In order to fundamentally improve the reconfiguration ability of spacecrafts, reconfigurability should be considered in design stage, and the reconfigurability design method must be involved to guide the system design. The objective of this paper is to construct a reconfigurability design method. First, some basic definitions relating to spacecraft reconfigurability are given. Then, on the basis of function tree, a reconfigurability modeling method is established to describe system's configuration characteristics. Quantitative reconfigurability indexes are further presented and a weak link analysis approach is proposed via the model. In addition, considering reliability constraints, an optimal design method of system configuration is given based on the minimal path set of the reconfigurability model. Finally, the proposed methodology is illustrated and verified in practical analyzing for spacecraft control system. Results show that the method can realize the system configuration design by synthetically considering components, configuration and reconfiguration strategies, and is suitable for the complex system such as spacecrafts.
Reconfigurability design for spacecraft control system based on reliability constraint
01.07.2014
245069 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Modularity, reconfigurability, and autonomy for the future in spacecraft: A review
Elsevier | 2023
|Reconfiguration-Goal-Oriented Control System Reconfigurability
British Library Online Contents | 2010
|MATE switching subsystem - a design for reconfigurability and testability
Tema Archiv | 1983
|Using Design Reconfigurability to Mitigate the Effects of Uncontrolled System Variations
British Library Conference Proceedings | 2010
|Optimization of Excess System Capability for Increased Reconfigurability
British Library Conference Proceedings | 2014
|