An extrapolation approach for aeroengine’s transient control law design

Kong, Xianglong; Wang, Xi; Tan, Daoliang; He, Ai; Liu, Yue

doi:10.1016/j.cja.2013.04.027

Cited by 9 publications

(4 citation statements)

References 7 publications

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“…According to the optimal matching work control law of the propulsion system, the supersonic inlet should reduce the supported air mass flow by increasing the inlet ramp angle. And equation (3) shows that the optimization goal of the deceleration process is to reduce the installation thrust provided by the propulsion system. To achieve this optimization goal, the external resistance of the propulsion system should be maximized and the total thrust of the engine should be reduced.…”

Section: Aero-propulsion Deceleration Control Design and Simulationmentioning

confidence: 99%

“…At present, the aircraft deceleration process is usually accomplished by reducing the fuel mass flow. 3 However, in normal aircraft flight, acceleration was always the next operation after the deceleration. Once the fuel mass flow has been decreased to a low level, the acceleration seemed hard to be accomplished in time due to the acceleration limit control line.…”

Section: Introductionmentioning

confidence: 99%

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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: Aero-propulsion Deceleration Control Design and Simulationmentioning

confidence: 99%

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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“…These unsafe factors are intolerable for the engine, so the acceleration controller is supposed to have the ability to avoid dangerous working conditions. The objective of engine acceleration control is to obtain the minimum acceleration time on the premise of safe operation (without over-temperature, over-speed and surge) [6,7] . The traditional method is composed of the fuel flow curve, the steady-state controller and the limit protection controller.…”

Section: Introductionmentioning

confidence: 99%

Optimization control with multi-constraint of aeroengine acceleration process based on reinforcement learning

Fang¹,

Zheng²,

Liu³

et al. 2023

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

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With the development of reinforcement learning (RL), it becomes able to solve the continuous action space problem, and shows strong ability in dealing with complex nonlinear control problem. Based on the deep deterministic policy gradient (DDPG) algorithm, a novel scheme of aeroengine acceleration controller is proposed in this paper. According to the characteristics of the engine acceleration stage, the reward function is constructed, and the state parameters are updated in the form of sliding window to reduce the sensitivity of the network to noise. DDPG adopts actor-critic framework, critic calculates value function by the deep neural network, actor outputs action command and forms a closed-loop control system with the engine. The method is verified by digital simulation at ground condition and the results demonstrate that compared with the traditional PID controller, the acceleration time of DDPG controller is reduced by 41.56%. Additionally, the network converges within 400 steps.

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“…The ACE performance model is a zero-dimensional model which can be used for parametric cycle analysis, performance analysis [14], control schedule [15] study and so on. The engine performance model is established by a set of interconnected gas components.…”

Section: Introductionmentioning

confidence: 99%

Equilibrium running principle analysis on an adaptive cycle engine

Zheng

Tang

Chen

et al. 2018

Applied Thermal Engineering

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h i g h l i g h t sThe adaptive cycle engine is an evolutional concept of variable cycle engine. The advantages of the adaptive cycle engine depend on the matching principles. The equilibrium running principles of the adaptive cycle engine are deduced. A nonlinear component-based adaptive cycle engine performance model is built. The application of the equilibrium running principles based on model is proposed. a r t i c l e i n f o b s t r a c tAs an evolutional concept of variable cycle engine, the adaptive cycle engine draws widely attention with high expectations. It combines a variable geometry schedule and component matching principles to demonstrate its advantages such as avoiding severe inlet spillage drag and the wide variable cycle characteristics. Thus, this paper aims at equilibrium running principle analysis on an adaptive cycle engine at variable operating modes, deriving the equilibrium running equations of an adaptive cycle engine for the first time, and exploring the physical essence of components matching principle on the basis of a newly developed nonlinear component-based adaptive cycle engine performance model. It uncovers the physical essence of components matching relationships and provides mathematical derivation of equilibrium running principles which lay theoretical foundation of the variable geometries modulation schedule and overall performance optimization on an adaptive cycle engine.

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An extrapolation approach for aeroengine’s transient control law design

Cited by 9 publications

References 7 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

Optimization control with multi-constraint of aeroengine acceleration process based on reinforcement learning

Equilibrium running principle analysis on an adaptive cycle engine

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