Äîêóìåíò âçÿò èç êýøà ïîèñêîâîé ìàøèíû. Àäðåñ îðèãèíàëüíîãî äîêóìåíòà : http://www.cosmos.ru/conf/2009elw/presentations/presentations_pdf/session2/martynov_ELW.pdf Äàòà èçìåíåíèÿ: Mon Mar 2 19:59:25 2009 Äàòà èíäåêñèðîâàíèÿ: Mon Apr 6 23:52:03 2009 Êîäèðîâêà:

The concept of expedition to Europa, the Jupiter's satellite


Main stages of mission
· · · · · · · · · · Insertion by using of LV "Proton" into a basic circular orbit in height of 200 km; Acceleration by using of USB "Breeze" on an interplanetary trajectory, separation of SC; Flight on Earth-Earth trajectory by using of transport module with electric propulsion system; Earth Gravity assist; Flight to Jupiter by using of transport module with electric propulsion system, TM EPS separation; Braking in sphere Jupiter action and insertion on initial high apogee orbit; Increasing of initial orbit pericenter to radius of orbit Ganimed; Repeated trial flight of galilee satellite for reduction of relative velocity of approach to Europa; Insert into a Europa circular orbit in height of 100 km; Landing

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Scheme of mission
Gravity assistant tour

Insertion into initial orbit ESP separation

Flight on a trajectory the Earth-Jupiter by using ESP

Landing

Gravity assistant

Launch

Flight on a trajectory the Earth-Earth by using ESP

LM OM separation Pericenter increasing

Insertion into Europa orbit

Acceleration on an interplanetary trajectory

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Heliocentric section of flight
The Earth at the moment of arrival to Jupiter 01.01.2022
200

Departure from the Earth 13.12.2017, V=1038 m/s

Earth Gravity Assist, 08.03.2019, V=9100 m/s, h=887 km
0 -200 0 200 400 600 800

Arrival to Jupiter 01.01.2022, V=5544 m/s
-200

End of ESP functioning (2.635 a.u., 668 days)
-400

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Insertion into Jupiter orbit
Increase of a perigee and inclination reduction, V=554 / ra=20 ml.km, rp=900 th.km, i=0°

ra=20 ml.km, rp=100 th.km, i=40°

Cruis trajectory, V=5544 m/s, rp=100 th.km

Insertion into Jupiter orbit, V=445 m/s Gravity Assistant (G1)

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Insertion into Europa orbit
Initial orbit: - Pericenter radius 900 thousand km; - Apocenter radius 20 million km. - Period ~200 days
G1 G2 G3 G4 C1 C2 G5 G6 C3 G7 G8 C4 G9 G10 G11 E1 E2 G12 G13 E3 E4 EOI Moon Ganymed Ganymed Ganymed Ganymed Callisto Callisto Ganymed Ganymed Callisto Ganymed Ganymed Callisto Ganymed Ganymed Ganymed Europa Europa Ganymed Ganymed Europa Europa Europa e e e e Height, km 1500 120 100 100 400 1909 100 1190 3095 958 100 1159 2695 1312 2594 6069 8773 1139 200 1451 1500 V, km/s Period, days rp, RJ 6.65 6.48 6.46 6.4 6.2 6.18 5.04 4.92 5.02 3.66 3.67 3.47 2.64 2.65 2.63 2.36 2.29 1.76 1.76 1.62 1.42 0.57 71.4 28.6 21.5 24.9 33.4 37.7 21.5 19.5 23.9 14.3 13.9 15.1 10.7 7.2 5.6 5.3 5.1 5.7 5.3 5.3 4.7 11.8 11.1 10.7 10.9 12.7 13.3 12.5 12.4 14.1 13.2 13.6 14.4 13.5 11.3 9.0 8.9 8.8 11.0 9.3 9.3 9.3 -

T = 23 Month

e e e e e e e

Manoeuvres 100 m/s Corrections during tour 50 m/s Rendezvous with Europa 145 m/s Insertion into Europa orbit (h = 100 km) 705 m/s Total
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e e

1000 m/s
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Landing onto Europa surface
Braking impulse 17.243 m/s Europa Initial orbit (100 km) Landing orbit (20â100 km)

Main parameters of landing module -Trust - Specific impulse - Initial mass - Mass on surface - Propellant mass 3000 N 220 s 1210 kg 550 kg 660 kg

Total value of characteristic velocity ~1600 m/s
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20

,

Braking and landing

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10

Estimation of stability of a polar circular orbit (h=100 km): ~2 Month ­ without correction maneuvers ; 1 Year ­ 200 m/s.
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5

0 0 50 1 00 150 200 25 0 30 0 3 50 4 00

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Landing scheme

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Flight time-schedule
Stage Launch Earth Gravity assist Arrival to Jupiter Date 13.12.2017 08.03.2019 01.01.2022 January 2022 ­ December 2023 1.3 years 3 years Duration

Flight in system of Jupiter Transfer into an orbit of Europa, flight on an orbit, choice of a place of landing Landing Total

2 years

January - March 2024 March 2024

2 months

6.5 years

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Exploded view of SC

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Spacecraft:: Overview
Name Orbital module Landing module Propulsion system Electroroket Propulsion system Intermediate structure S/C without propellant EPS propellant Propulsion system propellant Landing module propellant S/C with propellant
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Mass, kg 395 550 385 860

70 2260 1435 2005

660 6360

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Orbital module
HGA RTG Realisation of scientific experiments from Europa orbit; Selection of a landing area for a lander; Providing of data relay from a lander to the Earth.

Purpose of the orbital module:

Main engine unit Structure Gyros ST Tank

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Orbital:: Mass budget
Name Structure Propulsion system Radio system HGA, LDA Power system Thermal system Cables Scientific instruments Margin Orbital without propellant Mass, kg 80,2 51,6 7,2 32,2 44 20 20 50 90 395

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Landing module:: Exploded view

Scientific instruments unit Service system unit Landing unit

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Landing module:: Mass budget
Name Propulsion system Control system Radio system Antennas Power system Thermal system Cables Structure Landing unit Scientific instruments Margin Landing module without propellant Mass, kg 167 41 7,2 2,2 44 20 20 119,5 12 70 47,1 550

1 5

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Landing module:: Overview

X Y

Scientific instruments unit Service system unit

RTG

Landing unit

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Landing module:: Service system unit

Radiosystem Gyro Power system

Control system ST
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Propulsion system:: Overview
Tank unit 1

Purpose of propulsion system:
Providing of corrections during interplanetary cruise; Creation of a necessary of braking velocity for insertion into an orbit of Europa.

Trusters

Structure

Tank unit 2 Main egine Gas tank
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Propulsion system:: Mass budget
Name Tank unit Gas tank Main engine structure Valve panel Loading panel Valve unit Tubing Main engine support Truster structure Radiator TA Margin Total
1 9

Mass, kg 215,2 45,8 2 5,5 5 11,1 20 16,8 32 1,1 3,5 25 383

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Radio communication P 2500 Ussuriisk, Transmitter power 10 W
Transmission rate, bit/s LDA link margin, dB HGA link margin, dB Transmission rate, bit/s LDA link margin, dB HGA link margin, dB 4 -12,88 32,82 4 -6,86 38,84 128 -29,08 16,62 128 -23,06 22,64 512 -39,08 6,62 512 -33,08 12,64 32000 -47, 78 -2,08 32000 -41, 76 3,94

P 2500 Ussuriisk, Transmitter power 40 W

1500 MO, Transmitter power 40 W
Transmission rate, bit/s LDA link margin, dB HGA link margin, dB 4 -7,56 38,14 128 -23,76 21,94 512 -33,76 11,94 32000 -42, 46 3,24

ESA, Transmitter power 40 W
Transmission rate, bit/s LDA link margin, dB HGA link margin, dB
2 0

4 -12,56 33,14

128 -28,76 16,94

512 -38,76 6,94

32000 -47, 46 -1,76
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Adoption matrix

FOBOS SAMPLE RETURN

LUNA-RESURS

FOBOS SAMPLE RETURN

2 1

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