• T3

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

Virtual Trajectories Splitting After Swing-by

Applications for Another Kinds of Flybys

Callisto & Ganymede

Tour design problem lends itself well to optimization schemes

Callisto & Ganymede assists us to minimize fuel requirements

THANK YOU FOR YOUR ATTENTION !