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Eclipse Escape
Eclipse Escape
22 Mar 2004
(Source: European Space Agency)

http://sci.esa.int/science-e/www/object/index.cfm?fobjectid=34880

SMART-1
Eclipse Period Over
European Space Agency
March 22, 2004

The spacecraft has passed now completed over 250 orbits, is in good status and with all functions performing nominally. The eclipse season is now over, with the last eclipse occurring on 21 March. The longest eclipse occurred on 13 March (lasted for 2 hours and 15 minutes) and stressed the power systems to their maximum limit. The spacecraft performed extremely well throughout this period and the power and the thermal control systems have been able to overcome this long night without a glitch.

All the autonomous functions on board designed to monitor the eclipse phase and predict the power conditions have also been working very accurately. Now SMART-1 can re-start its journey to the Moon. The thrusting phase has restarted to increase further the orbit apogee. The new strategy involves thrusting around perigee at every revolution for about 8 to 10 hours for the next month. More details on this new strategy will be included in the next report.

Orbital/Trajectory information

The ESOC specialists periodically compute the osculating orbital elements. These elements define the so-called "osculating orbit" which would be travelled by the spacecraft if at that instant all perturbations, including EP thrust, would cease. Therefore, it is an image of the situation at that epoch. In reality, the path travelled by the spacecraft is a continuous spiral leading from one orbit to another. The most recent osculating elements are as follows:

EPOCH (UTC) 2004/03/14 23:11:07.1

Elements WRT Earth (J2000)
Pericentre Distance (km) 20 679.628282
Apocentre Distance (km) 68 788.909158
Semi Major Axis (km) 44 734.268720
Eccentricity 0.537723
Inclination (deg) 6.998998
Asc. Node (deg) 148.668864
Arg. of Pericentre (deg) 215.031401
True Anomaly (deg) 180.023840
Osc. Orbital Period (h) 26.155860

Displayed in the plot are the osculating orbits at launch (GTO) and at different times throughout the mission. Since the start of the mission the electric propulsion engine has changed the orbital parameters as follows:

Semi-major axis of the orbit increased by more than 20 000 km
Perigee altitude from 656 km to 14 305 km
Apogee altitude from 35 844 km to 62 410 km
Orbital period from 10 hours 41 minutes to 26 hours and 10 minutes

Contact Points

Giuseppe Racca
SMART-1 Project Manager
ESA/ESTEC - SCI-PD
Keplerlaan 1- 2200 AG Noordwijk, The Netherlands
E-mail: Giuseppe.Raccaesa.int

Bernard H. Foing
SMART-1 Project Scientist
ESA/ESTEC - SCI-SR
Keplerlaan 1- 2200 AG Noordwijk, The Netherlands
E-mail: Bernard.Foingesa.int

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Last Updated: 25 Mar 2004