考虑红外抑制器影响的直升机动力系统最优旋翼速度控制方法研究

IF 0.7 4区工程技术 Q4 ENGINEERING, AEROSPACE

International Journal of Turbo & Jet-Engines Pub Date : 2023-09-07 DOI:10.1515/tjj-2023-0048

Zhaoguang Wang, Jiatong Du, Haoran Guo

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引用次数: 0

摘要

摘要为了实现直升机动力系统的最经济运行，提出并设计了旋翼最优转速控制方法。首先，建立了直升机所需功率和涡轴发动机的简化性能计算模型，它们共同构成了直升机动力系统的性能计算模型;然后，根据上述模型，通过施加叶片载荷约束，以发动机燃油流量最小为优化目标，提出了基于黄金分割法的最优转子转速综合优化方法，揭示了不同工况下最优转子转速的变化规律。最后，分别进行了数值仿真和硬件在环仿真，验证了最优转子转速控制方法。结果表明，与转子恒转速运行相比，最优转速控制方法可使发动机燃油流量减少21% %以上，证明了该方法的显著有效性和令人满意的可行性。最优旋翼速度控制方法保证了直升机动力系统在最优旋翼速度下运行，有利于达到最经济的巡航目标。

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A study on optimal rotor speed control method for helicopter power system considering the influence of infrared suppressors

Abstract In order to realize the most economical operation of helicopter power system, the optimal rotor speed control method is proposed and designed. Firstly, the simplified performance calculation model of helicopter required power and turboshaft engine are established, which constitute the performance calculation model of helicopter power system together. Then, according to the above model, through applying blade loading constraint and selecting the minimum engine fuel flow as the optimization objective, an integrated optimization method of optimal rotor speed based on golden section method is proposed, which reveals the variation law of optimal rotor speed under different operation conditions. Finally, the numerical simulation and hardware-in-loop (HIL) simulation are conducted separately to validate the optimal rotor speed control method. The results indicate that compared with constant rotor speed operation, optimal rotor speed control method can decrease engine fuel flow by more than 21 %, which proves the significant effectiveness and satisfactory feasibility. The optimal rotor speed control method ensures that the helicopter power system operates at the optimal rotor speed, and is beneficial to reach the most economical cruise target.

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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.