FIELD: transport.
SUBSTANCE: invention relates to space engineering, particularly, to spacecraft fixed structural elements electrically connected with spacecraft control system, for example, solar batteries, antennas, moving covers, etc. Proposed device represents loop cable 7 secured by three yokes to solar battery moving part, solar battery drive and rigidly secured on spacecraft body. Yoke 10 divides loop cable 7 into two parts and is rigidly secured to axle 11 fitted in fork 12. Said fork 12 is pivoted to drive support 13 of turn drive. With fork 12 turning in opening the solar battery sections, roll displacement of the section of loop 7 arranged between said first and second yokes is tracked. Yoke 10 revolves about axis perpendicular to form turn axis.
EFFECT: expanded operating performances, longer life.
5 dwg
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