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

2010 ◽  
Author(s):  
Leonid V. Sokolov
Keyword(s):  
Control System ◽  
High Temperature ◽  
Pressure Sensors ◽  
Aircraft Engine ◽  
Engine Control ◽  
Engine Control System

Method of Spare Parts: Digital Simulation of Aircraft Turbine Engine Control System

1985 ◽  
Author(s):  
Guan Yan-Shen ◽  
Warng Juhng-Sheng ◽  
Lee Tzu-Cheng
Keyword(s):  
Control System ◽  
Computer Program ◽  
Digital Simulation ◽  
Aircraft Engine ◽  
Spare Parts ◽  
The Other ◽  
Engine Control ◽  
Turbine Engine ◽  
Engine Control System ◽  
System A

The paper presents a new method of digital simulation of a control system. A computer program of an aircraft engine control system, as for an example, is implemented as a full authority digital simulator. The results of simulation show that the functions and applications of the simulator are extended as compared with those of the other type mathematical simulators.

An Approach to an Integrated Control System for a Modern Fighter Aircraft Engine

1986 ◽  
Author(s):  
Jürgen Lemmin
Keyword(s):  
Control System ◽  
Large Scale ◽  
Integrated Control ◽  
Systems Integration ◽  
Aircraft Engine ◽  
Engine Control ◽  
Fighter Aircraft ◽  
Engine Control System ◽  
Aircraft Systems ◽  
Control Concept

In the field of today’s military aircraft engines, the engine control system consists in most cases of hydromechanical controls, as such, with an electronic supervisory system. This type of control makes the integration of engine and aircraft systems rather difficult. Even with the Tornado engine which features a full authority electronic engine controller, only initial steps in systems integration are realized. With the introduction of digital electronics into both the engine control and the aircraft systems, together with the availability of data highway systems, large scale systems integration can be envisaged on future fighter aircraft, with the resultant improvement in overall weapon system performance. This paper puts forward a proposal for a control concept for a reheated fighter engine, and outlines possibilities for integration with aircraft systems.

An Advanced Engine Control System Using Combustion Pressure Sensors

1987 ◽  
Vol 201 (1) ◽  
pp. 55-59 ◽  
Author(s):  
T Sasayama ◽  
S Suzuki ◽  
M Amano ◽  
N Kuribara ◽  
S Sakamoto ◽  
...  
Keyword(s):  
Control System ◽  
Pressure Sensor ◽  
Simple Structure ◽  
High Efficiency ◽  
Pressure Sensors ◽  
Engine Control ◽  
Combustion Pressure ◽  
Powertrain Control ◽  
Engine Control System ◽  
Automotive Engines

While investigating high-efficiency responsive driveability accompanied by low exhaust emissions, a new concept in engine control has been developed. The method is based on the direct monitoring and controlling of combustion conditions in engines, using a newly developed combustion pressure sensor. Fibre-optic technology is adapted to this sensor to produce a high noise immunity and a simple structure that facilitates applications in automotive engines. A sensing method to obtain information on engine output, knocking or detonation and the combustion temperature from the signal of the combustion pressure sensor has been proposed. A control system for the engine and powertrain control using this sensing method has been put forth to provide a remarkable improvement in engine and powertrain characteristics.

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

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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