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ABSTRACT: We describe the results of determining the mass of the International Space Station using the data of MAMS accelerometer taken during correction of the station orbit on August 20, 2004. The correction was
made by approach and attitude control engines (ACE) of the Progress transporting spacecraft. The engines were preliminary calibrated in an autonomous flight using the onboard device for measuring
apparent velocity increment. The method of calibration is described and its results are presented. The error in station mass
determination is about 1%. The same data of MAMS and similar data obtained during the orbit correction on August 26, 2004
were used for the analysis of high-frequency vibrations of the station mainframe caused by operation of the ACE of Progress. Natural frequencies of the ACE are determined. They lie in the frequency band 0.024–0.11 Hz. ACE operation is demonstrated
to result in a substantial increase of microaccelerations onboard the station in the frequency range 0–1 Hz. The frequencies
are indicated at which disturbances increase by more than an order of magnitude. The study described was carried out as a
part of the Tensor technological experiment.
Cosmic Research 04/2012; 47(2):173-184. · 0.39 Impact Factor
