status reports 24-June-2019 17:25:56

No. 35 - Final Lunar Orbit & Instrument Lunar Commissioning

14 March 2005

On 27 February, as planned, SMART-1 entered its final lunar orbit [full details below]. During the transfer trajectory the payload instruments had undergone a commissioning phase to enable observations of the Moon to take place. In order to maximise the results from lunar orbit it is, however, necessary to recalibrate the instruments. This consists of taking images and spectra of particularly well known targets and cross correlating observations between SIR, the IR spectrometer and AMIE, the camera. This procedure takes some time, as it is dependent on both the visibility of the target and the correct illumination conditions.

Unfortunately, on starting the calibration program, an anomaly occurred on board. On the night of 28 February the EP engine unexpectedly fired for about 11 hours. The cause was later traced to a recent change in the software and was subsequently corrected.

The consequence of this error is a delay in the completion of the instrument lunar commissioning of a couple of weeks. On 12 March, the ESOC Flight dynamics team commanded the spacecraft to perform an equivalent burn to compensate the unintentional one. By the start of April all the instruments should be tested and calibrated and ready to start collecting valuable science data.

Orbital/Trajectory Information

The following osculating orbital elements have been recently determined by a tracking campaign.

2005/02/28 05:18:39.9

Elements WRT Moon and its equator of date
Pericentre Distance (km)

2208.658559

Apocentre Distance (km)

4618.220201

Semi Major Axis (km)

3413.439380

Eccentricity

0.352952

Inclination (deg)

90.063603

Asc. Node (deg)

236.458625

Arg. of Pericentre (deg)

286.175662

True Anomaly (deg)

180.000024

Osc. Orbital Period (h)

4.970998

The diagram below shows the SMART-1 osculating orbit at several dates during the spiralling in to the final operational orbit.

  • The orbital period is now of slightly less than 5 hours and the inclination almost precisely 90 deg.
  • This orbital period means the spacecraft maintains the same relative position with respect to the Earth ground station.
  • The perilune of around 471 km and argument of 286 deg means the lowest altitude is in the Southern hemisphere at about 74 deg latitude.
  • The apolune altitude is on the opposite side at around 2880 km.
  • The orbital elements will vary during the operational period under the effect of the Earth gravity perturbations. The perilune will slowly decrease to about 300 km and the apolune will increase to about 3000 km, while the argument of perilune will swing around the south pole giving the highest resolution coverage in the southern hemisphere.

SMART-1 osculating orbit up to 14 March 2005

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


    Last Update: 28 August 2006

    For further information please contact: SciTech.editorial@esa.int

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