FIELD: spacecraft engineering.
SUBSTANCE: testing of multi-link mechanical system 3 of spacecraft 1 with use of rotary beam system 5 fixed on body 2 connected by suspension springs 7 to links 6 of mechanical system 3 is performed by adjusting forces of tension of springs 7 with providing for setting of upper end 9 of each link 6 of mechanical system 3 in horizontal plane with precision no higher than 0.4° with following opening of links 6 of system 3 with forces of opening dives, exceeding appropriate nominal forces of opening of links 6 of system 3 for no less than 30%.
EFFECT: higher efficiency.
1 dwg
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