Strain Monitoring and Installation Adjustment of Satellite–Rocket Connection Device Based on Distributed Optical Fibers
Xiaoxi Qu,
Shiyuan Zhao,
Fuqiang Ma,
Jianle Li,
Hanke Li,
Zhengyan Yang,
Hao Xu,
Lei Yang,
Zhanjun Wu
Affiliations
Xiaoxi Qu
State Key Laboratory of Structural Analysis, Optimization and CAE Software for Industrial Equipment, School of Mechanics and Aerospace Engineering, Dalian University of Technology, Dalian 116024, China
Shiyuan Zhao
School of Optoelectronic Engineering and Instrumentation Science, Dalian University of Technology, Dalian 116024, China
Fuqiang Ma
Dalian Scientific Test & Control Technology Institute, Dalian 116013, China
Jianle Li
State Key Laboratory of Structural Analysis, Optimization and CAE Software for Industrial Equipment, School of Mechanics and Aerospace Engineering, Dalian University of Technology, Dalian 116024, China
Hanke Li
State Key Laboratory of Structural Analysis, Optimization and CAE Software for Industrial Equipment, School of Mechanics and Aerospace Engineering, Dalian University of Technology, Dalian 116024, China
Zhengyan Yang
College of Transportation Engineering, Dalian Maritime University, Dalian 116026, China
Hao Xu
School of Materials Science and Engineering, Dalian University of Technology, Dalian 116024, China
Lei Yang
State Key Laboratory of Structural Analysis, Optimization and CAE Software for Industrial Equipment, School of Mechanics and Aerospace Engineering, Dalian University of Technology, Dalian 116024, China
Zhanjun Wu
School of Materials Science and Engineering, Dalian University of Technology, Dalian 116024, China
In this study, a distributed optical fiber sensor was used for strain monitoring and installation adjustment of a satellite–rocket connection device under a preload. The distributed optical fiber sensor was installed on both the tape and the satellite docking frame, utilizing OFDR (Optical Frequency Domain Reflectometry) based on Backward Rayleigh scattering strain demodulation methods to precisely measure the strain distribution of both components when subjected to a preload. In order to deal with the uneven stress of the belt in the process of preloading, a finite element analysis was performed to obtain the strain distribution of the belt under preloading. The strain monitoring results of the optical fiber and strain gauge were compared, and the strain trend of the finite element simulation results was verified. Finally, the measured strain data were adopted to assist the installation and adjustment of the satellite–rocket connection device to achieve a uniform distribution of the preload. The experimental results showed that the standard deviation of strain at each position of the tape was reduced after adjustment. This study provides guidance for the installation of satellite–rocket connection devices.
