Reliability evaluation method and device for spacecraft attitude control system under hybrid redundancy strategy

Abstract

This invention proposes a reliability assessment method and apparatus for spacecraft attitude control systems under a hybrid redundancy strategy. The actuators in the spacecraft attitude control system are a centrally located system. A hybrid redundancy strategy is employed to configure the thrusters within the actuators. The failure times of each thruster are independent and follow different distributions. Each thruster is divided into active redundancy units and cold standby redundancy units. A dynamic fault tree model is established based on the organizational structure of the actuators in the spacecraft attitude control system. The minimum cut set of the dynamic fault tree is solved using a conditional binary decision graph. The reliability of the spacecraft attitude control system is solved by quantifying the minimum cut set based on hybrid failure logic. The method provided by this invention can accurately simulate and analyze the complex dynamic behavior of the actuators in the spacecraft attitude control system, ensuring the accuracy of the reliability assessment results while simplifying the assessment process.

Images