Distributed Flight Control and Propulsion Control Implementation Issues and Lessons Learned

1999 ◽  
Vol 121 (1) ◽  
pp. 96-101 ◽  
Author(s):  
W. R. Schley
Keyword(s):  
Control System ◽  
Distributed Control ◽  
Flight Control ◽  
Lessons Learned ◽  
Distributed Control System ◽  
Propulsion Control ◽  
Data Bus ◽  
Control System Architecture ◽  
Typical Design ◽  
Control Implementation

This paper addresses the motivations for using a distributed control system architecture, technical challenges, typical functions which are off-loaded to remote terminals, sensor/effector interface issues, data bus selection, technology insertion issues, lessons learned, and objectives for future distributed control implementations. Typical design requirements, constraints, environmental conditions, and operational challenges will be described. Examples of various distributed control system implementations will be discussed, including both propulsion control and flight control examples.

Distributed Flight Control and Propulsion Control Implementation Issues and Lessons Learned

1998 ◽  
Author(s):  
William R. Schley
Keyword(s):  
Control System ◽  
Distributed Control ◽  
Flight Control ◽  
Lessons Learned ◽  
Distributed Control System ◽  
Propulsion Control ◽  
Data Bus ◽  
Control System Architecture ◽  
Typical Design ◽  
Control Implementation

This paper addresses the motivations for using a distributed control system architecture, technical challenges, typical functions which are off-loaded to remote terminals, sensor/effector interface issues, data bus selection, technology insertion issues, lessons learned, and objectives for future distributed control implementations. Typical design requirements, constraints, environmental conditions, and operational challenges will be described. Examples of various distributed control system implementations will be discussed, including both propulsion control and flight control examples.

Distributed Embedded Control Architecture of a Leader-Follower Mobile Robot Formation

2015 ◽  
Vol 779 ◽  
pp. 201-204
Author(s):  
Ran Li ◽  
Yun Hua Li
Keyword(s):  
Control System ◽  
Mobile Robot ◽  
Mobile Robots ◽  
Distributed Control ◽  
Electronic System ◽  
Control Architecture ◽  
Distributed Control System ◽  
Embedded Control ◽  
Data Bus ◽  
Robot Cooperation

Mobile robots have been widely used for the good adaptability, payload capability. Robot cooperation brings benefits for the task in a multi-robot team. In this paper, the modular hardware design of a leader-follower mobile robot team is discussed, including the distributed control architecture and the electronic system of each robot of the team. The basic idea behind this paper is to introduce the design of the hardware and distributed control architecture, which mainly manages the distributed control system, consisting of microcontroller modules connected through a data bus. The research has a potential applying prospect in mobile robot tracing and locating in the future.

Development of a Smart Actuator for Turbine Engine Applications

1998 ◽  
Author(s):  
William Lorenz
Keyword(s):  
Control System ◽  
Distributed Control ◽  
Credit Card ◽  
High Reliability ◽  
Minimum Size ◽  
Distributed Control System ◽  
Turbine Engine ◽  
Term Operation ◽  
Data Bus ◽  
Smart Actuator

The application of distributed control systems to turbine engine controls offers the potential for major reductions in development time and costs for the engine control and the engine. Once the data bus and power bus are standardized for elements of a distributed control system, the industry will have a group of sensors, actuators, and controllers that could be interchangeable between applications. Software and hardware will still require modification to fit the specific application, however, great strides will have been made toward a “plug and play” capability between sensors, actuators, and controllers all tied together on the same data bus. The main controller in a distributed control system, except for software, would be interchangeable from engine to engine. This paper describes the design and development of the electronics for a smart actuator and discusses the design considerations which were used to guide the requirements. Requirements unique to turbine engine applications include temperature environments to 30° C, a severe vibration environment, minimum size and weight, and very high reliability. The electronics developed for the smart actuator were packaged on credit card sized printed wiring board modules. Two of these modules were packaged in a housing approximately 23×3.4×1.1 inches. The electronics operate from 28 volt DC power and communicate with the rest of the control system via the MEL-STD-1553B data bus. Although a hydraulic actuator was chosen as the demonstration vehicle, the electronic module is adaptable to any servo application and can be expanded to read any of the common engine sensors and operate solenoids. The chosen actuator was intended as a development tool to expose the design problems of distributed systems. Therefore, this first demonstration unit was designed using electronic components rated for 125° C operation. AlliedSignal is currently a member of a consortium of companies under DARPA sponsorship developing a family of SOI (silicon-on-insulator) integrated circuits rated for 200° C operation. Our current 125° C design is compatible with the new devices being developed. A 200° C unit is planned for 1998. Further improvements in the metalization used in the SOI devices will allow reliable long term operation to about 300° C. Devices for this higher temperature range are expected to be available in 1999.

Integrated Flight/Propulsion Control for Flight Critical Applications: A Propulsion System Perspective

1992 ◽  
Vol 114 (4) ◽  
pp. 755-762 ◽  
Author(s):  
K. D. Tillman ◽  
T. J. Ikeler
Keyword(s):  
Control System ◽  
Real Time ◽  
Air Force ◽  
Flight Control ◽  
Closed Loop ◽  
Fault Tolerant ◽  
Lessons Learned ◽  
System Perspective ◽  
Propulsion Control ◽  
Development Center

The Pratt & Whitney and Northrop companies together, under the Air Force Wright Research and Development Center (WRDC) sponsored Integrated Reliable Fault-Tolerant Control for Large Engines (INTERFACE II) Program [1, 2], designed and demonstrated an advanced real-time Integrated Flight and Propulsion Control (IFPC) system. This IFPC system was based upon the development of physically distinctive, functionally integrated, flight and propulsion controls that managed the Northrop twin engine, statically unstable, P700 airplane. Digital flight control and digital engine control hardware were combined with cockpit control hardware and computer simulations of the airplane and engines to provide a real-time, closed-loop, piloted IFPC system. As part of a follow-on effort, lessons learned during the INTERFACE II program are being applied to the design of a flight critical propulsion control system. This paper will present both the results of the INTERFACE II IFPC program and approaches toward definition and development of an integrated propulsion control system for flight critical applications.

Integrated Flight/Propulsion Control for Flight Critical Applications: A Propulsion System Perspective

1991 ◽  
Author(s):  
Kenneth D. Tillman ◽  
Timothy J. Ikeler
Keyword(s):  
Control System ◽  
Real Time ◽  
Air Force ◽  
Flight Control ◽  
Closed Loop ◽  
Fault Tolerant ◽  
Lessons Learned ◽  
System Perspective ◽  
Propulsion Control ◽  
Development Center

The Pratt & Whitney and Northrop companies together, under the Air Force Wright Research and Development Center (WRDC) sponsored Integrated Reliable Fault-Tolerant Control for Large Engines (INTERFACE II) Program[1,2], designed and demonstrated an advanced real-time Integrated Flight and Propulsion Control (IFPC) system. This IFPC system was based upon the development of physically distinctive, functionally integrated, flight and propulsion controls that managed the Northrop twin engine, statically unstable, P700 airplane. Digital flight control and digital engine control hardware were combined with cockpit control hardware and computer simulations of the airplane and engines to provide a real-time, closed loop, piloted IFPC system. As part of a follow on effort, lessons learned during the INTERFACE II program are being applied to the design of a flight critical propulsion control system. This paper will present both the results of the INTERFACE II IFPC program and approaches toward definition and development of an integrated propulsion control system for flight critical applications.

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