Reconfigurable design method suitable for spacecraft platform system

The invention discloses a reconfigurable design method suitable for a spacecraft platform system, and belongs to the overall technical field of spacecrafts. The method comprises the following steps: establishing a state space model of an energy and time limited system under the condition of an actuator failure; based on task requirements and safety requirements, setting a minimum state envelope which must be recovered by the spacecraft under unit energy consumption, and determining a relationship between a system recoverable state domain and system structure parameters under given energy and time constraints; according to the inscribed ellipsoids and the circumscribed ellipsoids of the recoverable state domain, establishing a relation between a spacecraft reconfigurability quantitative index, namely a reconfigurability degree, and system structure parameters; and optimizing the installation configuration of the spacecraft control mechanism by taking the installation parameter of the control mechanism as a var