This invention discloses a reliability modeling and evaluation method for
spacecraft separation control systems under
radiation environments. The method constructs a
system state transition model considering
fault propagation, integrates the
space radiation environment and the single-event sensitivity characteristics of the hardware, generates a particle incident
time series conforming to a Poisson distribution, and performs
fault injection simulation of the
system based on the Monte Carlo method. On this basis, it extracts multi-dimensional evaluation indicators such as
system reliability, fault shielding rate, fault shielding capability, and fault
distribution uniformity to form a weighted comprehensive reliability
score index. Furthermore, it utilizes Bayesian networks to conduct
inverse analysis to identify critical fault paths and sensitive components. This invention can effectively characterize the
fault propagation mechanism of single-event upset effects in
spacecraft separation control systems, achieving high-reliability evaluation of critical space control systems, and providing theoretical and methodological support for system design optimization and safety
verification.