The design of fly-by-wire flight control systems

2001 ◽  
Vol 105 (1051) ◽  
pp. 543-549 ◽  
Author(s):  
C. Fielding
Keyword(s):  
Control System ◽  
Control Systems ◽  
Flight Control ◽  
Data Systems ◽  
Flight Control System ◽  
Control Laws ◽  
Handling Qualities ◽  
Future Developments ◽  
Control Computer ◽  
Actuation Systems

The design of an advanced flight control system (FCS) is a technically challenging task for which a range of engineering disciplines have to align their skills and efforts in order to achieve a successful system design. This paper presents an overview of some of the factors which need to be considered and is intended to serve as an introduction to this stimulating subject. Specific aspects covered are: flight dynamics and handling qualities, mechanical and fly-by-wire systems, control laws and air data systems, stores carriage, actuation systems, flight control computer implementation, flexible airframe dynamics, and ground and flight testing. The flight control system challenges and expected future developments are reviewed and a comprehensive set of references is provided for further reading.

Flight Simulator as a Tool for Flight Control System Synthesis and Handling Qualities Research

2009 ◽  
Vol 147-149 ◽  
pp. 231-236 ◽  
Author(s):  
Tomasz Rogalski ◽  
Andrzej Tomczyk ◽  
Grzegorz Kopecki
Keyword(s):  
Control System ◽  
Control Systems ◽  
Flight Control ◽  
Flight Simulator ◽  
Flight Control System ◽  
Aircraft Control ◽  
Flight Testing ◽  
Flight Tests ◽  
Control Laws ◽  
Handling Qualities

At the Department of Avionics and Control Systems problems of aeronautical control systems have been dealt with for years. Several different kinds of aeronautical control systems have been designed, prototyped and tested. These control systems are intended for general aviation aircraft and unmanned aircraft. During all research projects computer simulations and laboratory tests were made. However, since in some cases such tests were insufficient, in-flight tests were conducted leading to a series of reliable results. The in-flight tests were made with the use of M-20 Mewa aircraft (autopilot for a GA aircraft) and PZL-110 Koliber aircraft (control system for UAV and indirect flight control system for a GA aircraft). Nevertheless, in-flight testing is very expensive and problematic. To avoid some problems appearing during in-flight tests and their preparation, a simulator – which is normally used for professional pilot training – can be used. The Aviation Training Center of the Rzeszów University of Technology possesses the ALSIM AL-200 MCC flight simulator. We have started preparing this simulator for the research. It is possible to control the simulated aircraft with the use of an external control system. The solution proposed enables testing the aircraft control algorithms, indirect control laws (e.g. control laws modifying handling qualities), as well as testing and assessment of the students’ pilotage skills. Moreover, the solution makes it possible to conduct tests connected with aircraft control, crew management, crew cooperation and flight safety. The simulator allows us to test dangerous situations, which – because of safety reasons – is impossible during in-flight testing. This paper presents modifications to the simulator’s hardware and additional software, which enable the described research.

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.

Design of the wind tunnel based virtual flight testing evaluation method for flight control systems

2016 ◽  
Vol 232 (1) ◽  
pp. 17-29
Author(s):  
Min Huang ◽  
Zhong-wei Wang ◽  
Zhen-yun Guo ◽  
Yao-bin Niu
Keyword(s):  
Control System ◽  
Wind Tunnel ◽  
Control Systems ◽  
Flight Control ◽  
Evaluation Method ◽  
Simulation Models ◽  
Hardware In The Loop ◽  
Flight Control System ◽  
Flight Testing ◽  
Simulation Evaluation

In order to provide a method for evaluating flight control systems with the wind tunnel based virtual flight testing and provide a guide for building virtual flight testing systems, the virtual flight testing evaluation method was researched. The virtual flight testing evaluation method consisted of three parts: virtual flight testing method, virtual flight testing data processing method, and flight control system performance determination method, which were respectively designed for a pitching control system. Then, the hardware-in-the-loop simulation evaluation method was presented, and comparisons between the virtual flight testing and hardware-in-the-loop simulation evaluation method were conducted to highlight the characteristics of virtual flight testing evaluation method. Finally, virtual flight testing simulation models of a sample air vehicle were built and virtual flight testing were simulated to demonstrate the virtual flight testing evaluation method, which is helpful for the understanding of the virtual flight testing evaluation method with more sensibility. The evaluation results show that the virtual flight testing evaluation method designed can be used for flight control system evaluation.

scholarly journals Sliding Mode Implementation of an Attitude Command Flight Control System for a Helicopter in Hover

10.14311/748 ◽  
2005 ◽  
Vol 45 (4) ◽  
Author(s):  
D. J. McGeoch ◽  
E. W. McGookin ◽  
S. S. Houston
Keyword(s):  
Control System ◽  
Flight Control ◽  
Sliding Mode ◽  
Flight Control System ◽  
Design Standards ◽  
Handling Qualities ◽  
Control Scheme ◽  
Non Linear ◽  
Order Representation ◽  
Control Implementation

This paper presents an investigation into the design of a flight control system, using a decoupled non-linear sliding mode control structure, designed using a linearised, 9th order representation of the dynamics of a PUMA helicopter in hover. The controllers are then tested upon a higher order, non-linear helicopter model, called RASCAL. This design approach is used for attitude command flight control implementation and the control performance is assessed in the terms of handling qualities through the Aeronautical Design Standards for Rotorcraft (ADS-33). In this context a linearised approximation of the helicopter system is used to design an SMC control scheme. These controllers have been found to yield a system that satisfies the Level 1 handling qualities set out by ADS-33. 

Robust scheduled control of longitudinal flight with handling quality satisfaction

2011 ◽  
Vol 115 (1165) ◽  
pp. 163-174 ◽  
Author(s):  
D. Saussié ◽  
C. Bérard ◽  
O. Akhrif ◽  
L. Saydy
Keyword(s):  
Control Systems ◽  
Flight Control ◽  
Modal Control ◽  
Control Laws ◽  
Handling Qualities ◽  
Control Techniques ◽  
Centre Of Gravity ◽  
Modern Methods ◽  
Handling Quality ◽  
Scheduling Technique

AbstractClassic flight control systems are still widely used in the industry because of acquired experience and good understanding of their structure. Nevertheless, with more stringent constraints, it becomes difficult to easily fulfil all the criteria with these classic control laws. On the other hand, modern methods can handle many constraints but fail to produce low order controllers. The following methodology proposed in this paper addresses both classic and modern flight control issues, to offer a solution that leverages the strengths of both approaches. First, anH∞synthesis is performed in order to get controllers which satisfy handling qualities and are robust with respect to mass and centre of gravity variations. These controllers are then reduced and structured by using robust modal control techniques. In conclusion, a self-scheduling technique is described that will schedule these controllers over the entire flight envelope.

New Fault-Tolerant Scheme for Flight Control System of Unmanned Aerial Vehicles

2013 ◽  
Vol 284-287 ◽  
pp. 1883-1887
Author(s):  
Ji Hui Pan ◽  
Xiao Lin Zhang ◽  
Sheng Bing Zhang ◽  
Hao Ma
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicles ◽  
Control Systems ◽  
Flight Control ◽  
Fault Tolerant ◽  
Flight Control System ◽  
Data Link ◽  
Servo Actuator ◽  
Fly Control ◽  
Key Techniques

In complex systems like flight control systems etc., reliability is as important as performance. In order to improve the reliability of flight control system (FCS), the fault- tolerant technique was adopted. Three parts of the FCS which are Flight Control Fault Tolerant Computer, Redundancy sensor and Servo-actuator have been explored. The key techniques have been solved, such as Redundant Disposition, Synchronism of the Redundant Channels, Data link and Communication of Channels, etc. The experimental results show that the system meets with the fly control system’s demand of reliability.

Design, Flight Simulation, and Handling Qualities Evaluation of an LPV Gain-Scheduled Helicopter Flight Control System

2000 ◽  
Vol 6 (6) ◽  
pp. 553-566 ◽  
Author(s):  
Ian Postlethwaite ◽  
Ioannis K. Konstantopoulos ◽  
Xiao-Dong Sun ◽  
Daniel J. Walker ◽  
Adrian G. Alford
Keyword(s):  
Control System ◽  
Flight Control ◽  
Flight Simulation ◽  
Flight Control System ◽  
Handling Qualities ◽  
Helicopter Flight ◽  
Gain Scheduled

scholarly journals Research on Fault-Tolerant Flight Control Computer for High Altitude Long Endurance Unmanned Air Vehicle

2018 ◽  
Vol 36 (4) ◽  
pp. 761-767
Author(s):  
Jihui Pan ◽  
Shengbing Zhang ◽  
Danghui Wang
Keyword(s):  
Control System ◽  
High Altitude ◽  
Flight Control ◽  
Fault Tolerant ◽  
Test Method ◽  
Flight Control System ◽  
Redundancy Management ◽  
Failure Tolerance ◽  
Control Computer ◽  
Long Endurance

With the development of high altitude long endurance UAV, Flight Control System in high altitude long endurance UAV must have so strong failure tolerance ability that it can improve the whole system reliability. Using redundancy technique can extremely improve failure tolerance and reliability of flight control system. Compared among civil and military aircraft and UAV, the architectures and redundancy management of fault-tolerant flight control computer (FCC)systems are introduced. Then, give a new architectures and redundancy management of fault-tolerant FCC systems for high altitude long endurance UAV. The experimental results show that the system meets the UAV's demand of high reliability, low cost and good expansibility, maximize the utilization of system resources and effectively improve the fault tolerant capability of airborne computer and the reliability of sensor subsystem. With fault injection test method, the results show that the fault tolerant methods improve fault detection rate and fault isolation rate.

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