The paper deals with the rotational motion stabilization of the AIST small spacecraft prototype under the influence of a magnetic moment. According to the measurements of the Earth’s magnetic field by onboard measuring instruments, the angular velocity of small spacecraft rotation has significantly decreased over several years of active existence in a near-earth orbit. At the same time, attempts to actively control the angular velocity by magnetic executors were unsuccessful. In this investigation, approximate solution regions for the magnetic moment are obtained from the condition of the rotational motion stability around the center of mass of the AIST small spacecraft prototype. These regions can be further analyzed for compliance with the operation of the onboard equipment of a small spacecraft.

The paper deals with the issues of forming and minimizing the target function in the process of creating a small spacecraft for technological purposes. The main difference between such a spacecraft is the need to meet specific requirements for micro-accelerations. These requirements provide favorable conditions for the implementation of gravity-sensitive processes on board a small spacecraft. The constructed objective function allowed us to determine the design appearance of a small spacecraft for technological purposes. The results of the work can be used in the design of small spacecraft.

The paper investigates the dependence of the specific impulse on the temperature of the heater of an electrothermal micro-motor in order to analyze the possibility of its use as a part of a motion control system for a small technological spacecraft. The possibility of using an electrothermal micro-motor for unloading the angular momentum of flywheel motors is considered.

The paper analyzes the design features of a small technological spacecraft justifying the choice of design parameters and modeling the functioning of the spacecraft in terms of micro-acceleration requirements. These requirements are imposed in order to successfully implement gravitationally sensitive technological processes, determine the possibility and feasibility of their implementation and regulate the choice of design parameters, structural layout diagram and executive bodies of the orientation and motion control system of a small technological spacecraft. The experience of designing, creating and operating medium-class technological spacecraft is generalized and analyzed. Common points and differences are identified and discussed. The approaches proposed in the work and the results obtained can be used in the design of small technological spacecraft.

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