This paper describes the control algorithms and control design process for a generic commercial aircraft engine simulation of a 40,000 lb thrust class, two spool, high bypass ratio turbofan engine. The aircraft engine is a complex nonlinear system designed to operate over an extreme range of environmental conditions, at temperatures from approximately -60 to 120+ F, and at altitudes from below sea level to 40,000 ft, posing multiple control design constraints. The objective of this paper is to provide the reader an overview of the control design process, design considerations, and justifications as to why the particular architecture and limits have been chosen. The controller architecture contains a gain-scheduled Proportional Integral controller along with logic to protect the aircraft engine from exceeding any limits. Simulation results illustrate that the closed loop system meets the Federal Aviation Administration s thrust response requirements

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Control Design for a Generic Commercial Aircraft Engine

A new high-fidelity simulation of a generic 40,000 lb thrust class commercial turbofan engine with a representative controller, known as CMAPSS40k, has been developed. Based on dynamic flight test data of a highly instrumented engine and previous engine simulations developed at NASA Glenn Research Center, this non-proprietary simulation was created especially for use in the development of new engine control strategies. C-MAPSS40k is a highly detailed, component-level engine model written in MATLAB/Simulink (The MathWorks, Inc.). Because the model is built in Simulink, users have the ability to use any of the MATLAB tools for analysis and control system design. The engine components are modeled in C-code, which is then compiled to allow faster-than-real-time execution. The engine controller is based on common industry architecture and techniques to produce realistic closed-loop transient responses while ensuring that no safety or operability limits are violated. A significant feature not found in other non-proprietary models is the inclusion of transient stall margin debits. These debits provide an accurate accounting of the compressor surge margin, which is critical in the design of an engine controller. This paper discusses the development, characteristics, and capabilities of the C-MAPSS40k simulation

/pdf/a-high-fidelity-simulation-of-a-generic-commercial-aircraft-1uhsq9oase.pdf

A High-Fidelity Simulation of a Generic Commercial Aircraft Engine and Controller

https://engagedscholarship.csuohio.edu/cgi/viewcontent.cgi?article=1303&context=enme_facpub

A multi-regulator sliding mode control strategy for output-constrained systems

Review of advanced low-emission technologies for sustainable aviation

This paper investigates the switching control problem for aero-engines. An event-triggered switching control strategy is presented based on the proposed switched equilibrium manifold expansion (EME) model of the aero-engine in order to enhance the speed regulation performance. First, a switching law is given using an optimization index for the candidate EME models, which utilize different mappings based on the off-line data of the aero-engine so that the switched EME model has higher accuracy than general EME models. Then, controllers for the subsystems of the switched EME model are designed using the exact feedback linearization technique. Asymptotic stability of the closed-loop switched system is ensured for arbitrary switching with the given condition. This enables us to pursue other performances via design of switching law with stability guaranteed. An event-triggered switching law is constructed for the controllers to get a better performance. Finally, a case study for a two-spool turbofan engine is performed to verify the effectiveness and superiority of the proposed control strategy.

Switching Control for Aero-Engines Based on Switched Equilibrium Manifold Expansion Model

Covers the design of engine control & monitoring systems for both turbofan & turboshaft engines, focusing on four key topics: modeling of engine dynamics; application of specific control design methods to gas turbine engines; advanced control concepts; &, engine condition monitoring.

Link C. Jaw

Papers

Aircraft engine controls : design, system analysis, and health monitoring

Aircraft Engine Controls