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Moon Bound
Moon Bound
28 Oct 2004
(Source: European Space Agency)

On Course for Lunar Capture
European Space Agency
27 Oct 2004

On 25 October SMART-1 fired, for the last time, the electric propulsion engine. This small correction manoeuvre of about 4 hours was necessary to correct the slight over-performance of the engine during the last long burn of 100 hours (10-14 October) during the 'third resonance".

From now on the spacecraft will proceed unpowered in its journey towards the Moon - where it will arrive on 15 November. In the meantime, SMART-1 will perform another two revolutions around the Earth. The last time SMART-1 will approach the Earth, the last perigee, will be on 2 November at 07:28 UTC and finally the last part of the Earth orbit will lead to the capture by the Moon and the first perilune on 15 November at 17:56 UTC.

Up to 26 October, and the 289th engine pulse, the SMART-1 electric propulsion system has cumulated a total ON time of nearly 3648 hr, consumed about 58.8 kg of Xenon and imparted to the spacecraft a velocity increment of about 2737 ms-1. The electric propulsion firing will be resumed only in lunar orbit on 15 November at 05:28 UTC for a 4.5 days long burn, to reduce the lunar orbit.

Orbital/Trajectory information

The osculating orbital elements are periodically computed by the ESOC specialists. 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. So 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) 2004/10/26 06:12:40.9

Elements WRT Earth (J2000)

Pericentre Distance (km) 179 717.893983
Apocentre Distance (km) 305 214.125545
Semi Major Axis (km) 242 466.009764
Eccentricity 0.258791
Inclination (deg) 20.591807
Asc. Node (deg) 24.964145
Arg. of Pericentre (deg) 323.010043
True Anomaly (deg) 179.606049
Osc. Orbital Period (h) 330.053834

In this diagram the osculating orbits at launch (GTO) and at different times are plotted. It can be seen now the huge effect of the combination of the operations of the electric propulsion together with the last Moon encounter have on the orbit expansion. The moon effects is now mainly in the increase of the perigee altitude, in the rotation of the line of apsides (change in argument of perigee) and in the orbital inclination.

Since the start of the mission the orbital elements have been changed by the ion-engine and the lunar resonances as follows:

  • The semi-major axis from 24 626 km to 242 466 km
  • The perigee altitude from 656 km to 173 339 km
  • The apogee altitude from 35 880 km to 300 000 km
  • The orbital period from 10 hours 41 minutes to nearly 14 days

Also note the change in the orbit inclination, which has now reached 20?. As explained in the last report, it was mainly the task of the last resonance to shift the orbit plane of the spacecraft towards the the lunar orbit plane, which is inclined at 28? with respect to the Earth equator (it varies between 28?35' and 18?21' with a period of 18.6 years).

Contact Points

Giuseppe Racca
SMART-1 Project Manager
Keplerlaan 1- 2200 AG Noordwijk, The Netherlands

Bernard H. Foing
SMART-1 Project Scientist
Keplerlaan 1- 2200 AG Noordwijk, The Netherlands

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Last Updated: 28 Oct 2004