为确定高密度泡沫硅橡胶在准静态条件下的本构模型,分析了材料的可压性,进行了拉压试验,根据实验结果利用ABAQUS软件分别拟合了Mooney-Rivlin,N=2的多项式模型、Ogden3模型及Van der Waals 4种本构模型且筛选得出了最佳本构模型,对拉压...为确定高密度泡沫硅橡胶在准静态条件下的本构模型,分析了材料的可压性,进行了拉压试验,根据实验结果利用ABAQUS软件分别拟合了Mooney-Rivlin,N=2的多项式模型、Ogden3模型及Van der Waals 4种本构模型且筛选得出了最佳本构模型,对拉压试验进行了有限元仿真且仿真结果与实测试验进行了比较。结果表明:N=2的多项式本构模型为最佳本构模型。展开更多
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. T...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.展开更多
文摘为确定高密度泡沫硅橡胶在准静态条件下的本构模型,分析了材料的可压性,进行了拉压试验,根据实验结果利用ABAQUS软件分别拟合了Mooney-Rivlin,N=2的多项式模型、Ogden3模型及Van der Waals 4种本构模型且筛选得出了最佳本构模型,对拉压试验进行了有限元仿真且仿真结果与实测试验进行了比较。结果表明:N=2的多项式本构模型为最佳本构模型。
基金Supported by National Natural Science Foundation of China(Grant No.51605001)Joint Funds of the National Natural Science Foundation of China(Grant No.U1637207)Anhui University Research Foundation for Doctor(Grant No.J01003222)
文摘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.
