In order to solve the problem of push-broom optical camera’s imagery quality difficult to content request which windows size is too large, the author proposed a kind of project for camera’s following windows. The author analysed the characteristic of the push-broom optical camera’s windows, and proposed the ideal model of the push-broom optical camera’s windows. Simultaneously, analyzed the transformational rule of the windows’ location and size in the ideal condition. The author proposed the design project of the push-broom optical camera’s following windows according to the result of the ideal windows’ analysis, and performed an analysis of kinematics simultaneously. Finally, the author designed and analyzed kinematics for the following windows in allusion to a certain push-broom optical camera. According the analysis result, this project could decrease a half size of the light opening area compare with the current technique. It could decrease the stray light’s influence of the camera’s imagery quality, the following windows move smoothly, and this project could be satisfied to the requirements of engineering use.
To reduce the surface deformation of a star tracker reflector in a complex and execrable environment, a micro stress flexible support structure was designed according to the circular optical reflector subassembly. By defining the thickness, width and radius as design variables, the flexible hinge in an circular reflector subassembly was optimized. Then, the surface figure precision, structural strength and dynamic stiffness of the reflector subassembly in the thermal-structural coupling state were analyzed with the finite element method. Simulation results show that the natural frequency of the reflector is enough, which has a sufficiently high dynamic stiffness. Both surface precision RMS of the reflector (8.34nm, 9.26nm) have reached the index requirements of the optical system (λ/10, λ=632.8nm) under gravity and uniform temperature change from -20℃ to 65℃. The results show that the design for the micro stress flexible support structure is reasonable and feasible, and achieves the design goal.
Space sensors are used in navigation sensor fields. The sun, the earth, the moon and other planets are used as frame of reference to obtain stellar position coordinates, and then to control the attitude of an aircraft. Being the “eyes” of the space sensors, Optical sensor system makes images of the infinite far stars and other celestial bodies. It directly affects measurement accuracy of the space sensor, indirectly affecting the data updating rate. Star sensor technology is the pilot for Space sensors. At present more and more attention is paid on all-day star sensor technology. By day and night measurements of the stars, the aircraft’s attitude in the inertial coordinate system can be provided. Facing the requirements of ultra-high-precision, large field of view, wide spectral range, long life and high reliability, multi-functional optical system, we integration, integration optical sensors will be future space technology trends. In the meantime, optical technologies for space-sensitive research leads to the development of ultra-precision optical processing, optical and precision test machine alignment technology. It also promotes the development of long-life optical materials and applications. We have achieved such absolute distortion better than ±1um, Space life of at least 15years of space-sensitive optical system.