基于三模冗余的运载火箭增压控制设备设计

Design of Tank Pressure Controller of Launch Vehicle Based on Triple Modular Redundancy

目前某型号运载火箭增压输送系统采用机械式控制方式,该方式调试难度较高、误差较大;为此提出了一种基于三模冗余的数字式增压控制设备方案;该增压控制设备采用3个完全相同的处理单元进行压力数据采集及处理,在每个处理单元中,由数字式压力传感器进行贮箱压力测量并传送给单片机;通过单片机进行软件滤波和数据分析判读处理,输出控制信号;采用高可靠硬件表决单元对单片机输出的控制信号进行三取二表决,输出最终的电磁阀控制结果;试验表明,该增压控制设备易于调试和测试,测量精度在1%以内;该增压控制设备已完成样机研制,具有较高的通用性及可靠性。

The current launch vehicle pressurization system adopts mechanical control methods which is difficult for debugging and meas-urement error controlling. Therefore an electronic controller is proposed based on triple modular redundancy. There are three processing u-nits for pressure data acquisition and processing. In each unit？ tank pressure is measured by a digital sensor, and then transmitted to micro-controller. The data collected is handled by digital filters and intelligent interpretation to control the hardware voter. The control of electro-magnetic is obtained by the two - out-of-three strategy. Through testings the controller has good performance in debugging and testings and the pressure accuracy is within 1%. The controller completed the prototype, and has high universality and reliability.