Research on high-bandwidth linear active disturbance rejection control method for variable speed turboshaft engine

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-12-19 DOI:10.1515/tjj-2023-0090

Bo Huang, Wenbo Li, Yerong Peng, Jie Song

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引用次数: 0

Abstract

Abstract The wide flight range and high torsional vibration frequency of high-speed helicopters impose stricter criteria for the high-bandwidth control of turboshaft engines. Consequently, research is underway to implement a high-bandwidth control method for turboshaft engines using the linear active disturbance rejection control (LADRC) theory. Initially, the LADRC is designed based on the mathematical model of the integrated helicopter/engine system. To address the challenge of maintaining control quality with varying speed reference commands for the power turbine, an improved LADRC method with tracking differentiators (TD) is developed. Numerical simulations comparing the control effectiveness of LADRC with TD to cascade PID and conventional LADRC methods are conducted. The results demonstrate that the improved LADRC gains have a wider tuning range than the LADRC controller, and the power turbine speed tracking effect of LADRC with TD is optimal. It is more conducive to accomplish high-bandwidth control of turboshaft engine with variable rotational speed.

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变速涡轮轴发动机高带宽线性主动干扰抑制控制方法研究

摘要高速直升机飞行范围广、扭转振动频率高，对涡轮轴发动机的高带宽控制提出了更严格的要求。因此，研究人员正在利用线性主动干扰抑制控制（LADRC）理论为涡轮轴发动机实现高带宽控制方法。最初，LADRC 是根据直升机/发动机集成系统的数学模型设计的。为了解决在动力涡轮机速度参考指令变化时保持控制质量的难题，开发了一种带有跟踪微分器（TD）的改进型 LADRC 方法。我们进行了数值模拟，比较了带有 TD 的 LADRC 与级联 PID 和传统 LADRC 方法的控制效果。结果表明，与 LADRC 控制器相比，改进的 LADRC 增益具有更宽的调节范围，带 TD 的 LADRC 功率涡轮机转速跟踪效果最佳。这更有利于完成对转速可变的涡轮轴发动机的高带宽控制。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

International Journal of Turbo & Jet-Engines 工程技术-工程：宇航

CiteScore

1.90

自引率

11.10%

发文量

审稿时长

6 months

期刊介绍： The Main aim and scope of this Journal is to help improve each separate components R&D and superimpose separated results to get integrated systems by striving to reach the overall advanced design and benefits by integrating: (a) Physics, Aero, and Stealth Thermodynamics in simulations by flying unmanned or manned prototypes supported by integrated Computer Simulations based on: (b) Component R&D of: (i) Turbo and Jet-Engines, (ii) Airframe, (iii) Helmet-Aiming-Systems and Ammunition based on: (c) Anticipated New Programs Missions based on (d) IMPROVED RELIABILITY, DURABILITY, ECONOMICS, TACTICS, STRATEGIES and EDUCATION in both the civil and military domains of Turbo and Jet Engines. The　International Journal of Turbo & Jet Engines　is devoted to cutting edge research in theory and design of propagation of jet aircraft. It serves as an international publication organ for new ideas, insights and results from industry and academic research on thermodynamics, combustion, behavior of related materials at high temperatures, turbine and engine design, thrust vectoring and flight control as well as energy and environmental issues.