On-orbit ultra-large type deployable space structure system

Abstract

The invention discloses an on-orbit ultra-large expandable space structure system. The system comprises a star body; a plurality of rib rods which are circumferentially arranged with the star body as the center, and have first ends hinged to the star body; a plurality of ring beams which are respectively arranged between second ends of the adjacent rib rods, the second ends of the rib rods being connected with the adjacent ends of the adjacent ring beams through hooke joints; a plurality of foldable diagonal bars of which the two ends are hinged to the star body and the second ends of the corresponding rib rods respectively; and a plurality of first unfolding mechanisms through which the rib rods are relatively fixed to the star body, and which can drive the rib rods to rotate away from the star body so as to be unfolded. During folding, the second ends of the rib rods draw close to one another, and the ring beams and the diagonal bars are folded; and during unfolding, the first unfolding mechanisms drive the rib rods to rotate and unfold, and the rib rods drive the ring beams and the diagonal bars to unfold. The system is small in size and large in area after being unfolded.

Description

technical field [0001] The invention belongs to the technical field of ultra-large space structures, and in particular relates to an on-orbit ultra-large expandable space structure system. Background technique [0002] In the fields of space science and military applications, challenging space missions are constantly proposed, such as extraterrestrial planetary life detection, electronic reconnaissance and remote sensing detection, etc., and there is an urgent need to develop 100-meter-level reflector antennas, planar array antennas, and solar arrays. [0003] The traditional deployment technology is limited by the kinematic pair of the folding mechanism, the thrust of the launch vehicle, and the envelope of the fairing. There are problems such as complex folding mechanism, low reliability of on-orbit deployment, large antenna size, and difficult ground low-gravity simulation experiments. Fully meet the construction requirements of the above-mentioned ultra-large space struc...

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Problems solved by technology

[0005] However, due to the large size and low stiffness of the 100-meter-scale structure, large-scale flexural vibrations are prone to occur during the on-orbit assembly process, which poses a huge challenge to the assembly robot. On the one hand, it affects the positioning accuracy of the robot and reduces the assembly efficiency. On the one hand, it may cause unexpected collision and interference between the robot and the surrounding environment, resulting in failure of the assembly system

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