With the rapid development of microelectronics, nanotechnology and integrated design concept, the trend of satellite miniaturization is becoming more and more obvious, and the high resolution of small satellites is enhanced, and the capability of remote sensing is the forward position to promote space exploration and technological innovation. For the telephoto optical system, the influence of the spatial thermal environment changes and the change of the gravity field before and after the launch will change the focal length of the optical system, resulting in blurred image, so the need for focusing the focus parts to focus. According to the overall technical requirements of the satellite, a small-scale super-resolution spatial camera system based on the traditional Cass-grain optical system is designed. The modal, sinusoidal vibration and random vibration of the system are simulated by mechanical simulation software. The results shows that the mechanical properties of the system are good. The load has been successfully launched and a good image effect has been achieved.
In order to satisfy the strict requirements of the lightweight ratios and high dimensional stability for space mirror, the design method of lightweight structure and the flexible supporting structure of the primary mirror is proposed. Subsequently, the surface deformations of two different lightweight structures for primary mirror are discussed for analyzing the influence of the mirror weight on its surface. Finally, the finite element models for primary mirror assembly are built for calculating the surface deformation caused by different gravity orientations and various thermal environments. It is proved that the weight, stiffness and surface accuracy of the structure design for primary mirror can meet the engineering requirement.
The position of optical plane for a space remote sensing instrument will be changed in severe launching process and complex working thermal environments, which affects the imaging quality of the remote sensing instrument seriously. based on traditional R-C optical systems designed a new type of initiative thermal controlling focusing device, which was driver by the change of thermal according to the basic concepts of thermal expansion properties, the apparatus selectively adjusting the position of the secondary mirror to compensate for the amount of defocus, analysis the main factors of affecting the accuracy of focusing device, and using finite element analysis software for simulation data, while the device for the corresponding experimental verification according to the actual working environment .The results showed that the focusing device designed to meet the required shaking volume requirement 15."
To regularly evaluate the optical payload performance (geometric, radiometric, and spatial resolution) and the data quality for high-resolution airborne and satellite imaging systems, two new permanent targets (the knife-edge target and the fan-shaped target) made of gravel and with the advantages of year-round availability, lower maintenance operations, and a long lifetime were established in the Academy of Opto-Electronics Baotou site in China. The spectral properties of these targets are investigated in this study. Note that the anisotropy factor at 550 nm for the white gravel is approximately 6%, 12.5% 16.5%, 17.5%, 11.5%, and 5% at the principal plane for the observer zenith angle of 60 deg, 50 deg, 40 deg, 30 deg, 20 deg, and 10 deg (backscatter), respectively. The corresponding value for the gray gravel is 20.8%, 24.8%, 29.4%, 23.8%, 13%, and 3.7%, respectively, and 62.8%, 65.7%, 59.2%, 40.3%, 22.3%, and 9.0%, respectively, for the black gravel. The anisotropy of the black gravel is larger than that of the gray and white gravel areas. The nonuniformity of the target reflectivity is within 2.5%. Furthermore, a calibration for the optical payloads onboard the GF-1 satellite is performed with the knife-edge target, and the uncertainty analysis demonstrates that the uncertainty for this calibration is <2.12% when the relative error for the surface reflectance measurement, the aerosol optical depth, and the total column water vapor are approximately 1%, 10%, and 10%, respectively.