光学成像空间碎片探测载荷优化设计

A multidisciplinary co-design scheme integrating optical， mechanical， thermal and computational disciplines is proposed to meet the demand of CubeSats for low-cost optical payloads for space debris detection. With the minimum total system mass as the optimization objective，the payload is designed and developed under the constraint of satisfying detection performance，which is capable of detecting 1 cm-scale space debris at the distance of 80 km. The optical system adopts a lightweight Mangin catadioptric optical path，and an opto-mechanical integrated design is applied to achieve small volume and high image quality. For the structural part，topology and numerical optimization are combined to reduce the structural mass by 45. 8%，with the structural mass ratio of the whole payload dropped to 47. 2%. A fully passive thermal control scheme is adopted for thermal design，and the maximum internal temperature difference of the system is controlled within 6 ℃ by combining thermo-mechanical integrated design. In addition，image processing algorithms are used to compensate for the aberrations caused by low-cost optical design，balancing performance，efficiency and cost. During the development phase，the payload passes the mechanical simulation test of a launch vehicle. Thermal topology optimization ensures the CMOS works within the allowable temperature range，and the thermal simulation results verify the optical performance. The algorithms effectively correct optical and assembly errors，and realize star map recognition. The final payload has a total mass of 886 g. In ground tests，it can observe up to magnitude 11. 7 with an exposure time of 0. 2 s，and the mean angular distance residual is 5. 8 arcsec.