Spatially deployable prism unit for in-orbit assembly

Abstract

The invention discloses a space deployable prism unit for on-orbit assembly. The space deployable prism unit comprises a synchronizing mechanism, an inner cross rod, an outer vertical rod and a central vertical rod, a plurality of synchronizing mechanisms are connected end to end to form an upper ring and a lower ring, the adjacent synchronizing mechanisms in the same ring are folded, unfolded andlimited through connected volute spring hinges, the two rings are connected through outer vertical rods rotationally connected with the synchronizing mechanisms to form a regular hexagonal prism unit, and a center vertical rod is arranged in the center of the regular hexagonal prism unit. The central vertical rod is rotatably connected with the synchronizing mechanisms through foldable inner transverse rods to form a regular hexagonal prism folding and unfolding unit, the three synchronizing mechanisms arranged in the upper ring at intervals are connected with the two obliquely-opposite synchronizing mechanisms in the lower ring through inhaul cables respectively, and the three synchronizing mechanisms arranged in the upper ring at intervals are connected with the lower end of the centralvertical rod through inhaul cables. The deployable prism units are large in folding-unfolding ratio, good in force bearing performance, reliable, stable and good in symmetry, and the connecting rigidity of on-orbit butt joint of the space structure assembling unit can be improved.

Description

technical field [0001] The invention relates to a space expandable mechanism, in particular to a space expandable prism unit for on-rail assembly. Background technique [0002] With the rapid development of space communication, earth observation, deep space exploration, and manned spaceflight, the demand for large-scale, lightweight, and high-geometric stability aerospace space agencies has become very urgent, but limited by the volume of the rocket fairing Due to the limitations of the space structure, it is necessary to design a space structure assembly unit with a large folding-to-expanding ratio, which is in a folded state during the transportation and launch stages, and unfolds into a working state after the spacecraft enters orbit. With the gradual development of the aerospace research program and the escalation of the complexity of the space system, the space expandable mechanism has developed from a simple and single form in the past to a complex, multi-degree-of-fre...

AI Technical Summary

Problems solved by technology

[0003] The research on large-scale deployable satellite antennas has become a key technology in the development of satellites, and the requirements for the antenna diameter are getting higher and higher. The actual use requires stiffness

And how to improve the overall stiffness of the antenna, there is no good solution

Most of the existing ring truss deployable antennas use motors to pull the driving ropes to realize the deployment of the entire mechanism. Although the motor drive can effectively control the deployment speed and reduce the impact vibration during the deployment process, the complex drive mechanism not only increases the structure. The weight also reduces the reliability of the structure, and it is easy to cause the deployable antenna of the ring truss to fail, resulting in the failure of the space exploration mission.

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