GOCE data calibration
A gradiometer and a space-qualified GPS receiver were developed according to the specifications necessary for the high demands of the GOCE mission. Obviously, the technical demands for these instruments are very stringent, and they have been manufactured with the utmost precision. However, in reality instruments are never perfect. The minor differences between the actual instrument and the ideal design on paper are referred to as imperfections. Scientists accept that the accelerometers, the gradiometer and the GPS receiver on GOCE have slight imperfections, as all instruments do, but are able to partly compensate for this using a process of calibration and validation.
A full calibration procedure for GOCE is rather complicated. It is clearest when divided in to several steps, namely calibration activities that take place on ground before the mission on ground, activities that are performed (repeatedly) in-flight during the mission, and post-mission activities. These three steps are known as:
- pre-flight calibration
- internal calibration
- external calibration
'Full calibration' refers to the ensemble of activities in these three steps. All three steps are necessary to obtain the best data product, and should not really be looked at as separate entities.
This calibration step:
- constitutes a first estimate of the so-called common mode rejection ratio (CMRR) and differential mode rejection ratio (DMRR) to the 10-4 level
- makes sure that the accelerometer output is obtained in the required physical units to a certain level of accuracy, say to within 1%.
The CMRR and DMRR refer to the coefficients that account for common mode and differential mode couplings due to imperfections of the gradiometer instrument, like mis-alignments, differential scale-factors, etc.
Pre-flight calibration is performed before the mission, on the ground, using a test-bench. The accelerometers were tested first, then accelerometer pairs mounted on the gradiometer arms and finally the complete assembly. This process basically consists of rocking the accelerometers in a controlled direction on a pendulum bench. The 1-g environment, which is sustained by the vertical, less-sensitive axis, will project over the sensitive perpendicular axes and be measured by them. The differences in these readouts will provide information about the actual alignments of the axes. By rocking in different directions, it will be possible to determine all the ground calibration parameters.
In fact, the biggest difficulty with pre-flight calibration is that the 1 g environment on Earth prevents a proper calibration of the accelerometers since they are designed to operate with the highest accuracy in a 0 g environment. To compensate for this a microgravity test in free fall, utilising a 'drop tower' was also be performed.
During the mission internal calibration is done on board the satellite using the thrusters. A procedure has been designed which makes it possible to first calibrate the thrusters using the (un-calibrated) accelerometer measurements. Then, the procedure continues by activating the calibrated thrusters in a certain mode, which puts a known non-gravitational signal on the accelerometers. The signals of all the accelerometers are then analysed. From the differential mode signals along each arm the internal calibration parameters can be worked out.
More specifically, the internal calibration procedure provides information on relative scale factors and relative misalignments between accelerometer pairs on each arm and on common misalignments of accelerometer pairs on each arm.
External calibration aims to establish that the gradient observations really represent the gradients of the gravity field in Eötvös Units, that remaining unresolved errors are corrected for and that the observations are obtained with the required (or in any case with a known) accuracy. Typically, external data are used in this step, normally in the form of ground data or existing models, hence its name 'external calibration'.
Satellite-to-Satellite Tracking observations
Satellite-to-Satellite Tracking observations (SST) refer to determining the orbit of GOCE using GPS measurements. Gravity field parameters are derived from the combination of the GPS observations and the accelerometer common mode observations. Since GPS is a mature technique for which the instrumentation can be properly calibrated on-ground, the process is reasonably straightforward.
Pre-flight calibration consists of calibration of the GPS receiver. This is done by comparing observations made by the GOCE receiver with other GPS receivers, collocated SLR (Satellite Laser Ranging) ground stations or accurately determined baselines. It is fair to assume that the GPS performance will not be affected significantly by the launch conditions, so that no in-flight internal calibration step will be needed.
Last update: 16 September 2010