An on-orbit super-large deployable space structure system

Abstract

The invention discloses an on-orbit super-large deployable space structure system, comprising: a star body; a plurality of rib bars, which are arranged around the star body and whose first ends are hinged to the star body; a plurality of foldable ring beams, adjacent rib bars There is a ring beam between the second ends of the rib bar, and the second end of the rib bar and the adjacent end of the adjacent ring beam are connected by Hooke hinges; a number of foldable diagonal struts are hinged at both ends. at the second end of the star and the rib rod; a plurality of first unfolding mechanisms, each rib rod is relatively fixed to the star body through one of the first unfolding mechanisms, and the first unfolding mechanism can drive the rib rod to rotate away from the star body to unfold; When: the second ends of several rib rods are close to each other, and the ring beam and the diagonal bracing rod are folded; when unfolding: the first unfolding mechanism drives the rib rod to rotate and unfold, and the rib rod drives the ring beam and the diagonal bracing rod to unfold. The system is small in size and large in area when deployed.

Description

technical field [0001] The invention belongs to the technical field of super-large space structures, and in particular relates to an on-orbit super-large deployable space structure system. Background technique [0002] In the field of space science and military applications, challenging space missions, such as extraterrestrial planetary life detection, electronic reconnaissance and remote sensing detection, are constantly being proposed. [0003] The traditional deployment technology is limited by the kinematic pair of the folding and unfolding mechanism, the thrust of the launch vehicle and the envelope of the fairing, and there are problems such as the complex folding and unfolding mechanism, the low reliability of on-orbit deployment, the large size of the antenna, and the difficulty of low-gravity simulation experiments on the ground. It fully meets the construction requirements of the above-mentioned super-large space structure. [0004] The on-orbit assembly technolog...

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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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