A Research on Aero-engine Control Based on Deep Q Learning
-
Qiangang Zheng
,
Zhihua Xi
Abstract
For improving the response performance of engine, a novel aero-engine control method based on Deep Q Learning (DQL) is proposed. The engine controller based on DQL has been designed. The model free algorithm – Q learning, which can be performed online, is adopted to calculate the action value function. To improve the learning capacity of DQL, the deep learning algorithm – On Line Sliding Window Deep Neural Network (OL-SW-DNN), is adopted to estimate the action value function. For reducing the sensitivity to the noise of training data, OL-SW-DNN selects nearest point data of certain length as training data. Finally, the engine acceleration simulations of DQR and the Proportion Integration Differentiation (PID) which is the most commonly used as engine controller algorithm in industry are both conducted to verify the validity of the proposed method. The results show that the acceleration time of the proposed method decreased by 1.475 second while satisfied all of engine limits compared with the tradition controller.
Funding statement: This study was supported in part by National Natural Science Foundation of China under Grant 51906102, in part by National Science and Technology Major Project under Grant 2017-V-0004-0054, in part by Research on the Basic Problem of Intelligent Aero-engine under Grant 2017-JCJQ-ZD-047-21, in part by China Postdoctoral Science Foundation Funded Project under Grant 2019M661835, in part by Aeronautics Power Foundation under Grant 6141B09050385, in part by the Fundamental Research Funds for the Central Universities under Grant NT2019004.
Nomenclature
| Symbol | Explanation | Symbol | Explanation |
|---|---|---|---|
| H | Height | T41 | High pressure turbine inlet temperature |
| Ma | Mach number | Nf | Fan rotor speed |
| PLA | Power level angle | Nc | Compressor rotor speed |
| Wfb | Fuel flow | Smf | Fan surge margin |
| F | Engine thrust | Smc | Compressor surge marge |
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© 2020 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Original Research Articles
- Novel Closed-Form Equation for Critical Pressure and Optimum Pressure Ratio for Turbojet Engines
- Development of Combustor for a Hybrid Turbofan Engine
- A Parametric Study of Hydrogen Fuel Effects on Exergetic, Exergoeconomic and Exergoenvironmental Cost Performances of an Aircraft Turbojet Engine
- A Model Reference Adaptive Sliding Mode Control Method for Aero-Engine
- Numerical Study of Mixing Enhancement in 2D Supersonic Ejector
- Flow Development Through An S-Shaped Diffusing Duct
- Nozzle Geometry Effect on Twin Jet Flow Characteristics
- Application of Proper Orthogonal Decomposition Method in Unsteady Flow Field Analysis of Axial High Bypass Fan
- A Research on Aero-engine Control Based on Deep Q Learning
- Blade Number Selection for a Splittered Mixed-Flow Compressor Impeller Using Improved Loss Model
- Study of Correctly Expanded Sonic Jet with Air Tabs
- Large-Eddy Simulation of Shaped Hole Film Cooling with the Influence of Cross Flow
- Modal Analysis of the Axial Compressor Blade: Advanced Time-Dependent Electronic Interferometry and Finite Element Method
- Exergy Analysis of a Turboprop Engine at Different Flight Altitude and Speeds Using Novel Consideration
- Thermal Optimization Design of Heat Exchanger in Supersonic Engine with Parameters’ Fluctuation
Artikel in diesem Heft
- Frontmatter
- Original Research Articles
- Novel Closed-Form Equation for Critical Pressure and Optimum Pressure Ratio for Turbojet Engines
- Development of Combustor for a Hybrid Turbofan Engine
- A Parametric Study of Hydrogen Fuel Effects on Exergetic, Exergoeconomic and Exergoenvironmental Cost Performances of an Aircraft Turbojet Engine
- A Model Reference Adaptive Sliding Mode Control Method for Aero-Engine
- Numerical Study of Mixing Enhancement in 2D Supersonic Ejector
- Flow Development Through An S-Shaped Diffusing Duct
- Nozzle Geometry Effect on Twin Jet Flow Characteristics
- Application of Proper Orthogonal Decomposition Method in Unsteady Flow Field Analysis of Axial High Bypass Fan
- A Research on Aero-engine Control Based on Deep Q Learning
- Blade Number Selection for a Splittered Mixed-Flow Compressor Impeller Using Improved Loss Model
- Study of Correctly Expanded Sonic Jet with Air Tabs
- Large-Eddy Simulation of Shaped Hole Film Cooling with the Influence of Cross Flow
- Modal Analysis of the Axial Compressor Blade: Advanced Time-Dependent Electronic Interferometry and Finite Element Method
- Exergy Analysis of a Turboprop Engine at Different Flight Altitude and Speeds Using Novel Consideration
- Thermal Optimization Design of Heat Exchanger in Supersonic Engine with Parameters’ Fluctuation
