In order to realize long-term on-orbit running of satellites, space stations, etc spacecrafts, in addition to the long life design of devices, The life of the spacecraft can also be extended by the on-orbit servicing and maintenance. Therefore, it is necessary to keep precise and detailed maintenance of key components. In this paper, a high-precision relative position and attitude measurement method used in the maintenance of key components is given. This method mainly considers the design of the passive cooperative marker, light-emitting device and high resolution camera in the presence of spatial stray light and noise. By using a series of algorithms, such as background elimination, feature extraction, position and attitude calculation, and so on, the high precision relative pose parameters as the input to the control system between key operation parts and maintenance equipment are obtained. The simulation results show that the algorithm is accurate and effective, satisfying the requirements of the precision operation technique.
In order to achieve the rendezvous and capture of the space non-cooperative target, the relative position and pose measurement of non-cooperative target must be resolved. Since the marker is not installed into the non-cooperative target and there is no inter satellite link to transfer the information, so it is very difficult to measure the relative position and pose measurement of non-cooperative target. The solar array connecting frame of non-cooperative targets have their characters and are easy to capture, so the position and pose measurement of specific operation site of non-cooperative target based on stereo vision has been studied in this paper. The method composed of image acquiring, image filtering, edge detection, feature extraction and relative pose measurement. Finally, the relative position and attitude parameters of the solar wing connection were obtained and provided to the control system. The results of simulation and ground verification show that the algorithm is accurate and effective, and can satisfy the technical requirements of the on orbit operation. The measurement approach can be used for engineering implementation.