KEYWORDS: Staring arrays, Cameras, Flexible circuits, Copper, Resistance, Heatsinks, Control systems, Energy efficiency, Power supplies, Monte Carlo methods
The structure of a space electric cabinet based on a commercial CMOS chip is presented. Analysis is conducted according to the temperature specifications and the environmental constraints, which indicates the partitional thermal control method has higher energy efficiency than conventional TEC cooling. A flexible graphite thermal cable is used to build an independent cooling path for the focal plane component. The camera hood is utilized to cool down the peripheral circuit. Copper sinks are designed for high power electronic components. The thermal control design is verified by finite element simulation analysis and thermal balance test. The experimental results show that the partitional thermal control measures are effective and feasible, which can ensure the -30°C operating temperature of CMOS chip and the derating requirements of components with high power consumption.
In this paper, the lightweight design and analysis of the primary mirror structure for space camera with a diameter of Φ302 mm is carried out. The primary mirror material is glass ceramic and is fixed by peripheral support. It is necessary to minimize the weight of the primary mirror while meeting the complex mechanical conditions during launch and on-orbit. First, through comparative analysis of several lightweight forms, it is determined that the hexagonal honeycomb structure is selected as the final lightweight structural. Secondly, the finite element analysis and Zernike polynomial are used for iterative optimization. Under the condition that the RMS of the primary mirror surface shape accuracy needs to be better than 10 nm, the final result of the primary mirror mass of 5.46 kg and the light weight rate of 30% is obtained. Thirdly, in order to check the environmental adaptability of the primary mirror, statics and dynamics were analyzed. The analysis results show that the structural strength of the primary mirror can withstand 10 g overload acceleration and the first order mode is greater than 500 Hz. Finally, the optical mirror surface of the primary mirror is detected by the interferometer, and the surface shape accuracy RMS is 7.5 nm, which effectively proves the accuracy and reliability of the lightweight design and analysis of the primary mirror. This paper provides ideas and references for the lightweight design of small and medium-caliber mirror structures.
In order to improve the imaging quality of the space target detection camera while minimizing the size of the camera structure and facilitating its attitude control, a retractable lens hood is proposed. The basic structure and design method of the telescopic lens hood are introduced. The use of a retractable lens hood structure to replace the long lens hood in the previous design, optimizes the structure of the system, and greatly reduces the size of the system. Analyze the feasibility of the camera's retractable lens hood and the suppression effect of stray light. Use LightTools software to build a model to analyze the ray tracing of the camera's hood. The results show that the point source transmittance (PST) of the retractable hood is gradually reduced under different off-axis angles. When the off-axis angle is greater than 30°, the PST of the optical system reaches the order of 10-6 , which effectively suppresses the stray light of the system.
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