Evaluation of Quasi-State Component in Acceleration on Board the Earth Artificial Satellite

Two techniques for determining quasi-state component in acceleration on board the orbiter are considered. The first technique consists in digital filtering SAMS data, the other one reduces to rather accurate mathematical modelling of orbiter attitude motion on the base of information about real orbiter orientation and calculating for simulated motion the accelerations at given on board points. The results obtained by these techniques are compared for four periods of orbiter free drift in STS-60 mission. Durations of these periods are within 1 to 4 hours. During these periods the orbiter was in single-axis gravitational orientation. For the SAMS head C and the structural axis x the results obtained by different ways coincide with error about 50 per cent and in others cases discordance is greater.