基于FPGA的火箭发动机多路时序点火系统设计

Multiple Sequence Design for Fire Control System in Rocket Engine Based on FPGA

传统固体火箭发动机测控电路采用固态继电器或PLC控制,响应时间长、时间控制精度低,同步性不高,针对某固体火箭发动机多路时序点火测控信号同步性要求,以FPGA为核心架构,计算机、硬件调理电路等部分组成通用火箭发动机测试平台,设计点火时序控制系统,对点火、采集系统同步触发、设备启动等多路信号进行时序控制。FPGA设计部分主要有3个模块组成:计数器模块,NIOSII模块,计数比较输出模块。计数器模块控制时间延时,NIOSII模块控制通信部分,计数比较模块控制信号输出。系统使用50 M的有源晶振,设计中FPGA内部的逻辑线路延时为ns级别,基本能满足μs级的延时要求。经测试结果表明多路同步时序精度达到ns级,实验使用Modelsim与Quartus II进行联合仿真,仿真的结果与实际测量的结果相吻合,点火同步信号误差为5.8 ns,满足发动机点火复杂时序控制要求,满足了多级多参量发动机点火时序要求,并得到成功应用。

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 Quartus II for the joint simulation. The simulation results are consistent with the actual measurement results. The ignition synchronization signal deviation is5. 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.