Designing and Fabrication of Double Omega Cross-section Carbon Fiber Thin-walled Boom

With the rapid development of aerospace fields such as deep space exploration, satellite communication, and remote sensing, increasingly stringent performance requirements have been imposed on spacecraft platforms and their payloads. On one hand, there is a demand for deploying large-scale, high-precision, and multi-functional structures in harsh space environments (e.g., large antennas, solar arrays, telescope shields, and truss platforms). On the other hand, constrained by the fairing space and payload mass limitations of launch vehicles, these large structures must be kept in a highly compact folded or rolled state during launch, then reliably and accurately deployed in orbit while maintaining required stiffness and surface stability. Traditional metal structures face bottlenecks in achieving high storage ratios (storage volume/unfolded volume) and large-scale lightweight design. In this context, the deployable structure of composite materials has emerged as a promising solution, with the with the double omega-section carbon fiber thin-walled boom gaining attention as a novel space deployable structure. In this study, the geometric dimensions of the double omega cross-section were optimized, and the relationship between the cross-sectional moment of inertia and geometric parameters was established through geometric parameter transformation. Additionally, three distinct fabrication processes for the double omega-section carbon fiber thin-walled booms were proposed and discussed.