Discussion About Dynamic Simulation Test of an Aero-Engine Control System

1985 ◽  
Author(s):  
Wu Chi Hua ◽  
Fan Ding
Keyword(s):  
Control System ◽  
Control Systems ◽  
Dynamic Simulation ◽  
Physical Simulation ◽  
Engine Control ◽  
Simulation Test ◽  
Engine Control System ◽  
Aero Engine

In this paper, following viewes are expressed: (1). Introduction of partly physical simulation test about aero-engine control systems. (2). Several plans carried out for this test. (3). A real example of digital analogue hybrid partly physical simulation test.

On-line performance optimisation of aero engine control system

Automatica ◽  
2003 ◽  
Vol 39 (12) ◽  
pp. 2115-2121 ◽  
Author(s):  
O.D. Lyantsev ◽  
T.V. Breikin ◽  
G.G. Kulikov ◽  
V.Y. Arkov
Keyword(s):  
Control System ◽  
Engine Control ◽  
Engine Control System ◽  
Aero Engine ◽  
On Line

Engine Control Reliability and Durability Improvement Through Accelerated Mission Environmental Testing

1987 ◽  
Vol 109 (2) ◽  
pp. 142-145 ◽  
Author(s):  
W. J. Davies ◽  
R. W. Vizzini
Keyword(s):  
Control System ◽  
Control Systems ◽  
Flight Control ◽  
Structural Integrity ◽  
Salt Spray ◽  
Engine Control ◽  
Aircraft Carrier ◽  
Environmental Testing ◽  
Weapon Systems ◽  
Engine Control System

The integration of aircraft control systems for future weapon systems will require the engine control system to meet the mission reliability of the flight control system. This will be accomplished through system redundancy and verified by accelerated environmental testing. Combined environment reliability testing (CERT) will assure control system structural integrity and reliability growth of engine-mounted digital electronic controls. Pratt & Whitney, under contract to the U.S. Navy, has recently completed a 10,000-hr CERT program. Dual full authority digital electronic controls (FADEC), connected by a fiber optic data link, were subjected to environmental tests simulating a composite F-14 mission profile. The FADEC units were also exposed to periodic high vibration levels which would be experienced after foreign object damage and salt spray testing to simulate aircraft carrier environment. The test results are reported herein providing insight not only into the reliability and durability of digital electronic controls but also into the equipment and procedures required for testing of future military and commercial engine control systems.

scholarly journals Multi-Fault Diagnosis of an Aero-Engine Control System Using Joint Sliding Mode Observers

IEEE Access ◽  
2020 ◽  
Vol 8 ◽  
pp. 10186-10197 ◽  
Author(s):  
Linfeng Gou ◽  
Yawen Shen ◽  
Hua Zheng ◽  
Xianyi Zeng
Keyword(s):  
Control System ◽  
Fault Diagnosis ◽  
Sliding Mode ◽  
Engine Control ◽  
Engine Control System ◽  
Aero Engine ◽  
Sliding Mode Observers

Conceptual Design of an Optic-Based Engine Control System

1988 ◽  
Vol 110 (1) ◽  
pp. 28-32
Author(s):  
W. J. Davies ◽  
R. A. Baumbick ◽  
R. W. Vizzini
Keyword(s):  
Control System ◽  
Control Systems ◽  
Conceptual Design ◽  
Electromagnetic Interference ◽  
System Integration ◽  
Variable Geometry ◽  
Engine Control ◽  
Engine Control System ◽  
Propulsion Control ◽  
Electromagnetic Immunity

Advanced integrated flight and propulsion control systems may require the use of optic technology to provide enhanced electromagnetic immunity and reduced weight. Immunity to electromagnetic interference and pulses is required for integrated systems where flight and propulsion control systems communicate with each other and diverse systems located throughout a composite aircraft. Weight reduction is crucial to the complex engine control systems required for advanced engines incorporating diagnostics, variable geometry and vectoring/reversing exhaust nozzles. A team of Pratt & Whitney, McDonnell Aircraft, Hamilton Standard, and United Technologies Research Center have developed the conceptual design of an optic engine control system, under a contract from NASA Lewis, entitled Fiber Optic Control System Integration (FOCSI). FOCSI is a triservice/NASA joint program designed to provide the optic technology requirements for advanced fighter/attack aircraft.

Derivation of Diagnostic Requirements for a Distributed UAV Turbofan Engine Control System

2008 ◽  
Vol 130 (2) ◽  
Author(s):  
Olof Hannius ◽  
Dan Ring ◽  
Johan Karlsson
Keyword(s):  
Control System ◽  
Control Systems ◽  
System Level ◽  
Engine Control ◽  
Transient Faults ◽  
Turbofan Engine ◽  
Intelligent Monitoring ◽  
Engine Control System ◽  
Permanent Faults ◽  
Analytical Redundancy

This paper presents a method for deriving requirements for the efficiency of diagnostic functions in distributed electronic turbofan engine control systems. Distributed engine control systems consist of sensor, actuator, and control unit nodes that exchange data over a communication network. The method is applicable to engine control systems that are partially redundant. Traditionally, turbofan engine control systems use dual channel solutions in which all units are duplicated. Our method is intended for analyzing the diagnostic requirements for systems in which a subset of the sensors and the actuators is nonredundant. Such systems rely on intelligent monitoring and analytical redundancy to detect and tolerate failures in the nonredundant units. These techniques cannot provide perfect diagnostic coverage and, hence, our method focuses on analyzing the impact of nonperfect diagnostic coverage on the reliability and safety of distributed engine control systems. The method is based on a probabilistic analysis that combines fault trees and Markov chains. The input parameters for these models include failure rates as well as several coverage factors that characterize the performance of the diagnostic functions. Since the use of intelligent monitoring can cause false alarms, i.e., an error is falsely indicated by a diagnostic function, the parameters also include a false alarm rate. The method was used to derive the diagnostic requirements for a hypothetical unmanned aerial vehicle engine control system. Given the requirement that an engine failure due to the control system is not allowed to occur more than ten times per million hours, the diagnostic functions in a node must achieve 99% error coverage for transient faults and 90–99% error coverage for permanent faults. The system-level diagnosis must achieve 90–95% detection coverage for node failures, which are not detected by the nodes themselves. These results are based on the assumption that transient faults are 100 times more frequent than permanent faults. It is important to have a method for deriving probabilistic requirements on diagnostic functions for engine control systems that rely on analytical redundancy as a means to reduce the hardware redundancy. The proposed method allows us to do this using an existing tool (FAULTTREE+) for safety and reliability analysis.

scholarly journals FDIA System for Sensors of the Aero-Engine Control System Based on the Immune Fusion Kalman Filter

2021 ◽  
Vol 2021 ◽  
pp. 1-17
Author(s):  
Linfeng Gou ◽  
Ruiqian Sun ◽  
Xiaobao Han
Keyword(s):  
Kalman Filter ◽  
Control System ◽  
Fault Diagnosis ◽  
Filter Bank ◽  
Estimation Accuracy ◽  
Engine Control ◽  
Engine Control System ◽  
Multiple Sensors ◽  
Aero Engine ◽  
Non Gaussian

The Kalman filter plays an important role in the field of aero-engine control system fault diagnosis. However, the design of the Kalman filter bank is complex, the structure is fixed, and the parameter estimation accuracy in the non-Gaussian environment is low. In this study, a new filtering method, immune fusion Kalman filter, was proposed based on the artificial immune system (AIS) theory and the Kalman filter algorithm. The proposed method was used to establish the fault diagnosis, isolation, and accommodation (FDIA) system for sensors of the aero-engine control system. Through a filtering calculation, the FDIA system reconstructs the measured parameters of the faulty sensor to ensure the reliable operation of the aero engine. The AIS antibody library based on single sensor fault was constructed, and with feature combination and library update, the FDIA system can reconstruct the measured values of multiple sensors. The evaluation of the FDIA system performance is based on the Monte Carlo method. Both steady and transient simulation experiments show that, under the non-Gaussian environment, the diagnosis and isolation accuracy of the immune fusion Kalman filter is above 95%, much higher than that of the Kalman filter bank, and compared with the Kalman particle filter, the reconstruction value is smoother, more accurate, and less affected by noise.

Advanced Control Program for Army Gas Turbine Engines

1973 ◽  
Author(s):  
A. H. White ◽  
D. F. Wills
Keyword(s):  
Control System ◽  
Control Systems ◽  
Gas Turbine ◽  
Control Program ◽  
Turbine Engines ◽  
Engine Control ◽  
Gas Turbine Engines ◽  
System Technology ◽  
Engine Control System ◽  
Advanced Control

This paper summarizes the results of a 30-month program of design, fabrication, and test of an advanced electronic engine control system for small (2 to 5-lb/sec airflow) turboshaft engines. The objective of the program was to develop engine control system technology which would be implemented in future systems to meet advanced engine requirements and to alleviate many of the problems experienced with past and present control systems.

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