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.

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.

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.

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.

All-Weather Operation for Helicopters: Flight Control Systems for Helicopters

1969 ◽  
Vol 73 (698) ◽  
pp. 129-137
Author(s):  
H. Collomosse
Keyword(s):  
Control System ◽  
Control Systems ◽  
Flight Control ◽  
Weather Conditions ◽  
Flight Control System ◽  
Adverse Weather Conditions ◽  
Adverse Weather

The term “All-Weather Systems for Helicopters” is capable of many different interpretations dependent upon operational requirements. Certainly there are no hard and fast rules laid down defining the equipment required to enable a helicopter to operate under adverse weather conditions. The accuracy to which the aircraft has to be flown under instrument conditions and the ability of the pilot to complete a given mission safely without undue fatigue are the prime considerations which need to be considered in determining the facilities and degree of sophistication necessary for a flight control system.

Stiffness Calculation and Predetermined Preload Optimal Design of Cable Control System

2011 ◽  
Vol 311-313 ◽  
pp. 2452-2456
Author(s):  
Chun Ning Yang ◽  
Yu Qiang Mu ◽  
Zheng You
Keyword(s):  
Control System ◽  
Optimal Design ◽  
Control Systems ◽  
Flight Control ◽  
Design Parameter ◽  
Main Type ◽  
Experimental Results ◽  
Flight Control System ◽  
Numerical Example ◽  
Important Design

The stiffness of cable flight control systems is one of the most important design parameter for aviation aircraft, because it can change the characteristic of control stick and influence the maneuverability and stability of the flight control system. Flexible cable control system is the main type of mechanical flight control system, in which movement can only be transmitted by cable in tension, the stiffness of cable control system is affected mainly by predetermined preload(PP), however the excessive PP would increase friction between cable and pulley which leads pilot an unfavorable maneuver. In this paper, the theoretical stiffness calculation of cable control system with the complex cable braided construction has been calculated and discussed, in addition the effects of cable deflection and linkage pulley are taken into account to obtain a precise stiffness calculation, and also the predetermined preload related to friction is studied through numerical example, as well as the numerical results have been compared with the experimental results.

Autonomous Flight Control System for Intelligent Aero-robot for Disaster Prevention

2003 ◽  
Vol 15 (5) ◽  
pp. 491-500 ◽  
Author(s):  
Hiroaki Nakanishi ◽  
◽  
Hiroyuki Hashimoto ◽  
Naomi Hosokawa ◽  
Koichi Inoue ◽  
...  
Keyword(s):  
Control System ◽  
Control Systems ◽  
Flight Control ◽  
Online Training ◽  
Disaster Prevention ◽  
Unmanned Helicopter ◽  
Flight Control System ◽  
Adaptive Controllers ◽  
Autonomous Flight ◽  
Controlled Object

This paper describes methods to develop autonomous flight control systems for an aero-robot using an unmanned helicopter RMAX developed by YAMAHA Co., LTD. Such systems are difficult to develop because helicopter dynamics are nonlinear. We propose an efficient method to design controllers by training neural networks. The proposed method is easy to use with online training or adaptive controllers to compensate for undesirable effects not modeled or sudden changes of the controlled object and environment, making the control system highly reliable. Results of flight experiments demonstrate the effectiveness of our approach.

Future Trends in Flight Control Systems

1975 ◽  
Vol 28 (3) ◽  
pp. 286-299
Author(s):  
G. H. Hunt
Keyword(s):  
Control System ◽  
Control Systems ◽  
Flight Control ◽  
Pressure Sensors ◽  
System Structure ◽  
Total System ◽  
Central Processor ◽  
Flight Control System ◽  
Control Surfaces ◽  
Selection Of

This paper was presented at a joint meeting of the Institute with the Institution of Electronic and Radio Engineers in London on 15 January 1975. The theme of the meeting at which six papers were discussed (a selection of which will be published in the Journal) was Advances in Airborne Equipment for Navigation and Freight Control.Modern data processors because of their increasing power and flexibility are increasingly used for a variety of functions in modern aircraft, both civil and military. It might seem that a flight control system could be designed of the form shown in Fig. 1, with a powerful central processor taking in signals from all the relevant sensors, gyros, pressure sensors, radar, &c., and operating the control surfaces so as to drive the aircraft along any desired course. But such a system would be quite inadequate in two vitally important aspects: there is no facility for inputs from the aircrew and no account has been taken of failure cases. These and other factors drive the control system designer inexorably towards a total system structure very similar to the type currently used in operational aircraft. There are of course a wide variety of such systems, but most of them are characterized by a number of common features.

Real Time Simulators for Use in Design of Integrated Flight and Propulsion Control Systems

1988 ◽  
Author(s):  
William J. Davies ◽  
Charlie L. Jones ◽  
Robert A. Noonan
Keyword(s):  
Control System ◽  
Control Systems ◽  
Flight Control ◽  
Integrated Control ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Flight Control System ◽  
Simulation Tools ◽  
Military Applications ◽  
Propulsion Control

The introduction of Full Authority Digital Electronic Controls (FADEC) to both commercial and military aircraft gas turbine engines provides significant operational benefits. FADEC’s are reliable and more maintainable than the hydromechanical controls they have replaced. The next significant change in their use will be integration with the flight control, particularly in military applications, to provide reduced fuel consumption in cruise and rapid, accurate engine transients for increased maneuverability. Integration with the flight control system requires another level of control system testing beyond verification that the FADEC will perform it’s principle functions-control and protection of the engine. This new testing requires that the FADEC be tested in unison with the flight control to verify total control system capability and safety throughout the flight envelope. These testing requirements have been addressed at Pratt & Whitney and various airframers through application of the same simulation tools which have been in use to verify FADEC hardware and software capability prior to engine test. These test systems and their application to advanced integrated control systems are described herein to provide insight into both their operation and application.

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