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Multi thruster assemblies (Clusters) - are considered as a key technology to create powerful electric propulsion systems for perspective space transportation systems. Operation of a such assembly, interaction between thrusters and between exhaust plasma plumes have some specific, which is not well studied yet and requires dedicated research. In this article results of experimental study of three-thruster assembly, based on D-55 anode layer thruster, are presented. Flexibility of the cluster design and operation in regard to it's size, power supply scheme and propellant management system is studied. Possibility to utilize remote cathode for cluster operation is experimentally demonstrated. Additivity of the thrust and discharge currents of the thruster assembly in a different schemes are studied, and it was demonstrated that resulted thrust value of the cluster in all studied regimes and schemes is summa of individual thrust values in all tested schemes. Sensitivity of the cluster assembly operation to non symmetrical deviation thruster regimes was studied and possibility to vary cluster thrust vector by independent variation of thruster regimes demonstrated. Discharge current oscillations of each thruster and oscillations of the summarized current of three thrusters operating from one common power supply are considered. Observed oscillations were independent in each thruster discharge circuit despite on operation from common power supply. Measured amplitude of common current oscillations is of the same order as one in individual thruster circuit. The results of complex cluster plume characterization using Langmuir probes are presented. The comparison of single thruster plume parameters and cluster ones is carried out. Presence of nonlinear effects in the cluster joint plume was identified based on analysis of calculated and measured joint plume.