基于电液伺服控制的飞行台液压加载系统

Hydraulic Load System of Flight Test Bed Based on Electro-hydraulic Servo Control

针对航空发动机空中试验过程中液压功率提取的试验要求,采用电液伺服控制系统,研制航空发动机飞行台液压加载系统,以实现被试发动机飞行台试验过程中,液压加载无级可调的要求。试验结果表明:在被试发动机飞行台试验中,该系统可以按要求定量模拟液压功率提取,满足系统设计指标。

Hydraulic load system which was used to validate tested aero-engine performance by extracting hydraulic power in flight test bed was developed based on electro-hydraulic servo control. The design requirements and structure of overall system were described. The flight test results show that the system developed is stable and can quantitatively extract hydraulic power of tested engine during air and ground test, and the function is able to fully meet the technical qualification.