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The object to be studied is a spacecraft with a deployable pantograph structure as a solar-battery carrier. The objective of research is to design a mathematical model of this structure taking the elasticity of pantograph elements into account. The Lagrangian formalism is followed. To model the dynamic processes in the system, a software package has been developed, which can be adapted, if necessary, to study deployable structures of other types. The behavior of the structure during deployment, collapse, and redeployment under the action of various perturbations is modeled numerically. Plots illustrating the variation of characteristic variables are presented Introduction. Dynamics of reconfigurable systems is one of the promising and important areas of research in mechanics [1,2,5,[8][9][10][11]. Modern spacecraft incorporate elements that transform when in orbit (solar batteries, gravity-gradient booms, antennas, etc.). Such mechanical systems are delivered into orbit compactly packaged and then are deployed into the operational configuration.Issues of current importance in research of reconfigurable systems are minimization of deployment time and energy and the effect of reconfigurable structures on the motion and attitude of the spacecraft. Also, of vital importance is mass reduction for such systems. Their elements should be considered as elastic bodies.1. Mechanical Model. The object of study is a pantograph structure consisting of two connected parallelogram-type linkages (Fig. 1). The mechanical model is a reconfigurable structure with a pantograph-like deployment mechanism mounted on a rigid body.

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Рассмотрены характеристики излучения апертур в ближней и дальней зонах. Определен диапазон оптимальных расстояний между исследуемой антенной, коллимационным зеркалом и облучателем коллимационного зеркала в безэховой камере. Приведены характеристики коллимационного зеркала и безэховой камеры.