Structural design of 1 m diameter space mirror component of space camera

Hong, 徐宏 Xu; Ying-jun, 关英俊 Guan

doi:10.3788/ope.20132106.1488

Cited by 5 publications

(3 citation statements)

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“…High specific stiffness, high strength, low density, and mature processing of Titanium alloy (TC4R) is selected for the flexible hinges and supports, while the base plate is made of carbon fiber composite material with high specific stiffness and a low coefficient of linear expansion. The material properties are shown in Table 3 [14]. In this paper, we applied the Finite Element Simulation method to build up the model for three kinds of mirrors with the same thickness of stiffeners (tentatively 4 mm) and carried out a modal analysis.…”

Section: Design Of Support Structurementioning

confidence: 99%

Section: Design Of Support Structurementioning

confidence: 99%

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Design and Evaluation of Flexible Support Based on Space Mirror

Zhu,

Tian,

Liu

et al. 2024

Applied Sciences

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The mirror component is one of the most critical components in the space remote sensing payload, and the performance of its support essentially determines the imaging quality of the system. Mirror components need to have high face shape accuracy, high reliability, and high stability. In this paper, taking the square mirror with the size of 550 mm × 450 mm as an example, we chose the Ultra-Low-Expansion Glass (Corning) as the mirror blank material, and through in-depth research on the principle of the three-point backside support and the engineering realization, we designed a three-point backside flexible support structure applied to the space mirror component. The design results were testified by simulation analysis; the results showed that with the mirror’s weight of 13.2 kg, the surface density can reach 48.5 kg/m2. For each gravity acceleration of 1 g, within the temperature range from 16 to 24 °C, carrying a forced displacement of 5 μm, the RMS value of the mirror component can reach 1/55λ (λ = 632.8 nm), which meets the requirement of high face shape accuracy of the mirror component in space. Finally, the mechanical test was carried out on the assembled mirror component, and the intrinsic frequencies of three directions of the mirror component were obtained through the test: 173.8 Hz, 176.4 Hz and 271.5 Hz, respectively. The changes of the mirror and its support structure were all less than 5″ after the 8 g sinusoidal vibration test and the 5.66 g random vibration test, which indicates that the flexible support structure meets the requirements of the high reliability of the space remote sensing loads and the high accuracy of the space mirror component. It shows that the flexible support structure meets the high reliability and high stability requirements of space remote sensing loads. The theoretical data and test results in this research can provide theoretical references for mirror components of the same size and type.

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Section: Design Of Support Structurementioning

confidence: 99%

Section: Design Of Support Structurementioning

confidence: 99%

Design and Evaluation of Flexible Support Based on Space Mirror

Zhu,

Tian,

Liu

et al. 2024

Applied Sciences

View full text Add to dashboard Cite

show abstract

“…For the space shape, by leveraging the stability of the triangle, the three-point support becomes suitable for application in small and mediumsized aperture (≤Φ500 mm) optical elements. Regarding large aperture (≥Φ500 mm) optical elements, three points or a multiple of three are also used to complete the design of the supporting system [15]. Given the number of support points is calculated as 3.6, we select the three-point support design.…”

Section: Design Of Mirror Support Point Positionmentioning

confidence: 99%

Lightweight Design and Evaluation of Square Reflector

et al. 2023

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In order to reduce the weight of optical elements in space remote sensors while increasing their stiffness, this paper takes an off-axis system secondary mirror as an example to design a square mirror with a size of 500 mm × 500 mm. The mirror adopts ultra-low expansion glass as the raw material. The paper proposed a lightweight form of gradual reinforcement and conducted the mirror assembly simulation analysis. The analysis results show that the weight of the lightweight mirror is 13.6 kg, and the surface density can reach 54.4 kg/m2. Under the circumstances of 1 g gravity and the temperature change of 15 °C~25 °C, the surface shape accuracy of the mirror assembly can reach 1/90λ (λ = 632.8 nm). Through the final testing, the first-order intrinsic frequency of the reflex mirror components is 167.8 Hz. The gap between the test results and the theoretical simulation results is less than 3%, which proves that the mirror assembly in the lightweight form of gradual reinforcement fully meets the index requirements and can provide a theoretical reference for the assembly of a mirror of similar size and type.

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Design of High-lightweight Space Mirror Component Based on Automatic Optimization

Wu¹

2020

J. Phys.: Conf. Ser.

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Aiming at the problems of high weight, low cost and extremely short development cycle faced by commercial aerospace space remote sensing cameras, a mathematical model with modal fundamental frequency as the objective function under the constraints of weight and size has been established. Through the automatic optimization method, the lightening rate of the mirror can reach 71.8%. Using the “2 + 2 + 2” quasi-static constraint as the criterion, the flexible support structure of the mirror is optimally designed to realize the high rigidity of the component and ensure the high bearing capacity of the force and thermal environment. Static simulation analysis of the design results of the mirror assembly using hypermesh shows that under the combined influence of gravity field and temperature field, the change of the mirror surface shape (RMS) is within 0.0056λ. At the same time, the modal analysis of the design results shows that the first-order natural frequency of the component can reach 146.52 Hz, which has extremely high dynamic stiffness. It can effectively adapt to the dynamic environment, and the design of the mirror assembly can fully meet the needs of commercial aerospace space remote sensing cameras.

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Structural design of 1 m diameter space mirror component of space camera

Cited by 5 publications

References 0 publications

Design and Evaluation of Flexible Support Based on Space Mirror

Design and Evaluation of Flexible Support Based on Space Mirror

Lightweight Design and Evaluation of Square Reflector

Design of High-lightweight Space Mirror Component Based on Automatic Optimization

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