Abstract
Because of the limited space of the launch rockets, deployable mechanisms are always used to solve the phenomenon. One dimensional deployable mast can deploy and support antenna, solar sail and space optical camera. Tape-spring hyperelastic hinges can be folded and extended into a rod like configuration. It utilizes the strain energy to realize self-deploying and drive the other structures. One kind of triangular prism mast with tape-spring hyperelastic hinges is proposed and developed. Stretching and compression stiffness theoretical model are established with considering the tape-spring hyperelastic hinges based on static theory. The finite element model of ten-module triangular prism mast is set up by ABAQUS with the tape-spring hyperelastic hinge and parameter study is performed to investigate the influence of thickness, section angle and radius. Two-module TPM is processed and tested the compression stiffness by the laser displacement sensor, deploying repeat accuracy by the high speed camera, modal shape and fundamental frequency at cantilever position by LMS multi-channel vibration test and analysis system, which are used to verify precision of the theoretical and finite element models of ten-module triangular prism mast with the tape-spring hyperelastic hinges. This research proposes an innovative one dimensional triangular prism with tape-spring hyperelastic hinge which has great application value to the space deployable mechanisms.
Highlights
Conventional articulated truss structures are composed of mechanical hinges which can meet accuracy and stiffness requires of space mission
Yang et al [24, 25] optimized the geometric parameters of Tape-spring hyperelastic (TSH) hinge to improve driving moment and reduce deploying impact, and established two different theoretical models to analyze the stability of deployment status for the TSH hinges
This paper proposed a new ten-module triangular prism mast (TPM) with TSH hinges
Summary
Conventional articulated truss structures are composed of mechanical hinges which can meet accuracy and stiffness requires of space mission. Those structures have some disadvantages, such as large weight, high friction and energy-wasting features. (2018) 31:33 hyperelastic hinge rope triangular frame drive pipe are performed to verify the accuracy of the static theoretical models of the TPM. Finite element model of tenmodule TPM are establish by ABAQUS and geometrical parameter study are analyzed for bending and twisted modal frequencies. Yang et al [24, 25] optimized the geometric parameters of TSH hinge to improve driving moment and reduce deploying impact, and established two different theoretical models to analyze the stability of deployment status for the TSH hinges.
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