In this paper, the spatial positioning technology of off-axis optical elements is studied for the installation and positioning requirements of the off-axis mirror and the anomalous off-axis ellipsoid mirror in an optical system. In this paper, the assembly coordinate system is established according to the global coordinate system of space optical system. The key optical parameters of the optical system are accurately measured and controlled by the theodolite, laser tracker, interferometer and other instruments, so as to realize the precise positioning of the special-shaped off-axis optical element. Secondly, the optical characteristics of the system are analyzed by computer aided setting technology, and the optical misalignment is calculated according to the system wave aberration detection results. Thirdly, the attitude of optical element is adjusted precisely according to the amount of optical misalignment. After many iterations calculation and precision adjustment, the optical index requirements are finally achieved. The spatial positioning method of large size anomalous off-axis optical elements proposed in this paper provides an effective method for the spatial positioning and system assembly of anomalous off-axis optical elements in large aperture optical systems.
In this paper, a mirror with 400mm aperture is taken as the research object. A test system and experimental method for the study of the mechanism of action between the surface shape of the mirror and the actuating force are designed. The system is composed of five parts: optical element, the metering type surface shape control device, a stress-strain testing system, a measuring device for the mirror surface shape and a multi-dimensional translation table. Firstly, the support mode of φ400mm aperture plane mirror is determined by means of optically integrated analysis technique. Secondly, the design of the metrological surface shape control device is completed. The metrological surface shape control device can realize the micro-stress support of the mirror and provide the initial state for the experimental study. At the same time, the actuator component on the back can test and display the driving force in real time. Thirdly, with the mirror shape as the optimization target and the force applied on the back of the mirror as the control variable, the size of the force can be obtained by using the optic-mechanical integrated analysis technology for simulation optimization. In the experiment, the mirror shape can meet the expected requirements by applying the corresponding tension or pressure through the back actuator. In addition, set up a mirror surface shape - promoting the motivation mechanism research and testing system. The research flow of mirror shape regulation mechanism is put forward, through reflection mirror shape detection, the form data processing, and actuating force calculation, and the power, surface shape control effect assessment, through several rounds of iteration calculation and adjustment, realize the regulation and optimization of reflection mirror. The experimental system and method proposed in this paper provide a theoretical basis for the further study of active control technology of large aperture mirror.
In the assembly of space camera, the assembly of large aperture mirror is the key of the system assembly. In this paper, the flexible supported mirror of space camera is taken as the research object, and a process route is proposed to complete the micro-stress assembly of the mirror and the transmission from optical datum to mechanical datum at one time by taking the adhesive assembly of the mirror and the transmission from optical datum to mechanical datum into consideration. According to this process route, the assembly process design and installation platform construction are completed. In addition, the factors affecting the micro-stress assembly of the mirror are analyzed theoretically and experimentally, and the transfer accuracy of the optical-mechanical reference is analyzed. This process method has been successfully applied to the assembly of a space camera's primary mirror. After the assembly, the shape of the primary mirror RMS is less than λ/50, and the Angle between the optical axis and the normal of the structure's mounting surface is less than 10". The process method presented in this paper provides a technical reference for the assembly of similar optical-mechanical systems.
According to the assembly requirements of the space camera's primary and secondary mirror system, this paper proposes the assembly process of carbon fiber truss fuselage's primary and secondary mirror system based on adhesive error compensation technology. The process starts from a system point of view, the adhesive bonding of the truss fuselage was unified with the assembly of the primary and secondary mirror system. The adhesive technology was used to compensate the machining errors of the structural parts, and the adhesive bonding of the truss fuselage and the optical axis consistency assembly of primary and secondary mirror system are realized in the process of one adjustment. According to this assembly process idea, the assembly process of primary and secondary mirror system was designed. Firstly, the optical axis of the primary mirror and the optical axis of the secondary mirror were calibrated by the principle of autocollimation, and the optical axis was guided to the cross reticule as the reference for subsequent installation and adjustment. Secondly, in order to realize this process method, the assembly and adjustment platform of the primary and secondary mirror was designed and built. In addition, the factors that affect the assembly precision of the primary and secondary mirror system are analyzed one by one, and the calculation method of system assembly error is obtained. This assembly method has been successfully applied to a space camera. After assembly, the coaxiality between the optical axis of the primary mirror and the optical axis of the secondary mirror is better than 0.02mm, the Angle between the optical axis is better than 10 ", and the wavefront of the primary and secondary mirror system is close to the optical design index. The assembly method presented in this paper provides a technical reference for the assembly of similar large aperture optical machine system.
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