Thermally-induced vibration analysis of tensegrity modules during space deployment using dynamic stiffness method

Tensegrity is an ideal structural form for the modular assembly of ultra-large spacecraft. Understanding the dynamics of tensegrity modules during deployment under thermal effects is crucial for successful space deployment. In this paper, a space deployment dynamics model for tensegrity modules that incorporates dynamic stiffening and space thermal effects is developed using a rotating Bernoulli-Euler beam. The dynamic stiffness method is introduced to obtain numerically accurate solutions for the system's modal characteristics and dynamic response under space thermal effects. The deviation between the fundamental frequency and the finite element solution is within 1 & PTSTHOUSND;, and the maximum displacement deviation is 3%, confirming the accuracy of our method. Parametric analysis reveals that as the deployment speed increases, the frequency of the tensegrity modules' compression bars gradually increases, and an exchange between transverse and longitudinal modes occurs. Moreover, increasing the initial force and the angle of heat flow incidence leads to higher response amplitudes in the compression bars of tensegrity modules. This analysis reveals the dynamic evolution of tensegrity module space deployment under thermal effects.

Automated summary

In this study, a dynamics model based on rotating Bernoulli-Euler beam is developed to investigate the space deployment dynamics of tensegrity modules under thermal effects. The dynamic stiffness method is used to obtain accurate numerical solutions for the system's modal characteristics and dynamic response. Parametric analysis reveals the dynamic evolution of tensegrity module space deployment under thermal effects.