【摘要】 固体火箭发动机的燃面退移速度是评估发动机性能的重要参数，针对其动态性、精确性需求，本研究提出了一种高精度动态多路燃速测试系统。该系统由上位机、超声采集卡、换能器等组成，采集卡作为系统核心以FPGA为主控，结合高压脉冲波发射电路、回波信号处理电路及其他模块实现超声波的高压发射与回波采集。系统实现对多个通道的并行燃速实时测量，极大减小了系统的测量误差，提高测量精度。通过单介质标准试块的厚度测量实验验证系统的可行性与测量精度。最后进行Φ127标准试验发动机的燃速测量试验，并设置多靶线燃速测量方法作为对照。结果表明，本文所提出的多路燃速测试系统的燃速测量的平均误差<0.1 mm/s，展现出了较高的实时性和精度并具有更好的兼容性。更多还原

【Abstract】 The burn surface recession rate of solid rocket motors is a critical parameter for evaluating engine performance. To address the demands for dynamic response and precision,a high-precision dynamic multi-channel burn rate measurement system is presented. The system consists of a host computer,ultrasonic acquisition card,transducers,and other components. The acquisition card,serving as the core of the system,is controlled by an FPGA and integrated with high-pressure pulse wave emission circuitry,echo signal processing circuits,and other modules to achieve high-pressure ultrasound transmission and echo signal acquisition. The system enables real-time multi-channel parallel burn rate measurement,significantly reducing measurement errors and improving accuracy. The feasibility and measurement precision of the system are validated through thickness measurement experiments using a single-material standard test block. Subsequently,burn rate measurement tests are conducted on a Φ127 standard test engine,with a multi-target burn rate measurement method used as a reference. The results demonstrate that the proposed multi-channel burn rate measurement system achieves an average measurement error of <0.1 mm/s,showcasing high real-time performance,precision,and better compatibility.更多还原