A Novel Control Scheme for Aircraft Engine Based on Sliding Mode Control With Acceleration/Deceleration Limiter

Abstract

To provide the desired thrust and prevent the engine from exceeding any safety or operational limits, a min-max selector with linear limiters is widely employed in current aircraft engine control logic. However, with the further requirements of engine performance, the traditional linear limiters should be improved. Though there are many researchers working on the development of improvement methods, none of those methods consider the limitation of core shaft acceleration. In this paper, a novel control scheme for aircraft engine based on sliding mode control with acceleration/deceleration limiter is proposed. Above all, the controller construction process is introduced, and the asymptotic stability of the whole controller is given. Then, with linearized model of JT9D turbofan engine, the control performance of the new approach is presented, which is also compared with the traditional methods. The simulation results show that the proposed method is efficient, and it can ensure all outputs of the controller, including the core shaft accelerationṄ c , high-pressure turbine outlet temperature increment T 48 , high-pressure compressor stall margin increment SmHPC, and so on, are well controlled. INDEX TERMS Min-max logic, sliding mode control, aircraft propulsion, acceleration/deceleration limit.

An Output-Based Limit Protection Strategy for Turbofan Engine Propulsion Control with Output Constraints

“…The optimal augmented monotonic tracking controller (OAMTC) method [9] was considered to be used for designing the controllers in this paper. Because the controlled parameters of the limit plan, n Hr = f (T t1 ), and the main control plan, n Hr = f (PLA), are both n Hc , the two plans adopt the same controller gain, F nHc .…”

“…The value λ to be assigned is the pole of the closed-loop system, and it can be obtained by using genetic algorithm. For more details, see [9]. The map in Equation (49) can be described in Figure 13: placed at = 5 λ − , and at = 2 λ − for 6 Tt F .…”

“…In recent years, it has been widely used in commercial aero-engines [2][3][4][5]. For the Min-Max control strategy, current mainstream research interests mainly include the following three points: one is the controller design method to improve the control performance of the Min-Max scheme, such as applying a sliding mode controller to replace a linear controller to improve the limit protection control [6][7][8][9][10]. However, the changes proposed in this study necessitate a complete redesign of the engine controller, which will impose challenges in terms of verification across the whole operating envelope and acceptance by engine control implementers [1].…”

A scientometric analysis and critical review of gas turbine aero-engines control: From Whittle engine to more-electric propulsion

“…In Table 2, scientometric survey data in the Histcite are shown. As shown in Table 2, the number of articles reviewed in scientometrics is 111, 12…”

“…In 2019 Yu proposed “a novel control scheme for an aircraft engine based on a sliding mode control with acceleration/deceleration limiter.” 21…”