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Main Structure of the Survey Camera for CSST: A Paradigm for Structural Design of Large-Scale Complex Space Optical Instruments

Gardado en:
Publicado en:Aerospace vol. 12, no. 12 (2025), p. 1036-1062
Autor Principal: Jiang Renkui
Outros autores: Zhang, Ang, Li, Zhaoyang, Liu Enhai, Wang, Libin, Le Sixian, Zhang, Yongchao, Zhang Haini, Wang, Hongyu, Guan Shaohua, Luo Qian, Mao Yufeng, Xu, Weiqi, Chen Panke, Su Haibing, Zhang, Yanqing, Du Junfeng, Shao Junming, Huang Mingzhu, Liang, Wei
Publicado:
MDPI AG
Materias:
China
Load
Thermal stability
Structural engineering
Layers
Verification
Spacecraft components
Carbon fiber reinforced plastics
Optimization
Cameras
Space stations
Structural design
Astronomical instruments
Focal plane devices
Structural strength
Cyanates
Optical instruments
Carbon
Composite materials
Position measurement
Titanium base alloys
Space exploration
Space telescopes
Temperature
Machining
Sensors
Resonant frequencies
Design
Astronauts
Complexity
Design optimization
Vibration tests
Structural stability
Interfaces
Contact angle
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Resumo:As the core observation instrument of the China Space Station Telescope (CSST), the Survey Camera (SC) features large volume, heavy weight and high complexity, which poses considerable challenges to the development of its Main Structure (MST). Focusing on the design, optimization and verification of the MST, this study aims to meet the technical requirements of lightweight, high stiffness, high strength and mechanical stability, and provide high-precision Measurement References (MRs) for components such as the Focal Plane Array (FPA). The MST is an M55J carbon fiber/cyanate ester resin composite framework and incorporates titanium alloy inserts for thread machining. The thickness of carbon fiber plies was optimized using size optimization techniques to maximize structural efficiency. The carbon fiber plies and embedded parts along the structural force transmission path were strengthened to improve structural strength. A spherically mounted retroreflector (SMR)–cube mirror composite MR system was employed, along with a contact–non-contact integrated measurement scheme, achieving a position and angle measurement uncertainty of 5.26 μm/5.53″ (3σ). Through experimental verification, the final mass of the MST was controlled at 66.8 kg, and the fundamental frequency reached 120.6 Hz. After assessment via vibration tests and thermovacuum tests, the strength, mechanical stability, and thermal stability of the structure all met the mission requirements.
ISSN:2226-4310
DOI:10.3390/aerospace12121036
Fonte:Advanced Technologies & Aerospace Database