A study on optimal control of the aero-propulsion system acceleration process under the supersonic state

Sun, Fengyong; Du, Yao; Zhang, Haibo

doi:10.1016/j.cja.2017.02.002

Cited by 14 publications

(7 citation statements)

References 9 publications

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“…It has many advantages such as strong convergence, strong adaptability, and stability. 19 For the optimization problem described in equation ( 13), the objective function is constructed as equation ( 17)…”

Section: Principle Of Algorithmmentioning

confidence: 99%

“…However, it fails to follow the engine state when the engine degenerates. FSQP algorithm 19 is adopted to optimize the control variables including inlet ramp angle, fuel flow, and nozzle area online, which reduces the acceleration time by 5%. The coupling between inlet and engine is fully considered in this method, but it is difficult to apply it to engineering due to the long time consumption of FSQP.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Research and verification on aero-propulsion system acceleration control under supersonic state

Fang

Xiang

Zheng

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part I:

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Under supersonic acceleration flight, the traditional passive control method brings about acceleration performance deterioration, due to the bad matching between inlet and engine. Accordingly, a real-time optimization control method of the integrated propulsion system is proposed. In the article, the effect of a supersonic inlet on propulsion system performance is analyzed, and an onboard model of the integrated propulsion system is built to calculate the installed parameters. An improved trust region algorithm is adopted to optimize the inlet ramp angle in real time. Besides, digital simulation and hardware-in-the-loop simulation are carried out. The digital simulation result shows that compared with conventional inlet passive control, the acceleration time of the propulsion system is reduced by 8.59%. The result of the hardware-in-the-loop simulation indicates that the proposed method has high real-time performance simultaneously, which proves the engineering application value.

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Section: Principle Of Algorithmmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Research and verification on aero-propulsion system acceleration control under supersonic state

Fang

Xiang

Zheng

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part I:

Self Cite

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“…Fig. 6 shows an example matrix of a turbofan core engine [44]. For the ease of understanding, equations of all the components are integrated into the matrix K based on the order of engine structure.…”

Section: Given the Following Nonlinear Equationsmentioning

confidence: 99%

A Linearization Model of Turbofan Engine for Intelligent Analysis Towards Industrial Internet of Things

et al. 2019

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Big data processing technologies, e.g., multi-sensor data fusion and cloud computing are being widely used in research, development, manufacturing, health monitoring and maintenance of aero-engines, driven by the ever-rapid development of intelligent manufacturing and Industrial Internet of Things (IIoT). This has promoted rapid development of the aircraft engine industry, increasing the aircraft engine safety, reliability and intelligence. At present, the aero-engine data computing and processing platform used in the industrial Internet of things is not complete, and the numerical calculation and control of aero-engine are inseparable from the linear model, while the existing aero-engine model linearization method is not accurate enough to quickly calculate the dynamic process parameters of the engine. Therefore, in this paper, we propose a linear model of turbofan engine for intelligent analysis in IIoT, with the aim to provide a new perspective for the analysis of engine dynamics. The construction of the proposed model includes three steps: First, a nonlinear mathematical model of a turbofan engine is established by adopting the component modeling approach. Then, numerous parameters of the turbofan engine components and their operating data are obtained by simulating various working conditions. Finally, based on the simulated data for the engine under these conditions, the model at the points during the dynamic process is linearized, such that a dynamic real-time linearized model of turbofan engine is obtained. Simulation results show that the proposed model can accurately depict the dynamic process of the turbofan engine and provide a valuable reference for designing the aero-engine control system and supporting intelligent analysis in IIoT.INDEX TERMS Industrial Internet of Things, multi-sensor data fusion, cloud computing, turbofan engine, linearized model.

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“…The optimization control method, which can yield well engine transient performance with satisfactory opera-tion restrictions, has arouse great research interest in Min-Max limit protection design [6][7][8][9][10][11][12][13][14] . Ref.…”

Section: Introductionmentioning

confidence: 99%

“…[7] proposed a linear weighting method and an adaptive variable weight weighting method for multi-objective transient optimization problem. The Sequential Quadratic Programming (SQP) algorithm was applied to solve the optimiza-tion control [8][9] . The Feasible Sequential Quadratic Programming (FSQP) algorithm which has better global con-vergence and complete local super-linear convergence was employed to avoid the influence of the penalty function of SQP [10] .…”

Section: Introductionmentioning

confidence: 99%

A new min-max limit protection design method for aero-engine based on inverse mapping

zhu

Zheng

Zhang

2023

Third International Conference on Artificial Intelligence and Computer Engineering (ICAICE 2022)

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In order to improve the control accuracy of aero-engine operation limits, a novel design approach of Min-Max limit protection is proposed. The inverse mapping models of different limits based on On-Line Sliding Window Deep Neural Network (OL SW DNN) are proposed and established firstly. The OL SW DNN models calculate the limit value of fuel flows to ensure that engine satisfies all operation limits. The operation restrictions in the proposed method can vary in different flight conditions. With the application of on-line learning modeling method, the engine can always operate within the given operation limits no matter whether engine degrades or not. Moreover, the OL SW DNN adopts deep learning structure and has strong fitting capacity for the nonlinear object. The comparison simulations of the popular limit protection design method based on optimization method and the proposed one are carried out. Compared with the popular method, the limit line of each operation limits in the proposed method not only has much higher accuracy especially when engine appears degradation, but also can be continuous changed

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A study on optimal control of the aero-propulsion system acceleration process under the supersonic state

Cited by 14 publications

References 9 publications

Research and verification on aero-propulsion system acceleration control under supersonic state

Research and verification on aero-propulsion system acceleration control under supersonic state

A Linearization Model of Turbofan Engine for Intelligent Analysis Towards Industrial Internet of Things

A new min-max limit protection design method for aero-engine based on inverse mapping

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