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.
To improve environmental adaptability, an optical system with passive optical athermalization was designed. This system adopts a transmission structure with a spectral range of 0.4-1.0μm, a focal length of 166mm, a F number of 3.7 and a field view of 5°. An optical system with passive optical athermalization should satisfy three constraints. The first is the power distribution of each lens. The second is the achromatic equation. The last one is the athermal equation. A reasonable optical material combination is obtained by solving the three conditional equations. Then the initial optical system is simulated and optimized by Zemax. In the end, this system gains good imaging quality in the working temperature range of 10-30°C.
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 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.
Analyze the source of stray radiation of the geosynchronous infrared telescope system, and list the methods of suppressing infrared stray radiation. The method of setting the internal optical components ‘field stop heat dissipator’ to suppress the stray radiation of the geosynchronous orbit infrared telescope system. Explain the necessity of using heat dissipator and optimize the internal optical and mechanical structure of the telescope system. Use LightTools software to build a model of the infrared telescope system and perform ray tracing analysis, calculate and compare the point source transmittance (PST) value of the infrared telescope system before and after the suppression measures are taken, and evaluate the effectiveness of the stray radiation suppression measures.
Fiber-coupled laser diodes have become essential sources for fiber laser pumping and direct energy applications. To obtain high power, high brightness semiconductor laser beam output, a 976nm wavelength fiber coupling module with 12 single-emitter laser diodes has been designed using ZEMAX optical design software, and single-emitter has an output power of 10 W with a 105μm wide emission aperture. The core diameter of output fiber is set as 105μm with a numerical aperture (NA) of 0.15. Finally, the simulated result indicates that the module will have an output power over 100W with the brightness of 16.63MW·cm-2·str-1, and the coupling efficiency achieved 85%.
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