Optimization of the stages of unfolding a large-sized space-based reflector

Abstract

The safety of space flights depends on the reliable and smooth unfolding of large parts of the spacecraft. The process of unfolding the elements of a large-sized space-based reflector is considered. Unfolding structures are used in various spacecraft from satellites to inhabited stations. Due to increased interest in large-sized reflectors, the processes of unfolding are considered specifically for such a system. It is demonstrated that the minimization of oscillations of the unfolding structure is important. The fulfillment of this condition improves the reliability of the system. In the process of bringing the unfolding system into the operation state and after its completion, high stresses arise in the structural elements as a result of impacts from the control organ, as well as the mechanisms of restraint and fixation. As a result, oscillations of the entire satellite can occur, leading to a long period of its inactivity. Algorithms for the correction of the control structure parameters have been developed, which in real time allow solving the optimal control problem in the absence of difficulties in convergence, in contrast to the classical methods of the optimal control theory. To unfold the construction, specific actuators and measuring devices have been selected. The distribution laws of random system parameters have been estimated. A prototype facet of a large-sized reflector has been developed. A method based on the Laplace equation for the membrane has been used for pointwise adjustment of the shape of this prototype.