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.

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.

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.

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.

scholarly journals Co-Simulation of Distributed Engine Control System and Network Model using FMI & SCNSL

2015 ◽  
Vol 48 (16) ◽  
pp. 261-266 ◽  
Author(s):  
Nicolai Pedersen ◽  
Jan Madsen ◽  
Morten Vejlgaard-Laursen
Keyword(s):  
Control System ◽  
Network Model ◽  
Engine Control ◽  
Engine Control System

Second Paper: Failure-Survival Automatic Flight Control Systems for Aircraft with Particular Reference to a High Reliability Electrohydraulic Actuator

1965 ◽  
Vol 180 (1) ◽  
pp. 246-259
Author(s):  
R. Ruggles
Keyword(s):  
Control System ◽  
Control Systems ◽  
Flight Control ◽  
High Reliability ◽  
Supply System ◽  
Design Criteria ◽  
Flight Control System ◽  
Advantages And Disadvantages ◽  
System Configurations ◽  
Very High

The author discusses some of the problems of failure-survival automatic flight control systems and suggests some basic ground rules as design criteria. The advantages and disadvantages of some of the main types of system are discussed: duplex, triplex, triple component, duplicate-monitored and quadruplex systems being covered. In particular, a quadruplex actuator is described which has been designed and developed mainly for automatic flight control system applications where a very high degrees of failure-survival capability is required. A detailed failure analysis of the various systems is carried out and the importance of the electrical and hydraulic supply system configurations and failure rates is brought out.

Advanced Control System Considerations for Small Shaft-Type Aircraft Gas Turbines

1970 ◽  
Author(s):  
D. A. Prue ◽  
T. L. Soule
Keyword(s):  
Control System ◽  
Gas Turbines ◽  
Evaluation Criteria ◽  
Open Loop ◽  
Engine Control ◽  
Gas Generator ◽  
Engine Control System ◽  
Power Turbine ◽  
Advanced Control ◽  
Temperature Load

The next generation of free-turbine engines in the 2 to 5-lb/sec airflow class will undergo vast improvements in performance and efficiency. The improvements will be achieved concurrent with overall reductions in size and weight. Effort is required at optimization and miniaturization of the engine control system to keep pace with these improvements. This paper describes a conceptual design of an advanced engine control system for this class of engine. It provides gas generator and power turbine control with torque, temperature, load sharing and overspeed limiting functions. The control system was concepted to accommodate, with minimum hardware changes, such variants as regenerative cycle and/or variable power turbine geometry. In addition, considerations for closed and open loop modes of control and fluidic, electronic and hydromechanical technologies were studied to best meet a defined specification and a weighted set of evaluation criteria.

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