Abstract
The paper considers the necessity to develop specialized technological equipment (a weight component compensation system) for ground-experimental testing of the functioning of high-technological large-size transformable reflectors for a spacecraft and their components. A simplified block diagram of the module layout of the weight compensation system with one carriage is presented. A mathematical model of cascade-connected regulation of a control system of a weight component compensation system was developed. An adaptive model has been presented. It determines the more appropriate settings for proportional–integral–derivative (PID-controller) through a fuzzy inference system applicable to test technological large-size transformable reflectors for a spacecraft.
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