Reconfigurability analysis method for spacecraft autonomous control

It has become an effective way to introduce reconfigurability design in design phase for improving the ability of spacecraft autonomous control since the precondition of fault processing is that the spacecraft is reconfigurable. In this paper, the reconfigurability analysis method is specially considered for the reconfigurability in design phase. Firstly, some basic definitions related to spacecraft reconfigurability are listed. On the basis of observability and controllability, the reconfigurability criterion is given out. Then, the function tree is built for the research of reconfigurability modeling. Next, the steps of reconfigurability modeling and analysis method based on minimal cut set and minimal path set are presented. After that, the indexes of fault reconfigurable degree and system reconfigurable rate for evaluating the reconfigurability are defined, and the method for analyzing the week links of a system is given out also. Finally, the above analysis method is applied to a spacecraft attitude measuring system. The method in this paper can achieve the quantitative evaluated result of reconfigurability and the weak links of a system, which are conducive for theoretical research for reconfigurability design in design phase of spacecraft.