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.
The sources of different spurious radiation in infrared optical system are analyzed, and the measures to suppress the spurious radiation are listed. Taking the infrared optical system of a detector as an example, the stray radiation of the infrared optical system is suppressed by setting the lyot stop. The optical and mechanical structure model of the infrared optical system was established, and the Monte Carlo method in LightTools software was used for ray tracing analysis. The illuminance of the image plane of the detector after adding lyot stop was obtained, and the point source transmittance (PST) and veiling glare index (V) of the infrared system were calculated, and the effectiveness of the suppression effect was evaluated. At the same time, the background heat radiation of the internal optical and mechanical structure of the infrared optical system is simulated and analyzed. The comprehensive consideration ensures that the imaging quality of the infrared optical system is not affected.
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.
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