A mimicking technique of back pressure in the hardware-in-the-loop simulation of a fuel control unit

Yuan, Yuan; Zhao, Zhiwen; Zhang, Tianhong

doi:10.1177/0037549719873969

Cited by 6 publications

(4 citation statements)

References 13 publications

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“…The numerical results confirmed that the larger the input current to the torque motor, the faster the fuel metering valve responded. In [13], the effect of the FMU back pressure, namely the pressure downstream of the FMU, on the metered fuel was investigated using an AMESim model. It was found that the rate of metered fuel decreased with the back pressure increase.…”

Section: Figure 1 Aircraft Control Systemmentioning

confidence: 99%

“…The pilot in the cockpit can change the thrust level by acting on a throttle lever as shown in Fig. 1 [9,13]. In particular, by acting on the throttle lever, the pilot stage of the fuel metering valve (which is typically a two-stage servovalve), controlled by the Electronic Control Unit (ECU), changes the pressures acting on the main-stage spool ends, thus changing the spool displacement, which in turn changes the flow rate delivered into the combustion chamber.…”

Section: Introductionmentioning

confidence: 99%

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Detailed simulations of an aircraft fuel system by means of Simulink

Sciatti

Tamburrano

Palma

et al. 2022

J. Phys.: Conf. Ser.

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The fuel system is one of the most important and complex parts of aircraft, being tasked with suppling the correct quantity of fuel to the aircraft engine during all operative conditions, from flight to ground operation. It must operate efficiently in any condition to guarantee safety and reliability. A fuel system for kerosene-based fuels (i.e., jet fuels) is a combination of hydraulic components, namely, tanks, pumps, bypass valves, safety valves, servovalves. The aim of this paper is to provide an accurate simulation model of an entire fuel system for gas turbine (turboprop and turbofan) engines, which can be used by manufacturers and researchers to evaluate the performance of the fuel system under different operating conditions for given components or to select the geometries of the components to obtain specific performance levels. The numerical code is developed in the Simulink environment, which is a software package widely used in industry. A detailed description of the model is provided in this paper, and results under specific operating conditions are shown and discussed. The power consumption of the system is assessed as well, with indication of the main sources of losses, which will be useful for current EU projects aimed at reducing the power consumption of aircraft.

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Section: Figure 1 Aircraft Control Systemmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Detailed simulations of an aircraft fuel system by means of Simulink

Sciatti

Tamburrano

Palma

et al. 2022

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

show abstract

“…Meanwhile, the effects of back pressure and other nonlinear factors on pressure difference across metering valve have been researched. Yuan et al [52] researched the effect of the back pressure on the differential pressure. Chen et al [53] proposed the differential pressure fluctuation was the result of the dead zone in the zone-relay link.…”

Section: Influence Factorsmentioning

confidence: 99%

Fuel Flowrate Control for Aeroengine and Fuel Thermal Management for Airborne System of Aircraft—An Overview

Dong

Hang

et al. 2021

Applied Sciences

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Fuel flowrate control system and fuel thermal management are very important for aeroengine and the overall aircraft, and it has been researched for several decades. This survey paper makes a comprehensive and systematic overview on the exiting fuel flowrate regulation methods, thermal load of fuel metering units, fuel-based thermal management, and the fuel tank’s thermal management topology network with drain and recirculation. This paper firstly reviews the mechanism, technical advantages, and technical challenges of the fuel metering unit with flowrate control valve and constant pressure difference valve compensator, flowrate control valve and variable displacement pump-based pressure difference compensator, and motor-based flowrate regulation. Then, the technical characteristics of above fuel flowrate control methods related to thermal management are discussed and compared. Meanwhile, the behaviors of recirculated fuel flow within single tank system and dual tank system are explored. Thirdly, the paper discusses the future directions of fuel flowrate control and thermal management. The survey is significant to the fuel flowrate control and fuel thermal management of the aircraft.

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“…The hardware-in-the-loop (HIL) test provides an effective platform by testing actual components of a system along with virtual computer-based simulation models in real time [31,32]. By this means, the test quality is enhanced, the design cycle is shortened and the reliability of the tested components is improved.…”

Section: Hardware-in-the-loop Testmentioning

confidence: 99%

Actuator Fault Tolerant Control of Variable Cycle Engine Using Sliding Mode Control Scheme

et al. 2021

Self Cite

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This paper presents a fault tolerant control (FTC) design for the actuator faults in a variable cycle engine (VCE). Ensured by the multiple variable geometries structure of VCE, the design is realized by distributing the control effort among the unfaulty actuators with the “functional redundancy” idea. The FTC design consists of two parts: the fault reconstruction part and the fault tolerant control part, which use a sliding mode observer (SMO) and a sliding mode control (SMC) scheme respectively. Considering the inaccuracy of the fault reconstruction result, the proposed design requires only inaccurate fault information. The stability of the closed-loop control system is proved and the existence condition for the proposed control law is analyzed. This work also reveals its relation to the sliding mode control allocation design and the adaptive SMC design. An application case is then studied for tolerating the loss of effectiveness fault of the nozzle area actuator. Results show that the FTC design is able to tolerate the fault and achieves the same control goal as in the fault-free situation. Finally, a hardware-in-the-loop test is carried out to verify the design in a real-time distributed control system, which demonstrates its use from the engineering perspective.

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A mimicking technique of back pressure in the hardware-in-the-loop simulation of a fuel control unit

Cited by 6 publications

References 13 publications

Detailed simulations of an aircraft fuel system by means of Simulink

Detailed simulations of an aircraft fuel system by means of Simulink

Fuel Flowrate Control for Aeroengine and Fuel Thermal Management for Airborne System of Aircraft—An Overview

Actuator Fault Tolerant Control of Variable Cycle Engine Using Sliding Mode Control Scheme

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