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

摘要:

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。

Abstract:

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