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SpaceX
Роскосмос
NASA
СпутникиРНSpaceXРоскосмосNASATo meet the requirements of high precision, high stiffness, and large stowage-to-deployment ratio in space missions, this paper proposes and investigates the design and dynamic simulation of a deployable space telescopic mast unit. Initially, several truss configurations were compared, and a structural performance evaluation was conducted via finite element analysis. A combined structure based on a quadrangular prism truss integrated with cable-stayed elements was identified as the optimal configuration. On this basis, a telescopic screw-driven mechanism was introduced, enabling a compact folded profile while achieving a high deployment ratio. The stowage-to-deployment ratio of a single mast unit reaches 8.3, and the ratio increases proportionally with the number of deployed units. Subsequently, the deployment process of the mast was simulated under microgravity conditions using ADAMS software, focusing on three representative motion profiles: uniform velocity, uniform acceleration, and acceleration–deceleration profiles. The simulation results demonstrate that the uniform velocity profile introduces significant impact loads at the end of deployment; the uniform acceleration profile generates higher end-stage kinetic energy and increased peak driving force; while the acceleration–deceleration profile achieves a maximum driving force of only 12 N, effectively reducing terminal impact and allowing for a smooth release of kinetic energy. The proposed mast unit offers a structurally efficient and dynamically stable solution for space deployable support systems, and provides valuable reference for the structural design and optimization of deployable space structures.
To meet the requirements of high precision, high stiffness, and large stowage-to-deployment ratio in space missions, this paper proposes and investigates the design and dynamic simulation of a deployable space telescopic mast unit. Initially, several truss configurations were compared, and a structural performance evaluation was conducted via finite element analysis. A combined structure based on a quadrangular prism truss integrated with cable-stayed elements was identified as the optimal configuration. On this basis, a telescopic screw-driven mechanism was introduced, enabling a compact folded profile while achieving a high deployment ratio. The stowage-to-deployment ratio of a single mast unit reaches 8.3, and the ratio increases proportionally with the number of deployed units. Subsequently, the deployment process of the mast was simulated under microgravity conditions using ADAMS software, focusing on three representative motion profiles: uniform velocity, uniform acceleration, and acceleration–deceleration profiles. The simulation results demonstrate that the uniform velocity profile introduces significant impact loads at the end of deployment; the uniform acceleration profile generates higher end-stage kinetic energy and increased peak driving force; while the acceleration–deceleration profile achieves a maximum driving force of only 12 N, effectively reducing terminal impact and allowing for a smooth release of kinetic energy. The proposed mast unit offers a structurally efficient and dynamically stable solution for space deployable support systems, and provides valuable reference for the structural design and optimization of deployable space structures.
Authors Yutong Wang and Junjie Li have equally contributed to this chapter.
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Key Laboratory of Space Utilization, Technology and Engineering Center for Space Utilization, Chinese Academy of Sciences, Beijing, 100094, China
Yutong Wang, Junjie Li, Chong Zhao & Ke Wang
University of Chinese Academy of Sciences, Beijing, 100049, China
Yutong Wang & Junjie Li
Authors
Correspondence to Chong Zhao.
School of Mechanical Engineering, Zhejiang University, Hangzhou, Zhejiang, China
Jianrong Tan
School of Mechanical Engineering, Zhejiang University, Hangzhou, Zhejiang, China
Zhenyu Liu
Mechanical Engineering, Zhejiang University, Hangzhou, Zhejiang, China
Weifei Hu
© 2027 The Chinese Mechanical Engineering Society
Wang, Y., Li, J., Zhao, C., Wang, K. (2027). Design and Dynamic Simulation of Deployable Space Telescopic Mast Unit. In: Tan, J., Liu, Z., Hu, W. (eds) Advances in Mechanical Design. ICMD 2025. Mechanisms and Machine Science, vol 206. Springer, Singapore. https://doi.org/10.1007/978-981-95-7904-4_82
Download citationDOI: https://doi.org/10.1007/978-981-95-7904-4_82
Published: 25 June 2026
Publisher Name: Springer, Singapore
Print ISBN: 978-981-95-7903-7
Online ISBN: 978-981-95-7904-4
eBook Packages: Mechanical Engineering (R0)Springer Nature Proceedings excluding Computer Science