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Aerospace Instrument-Making

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METHOD OF STABILIZATION A SPACECRAFT IN FUNCTIONAL ORBIT
V.D. Atamasov, I.I. Dementev, A.P. Kovalev, A.N. Ustinov

In modern designs of spacecraft (SC) used large outrigger resilient elements for placing devices and instruments of special and service systems. When SC position control with respect to the center of mass and stabilization in functional orbit arise vibrations of resilient design elements (RDE). We mean that RDE of apparatus is outrigger elements and the body shell. To reduce the influence of oscillatory movements to the resilient elements of the SC in flight mode, cyclograms reserve timeout calming vibrations due dissipative effects, which arising in structural materials of RDE and nodes fixing outrigger elements to the body of apparatus. Redundant time significantly increases the time required to bring the SC into an oriented position and stabilization at the working orbit. The article presents a method of stabilization a spacecraft in functional orbit by controlled damping vibrations of RDE, which reduces the time required to bring the SC into an oriented position and stabilization at the working orbit.
Key words: spacecraft; resilient design element; vibrations on functional orbit; vibration damping system; antiresonance.

Contacts: E-mail: iidementev@mail.ru, E-mail: kbarsenal@kbarsenal.ru, E-mail: arsenal@mzarsenal.spb.ru

Pp. 03-08.

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