In order to comprehensively verify the fault detection algorithm in the ducted rocket rapidly, a simulation platform based on system configuration switch method was built, which can simulate various fault mode for ducted rocket. Based on the simulation platform, the ducted rocket ignite fault model, pressure sensor fault model, device interface model and fault detection algorithm model which have a same interface and system configuration with the aircraft engine controller, etc. were built. Compared with the fault detect result of mathematical model and engine control system under a same fault mode, the fault detection algorithm in the engine control system can be verified rapidly. Taking the fault simulation of nozzleless booster ignition as an example, the modeling, the test, the verification, and the process of analysis were narrated. In addition, it is also applicable to the fault simulation and verification of the shutdown of nozzleless booster, the open of air inlet cover, the ignition of gas generator, and fault tolerant control of gas flow, which has strong universality, and can greatly reduce the time cost on system development and verification, and it has a strong applied value.