Abstract: The traditional solid rocket motor measurement and control circuit adopts solid state relays or PLC control. It has long response time, low time control precision, and low synchronization.In view of the synchronization requirements for multiple sequences fire control system in solid rocket engine. The System was designed based on FPGA. The FPGA design part mainly consists of three modules, counter module, NIOSⅡ module, and count comparison output module. Counter module control time delay, NIOSⅡ module control communication part, count comparison module control signal output. The system uses a 50 M active crystal oscillator. The delay of the internal logic circuit in the design is ns level, which can basically satisfy the μs delay requirement. The test results show that the multi-channel synchronous timing accuracy reaches ns level. The experiment uses Modelsim and QuartusⅡ for the joint simulation. The simulation results are consistent with the actual measurement results. The ignition synchronization signal deviation is 5.8 ns,which meets the complex timing control requirements of the engine ignition and satisfies the ignition timing requirements of multi-stage and multi-parameter engines. It has been successfully applied.