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No. 27 - Making Progress Towards the Moon

No. 27 - Making Progress Towards the Moon

The spacecraft is now into its 321st orbit, in good status and with all functions performing nominally. The current thrusting strategy is progressing well and one of the longest thrust arcs took place on 9 August at 22:14 for 56.7 hours. The next arc started on 14 August and will last for 39 hours. The thrust strategy has recently been re-optimised in order to take into account the actual engine performance. Long thrust arcs, alternating with short ones, will continue until Moon capture in mid November.

Up to 10 August, and the 262nd engine pulse, the SMART-1 electric propulsion system has cumulated a total ON time of nearly 3000 hr, consumed about 47 kg of Xenon and imparted to the spacecraft a velocity increment of about 2213 ms-1.


The power system performance are good and as expected the power generated by the solar arrays continues to rise since aphelion (4 July), as shown in the graph below which shows the evolution of the power produced by the solar panel since launch.

Power Output from Solar Panels since Launch

Systems Update

This period has been characterised by a change in the thermal environment caused by the EP thrusting strategy and the elongation of the orbit. Some units, like batteries and the star tracker optical heads, have registered high temperatures. This has caused a minor incident resulting in a reconfiguration to the redundant unit. The degradation of the transmitter A has slowed down considerably in the last two months, after a steady degradation for about three months. The cause of the degradation is still unknown and under investigation.

Two Opto-coupler Single Event Upsets (resulting in an engine flame-out) occurred on 20 and 21 July. Some correlation could be identified with recent increased solar activity, although the upsets occurred about 1.5 days in advance. In both cases, the on-board software automatically restarted the engine.

On 30 July, there were fluctuations in the Xenon supply thermothrottle current and several other thruster parameters. The cause of this behaviour is the closed loop control switching between two discrete operating conditions.  This event was first reported in status report 21.

In order to avoid such fluctuations, the EP nominal power setting was reduced from 1358.1W to 1285.3W. As a result, the subsequent thrust pattern has been re-optimised.

Science Update

The first lunar resonance approach is planned on 19 August around 17:25 UT, when the spacecraft will be at 230 000 km geo apocentre and 197 492 km from the Moon. Some payload operations are planned including possible views of part of the far side of the Moon by AMIE (a European first).

AMIE views of the Mediterranean, North East Africa, Middle East and part of India

Click for larger image

AMIE view of the Pacific Ocean: the mosaic is composite of observations through the colour filters and the AMIE clear view channel. One can recognize Australia, New Zealand, but also New-Guinea, Philippines, and Japan under clouds, as well as China at the limb.

Click for larger image

Future Activities

The next lunar resonances are scheduled for 13 September and 13 October. Lunar capture is planned for 15 November, and after EP spiralling down to polar lunar orbit with 300 km perilune and 3000 km apolune, we should start lunar commissioning and lunar science operations in mid-January 2005.

The latest status and first results from SMART-1 were presented during the Lunar session and a dedicated press conference organised at COSPAR Paris on 22-23 July. In particular images obtained from the AMIE camera from Middle East and Mediterranean, as well as of Australia and Pacific were presented. The world space agencies recognised the precursor role of SMART-1 in a fleet of lunar orbiters and landers planned for the next 10 years.

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) 2004/08/09 08:38:45.9

Elements WRT Earth (J2000)
Pericentre Distance (km)

32 428.761276

Apocentre Distance (km)

208 705.391870

Semi Major Axis (km)

120 567.076573



Inclination (deg)


Asc. Node (deg)


Arg. of Pericentre (deg)


True Anomaly (deg)


Osc. Orbital Period (h)


In this diagram the osculating orbits at launch (GTO) and at different times are plotted. The large effects that the operations of the electric propulsion now have on the orbit expansion is clearly visible. Especially the height of the apogee has dramatically increased and now exceeds one third of the Earth Moon distance.

Click for larger version of image

SMART-1 osculating orbit up to 10 August

Since the start of the mission, the electric propulsion system has changed the orbital parameters as follows:

  • The semi-major axis from 24 626 km to 120 567 km
  • The perigee altitude from 656 km to 26 050 km
  • The apogee altitude from 35 880 km to 200 000 km
  • The orbital period from 10 hours 41 minutes to 4 days 19 hours

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

Last Update: 1 September 2019
25-Feb-2024 05:28 UT

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