Abstract
Foldable and deployable flexible composite thin-walled structures have the characteristics of light weight, excellent mechanical properties and large deformation ability, which means they have good application prospects in the aerospace field. In this paper, a simplified theoretical model for predicting the position of the neutral section of a lenticular deployable composite boom (DCB) in tensile deformation is proposed. The three-dimensional lenticular DCB is simplified as a two-dimensional spring system and a rigid rod, distributed in parallel along the length direction. The position of the neutral cross-section can be determined by solving the balance equations and geometric relations. In order to verify the validity of the theoretical model, a finite element model of the tensile deformation of a lenticular DCB was established. The theoretical prediction results were compared with the finite element calculation results, and the two results were in good agreement.
Highlights
IntroductionThe limitation of vehicle storage space and the demand for the construction of large space structures (such as solar wings, reflector antennas, solar sails, etc.) has promoted research and applications in relation to foldable (deployable) structures
The limitation of vehicle storage space and the demand for the construction of large space structures has promoted research and applications in relation to foldable structures
When the tensile deformation increases, the elastic deformation of the bonding edge can affect the position of the neutral section
Summary
The limitation of vehicle storage space and the demand for the construction of large space structures (such as solar wings, reflector antennas, solar sails, etc.) has promoted research and applications in relation to foldable (deployable) structures. A deployable composite boom (DCB) is a classic flexible structure with excellent mechanical properties. DCBs exhibit large elastic deformation during the entire folding process, and strain energy can be stored while folding. When the DCB needs to be deployed, it can realize the deploying function with the help of an auxiliary mechanism and its own storage of elastic strain energy. Due to its high storage ratio and excellent mechanical properties, the lenticular DCB provides a new technical approach for large-scale deployable aerospace engineering structures [7,8]. In terms of technical realization, it is necessary to perform verification tests of its materials, mechanics, and fabrication, as well as functional and extreme environmental verification in relation to its large deformation function and high deploying performance, the electromechanical integration of the folding/deploying mechanism with flexible characteristics, etc
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