Boundary protection control method of helicopter power system based on flight test analysis
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摘要:
涡轴发动机作为直升机等旋翼飞行器动力系统的主要部件，一旦发动机关键参数超限，一般采用降低燃油量及功率的方法进行限制，会暂时降低动力涡轮转速，使其低于正常额定状态约4%~6%。若未及时脱离超限状态，可导致动力涡轮转速继续降低，威胁飞行安全。为解决上述问题，基于对某型直升机从现象到数据的试飞分析，提出一种控制方法，通过设计总距控制律，在发参超限状态下实现动力系统边界保护控制，若未及时脱离超限状态，则自动改出，恢复动力系统正常控制，大幅增强了直升机动力系统控制的鲁棒性及飞行的安全性。通过动力系统建模，并对控制律进行仿真，验证了所提方法的正确性。
Abstract:Turboshaft engine is the main part of the power system of rotor aircraft such as helicopter. Once the key engine parameters exceed the limit, the method of reducing fuel quantity and power is generally adopted to limit, which will temporarily reduce the speed of power turbine, making it about 4%−6% lower than the normal rated state. However, if the overlimit state is not removed in time, the speed of the power turbine will continue to decrease, threatening the flight safety. Based on the flight test analysis of a certain helicopter from phenomena to data to solve the above problems. This paper proposes a control method, through the design from the total distance control law, achieve dynamic system boundary protection control in the condition of engine parameters overrun. if overrun status can’t get out timely, then engine change automatically to recover the normal control of power system. This method significantly enhances the robustness of helicopter power system control and the safety of the flight. The correctness of the design is verified by modeling the power system and simulating the control law.
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图 7 正常状态总距变化转速仿真曲线
Figure 7. Simulation curve of total distance change speed under normal circumstances
图 8 发参超限保护仿真曲线
Figure 8. Simulation curve of over-limit protection for engine parameter
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