A study on the high stability control for the integrated aero-propulsion system under supersonic state

Sun, Fengyong; Li, Yongjin; Du, Yao; Zhang, Haibo

doi:10.1016/j.ast.2018.02.017

Cited by 11 publications

(2 citation statements)

References 8 publications

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“…During the aircraft’s flight, the dynamic process of aero-engine always completed in very short time, but the flight conditions stayed the same as before. 11 Then, the coupled problems appeared. Usually, the coupled problems lead the engine into safety issues such as surge and net thrust drop.…”

Section: Introductionmentioning

confidence: 99%

A new solution to the coupled problems of aero-propulsion system deceleration under supersonic state

Sun

Chen

Zhang

2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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Under supersonic state, the aero-propulsion system exhibits different coupled characters in deceleration from that in acceleration. However, the deceleration control has not been fully studied. In order to solve the coupled problems, an integrated component-level model including inlet and turbofan engine was established. Based on the integrated model, the particularity of inlet adjustment during deceleration was analyzed. And the analyzed results showed that the inlet regulation is not necessary to keep the inlet and engine working in well-matched at any time under supersonic state. Due to the coupled relationship between inlet and turbofan engine, a new optimal integrated control scheme is proposed in this paper. The inlet ramp angle is taken as an optimal control variable as the same as main fuel mass flow and nozzle throat area. The simulation results indicate that inlet ramp angle regulation showed a more effective control quality in the rapid drop of aero-propulsion–installed thrust. Furthermore, the deceleration could be completed in a shorter control time.

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Section: Introductionmentioning

confidence: 99%

A new solution to the coupled problems of aero-propulsion system deceleration under supersonic state

Sun

Chen

Zhang

2021

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…This results in enormous additional spillage drag, which seriously affects the thrust coupling effect between aircraft and propulsion system and further reduces the driving quality. 13–15 Therefore, it is of great theoretical and engineering significance for the design of supersonic passenger aircraft to explore the coupling dynamic mechanism of inlet disturbance, inlet, and engine under supersonic flight conditions.…”

Section: Introductionmentioning

confidence: 99%

Study on integrated control for supersonic inlet and turbofan engine model

Chen

Zhang

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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Considering the supersonic inlet model with normal shock position feedback, the integrated control method of inlet and turbofan engine is studied. The integrated model includes the supersonic inlet model and the component level model of engine. Combining the relationship between the normal shock position and the total pressure recovery coefficient, the supersonic inlet and engine model is constructed. On the basis of this model, the normal shock position closed-loop control simulation is carried out, which shows that the normal shock position matching point could be stabilized near the optimal value while restraining the inlet stream disturbance. Furthermore, based on the H∞ control algorithm, an inlet and engine integrated control is designed to control the installation thrust and turbine pressure ratio with fuel, nozzle throat area, and normal shock position as control variables. The simulation results show that the response time of the integrated control is faster than the independent control. The integrated control has stronger ability to restrain the atmospheric disturbance, which could ensure the stable and reliable operation of the propulsion system.

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Research on the Integrated Modeling Method of Inlet and Engine Based on Component Level Model

Sun,

Song,

et al. 2024

Int. J. Aeronaut. Space Sci.

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A study on the high stability control for the integrated aero-propulsion system under supersonic state

Cited by 11 publications

References 8 publications

A new solution to the coupled problems of aero-propulsion system deceleration under supersonic state

A new solution to the coupled problems of aero-propulsion system deceleration under supersonic state

Study on integrated control for supersonic inlet and turbofan engine model

Research on the Integrated Modeling Method of Inlet and Engine Based on Component Level Model

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