Parallel processing in high integrity aircraft engine control

Limit protection, which frequently exists as an auxiliary part in control systems, is not the primary motive of control but is a necessary guarantee of safety. As in the case of aircraft engine control, the main objective is to provide the desired thrust based on the position of the throttle; nevertheless, limit protection is indispensable to keep the engine operating within limits. There are plenty of candidates that can be applied to design the regulators for limit protection. PID control with gain-scheduling technique has been used for decades in the aerospace industry. This classic approach suggests linearizing the original nonlinear model at different power-level points, developing PID controllers correspondingly, and then scheduling the linear time-invariant (LTI) controllers according to system states. Sliding mode control (SMC) is well-known with mature theories and numerous successful applications. With the one-sided convergence property, SMC is especially suitable for limit protection tasks. In the case of aircraft engine control, SMC regulators have been developed to supplant traditional linear regulators, where SMC can strictly keep relevant outputs within their limits and improve the control performance. In aircraft engine control field, we all know that the plant is a nonlinear system. However, the present design of the sliding controller is carried out with linear models, which severely restricts the valid scope of the controller. Even if the gain scheduling technique is adopted, the stability of the whole systems cannot be theoretically proved. Research of linear parameter varying (LPV) system throws light on a class of nonlinear control problems. In present works, we propose a controller design method based on the LPV model to solve the engines control problem and achieve considerable effectiveness. In this paper, we discuss the design of a sliding controller for limit protection task of aircraft engines, the plant of which is described as an LPV system instead of LTI models. We define the sliding surface as tracking errors and, with the aid of vertex property, present the stability analysis of the closed-loop system on the sliding surface. An SMC law is designed to guarantee that the closed-loop system is globally attracted to the sliding surface. Hot day (ISA+30° C) takeoff simulations based on a reliable turbofan model are presented, which test the proposed method for temperature protection and verify its stability and effectiveness.

High-temperature microelectromechanical pressure sensors based on a SOI heterostructure for an electronic automatic aircraft engine control system

10.1117/12.885688 ◽

2010 ◽

Author(s):

Leonid V. Sokolov

Keyword(s):

Control System ◽

High Temperature ◽

Pressure Sensors ◽

Aircraft Engine ◽

Engine Control ◽

Engine Control System

Parallel Processing for Jet Engine Control

10.1007/978-1-4471-1972-2 ◽

1992 ◽

Cited By ~ 5

Author(s):

Haydn A. Thompson

Keyword(s):

Parallel Processing ◽

Engine Control ◽

Jet Engine

Design issues in a fiber optic sensor system architecture for aircraft engine control

10.2514/6.1992-3483 ◽

1992 ◽

Author(s):

SAMHITA DASGUPTA

Keyword(s):

System Architecture ◽

Fiber Optic ◽

Aircraft Engine ◽

Fiber Optic Sensor ◽

Sensor System ◽

Engine Control ◽

Design Issues ◽

Optic Sensor

Optical sensors and multiplexing for aircraft engine control

10.1117/12.141349 ◽

1993 ◽

Author(s):

Ertugrul Berkcan

Keyword(s):

Optical Sensors ◽

Aircraft Engine ◽

Engine Control

How to Improve Integration of a Change to Aircraft Engine Control Using ARP6109

10.4271/2015-01-2428 ◽

2015 ◽

Author(s):

Richard Ambroise ◽

Gabriel Godfrey

Keyword(s):

Aircraft Engine ◽

Engine Control

A Study on Aircraft Engine Control Systems for Integrated Flight and Propulsion Control

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES ◽

10.2322/jjsass.56.80 ◽

2008 ◽

Vol 56 (649) ◽

pp. 80-87 ◽

Cited By ~ 1

Author(s):

Hideaki Yamane ◽

Yasushi Matsunaga ◽

Takeshi Kusakawa

Keyword(s):

Control Systems ◽

Aircraft Engine ◽

Engine Control ◽

Propulsion Control

Optical temperature compensation schemes of spectral modulation sensors for aircraft engine control

10.1117/12.141345 ◽

1993 ◽

Author(s):

Ertugrul Berkcan

Keyword(s):

Temperature Compensation ◽

Aircraft Engine ◽

Engine Control ◽

Spectral Modulation

Real-Time Multi-Color Techniques for Identification and Filtering of Burst Signals in Jet Engine Pyrometers

Volume 2, Fora: Cavitation and Multiphase Flow; Fluid Measurements and Instrumentation; Microfluidics; Multiphase Flows: Work in Progress ◽

10.1115/fedsm2013-16623 ◽

2013 ◽

Cited By ~ 2

Author(s):

Guanghua Wang ◽

Jordi Estevadeordal ◽

Nirm Nirmalan

Keyword(s):

High Speed ◽

Aircraft Engine ◽

Color Temperature ◽

Great Promise ◽

Engine Control ◽

Simulink Model ◽

Voltage Signal ◽

Temperature Signal ◽

Reliable Temperature ◽

Radiant Temperature

A Multi-color Pyrometry (MCP) experiment was carried out on a aircraft engine to study the nature of hot particulate bursts generated from the combustor at certain engine conditions. These bursts of hot particulates lead to intermittent high-voltage signal output from the line-of-sight (LOS) pyrometer which is ultimately detected and used by the onboard Digital Engine Controller (DEC). The investigation used a high-speed MCP system designed to detect bursts and identify their properties. Results of the radiant temperature, multi-color temperature and apparent emissivity are presented. The results indicated that the apparent emissivity calculated during the signal burst was lower than that of the blade. The root cause for the signal burst was identified as soot particles generated as by-product of combustion under certain conditions. A digital filter technique is developed to send reliable temperature signal to DEC for robust engine control even under the engine bursting conditions. Simulink model is used to simulate the performances of the design and showed great promise for engine control.