某型直升机油门控制系统研究

Research on Throttle Control System of a Helicopter

某型直升机安装的发动机采用电调控制,EECU通过感受总距位置信号的变化,快速调整发动机油门开度,来实现对整机需用功率变化的迅速响应。本研究基于飞行动力学仿真模型,计算在不同高度、温度、重量条件下,直升机悬停、平飞、爬升时的需用功率、油耗率和总距位置,确立总距-油门关系基准曲线。通过与试飞数据的对比,验证了本文的研究方法,为该型直升机油门控制系统设计提供理论基础。

The engine installed in a helicopter adopts electric control. EECU can quickly adjust the engine throttle opening by sensing the change of the total distance position signal to realize the rapid response to the required power of the helicopter. Based on the flight dynamics simulation model, this paper calculates the required power, fuel consumption rate and total position of the helicopter during hover, level flight and climbing/slipping under different altitude, temperature and weight conditions, and finally establishes a reference curve of collective-throttle relationship. By comparing with the flight test data, the research method of this paper is verified, which provides a theoretical basis for the design of throttle control system of the helicopter.