scholarly journals The fly-by-wire system

2019 ◽  
Vol 11 (4) ◽  
pp. 217-222 ◽  
Author(s):  
Ilie NICOLIN ◽  
Bogdan Adrian NICOLIN
Keyword(s):  
Control Systems ◽  
Flight Control ◽  
Aircraft Design ◽  
Computer Assisted ◽  
Aircraft Industry ◽  
Flight Control System ◽  
Analog To Digital ◽  
Human Control ◽  
Mechanical Linkage ◽  
Wire System

This report shows the execution and evolution of airplane flight control systems. The report describes the development of airplane flight control systems and gives a survey of the principal phases of the flight control systems that assure the finding and execution of the fly-by-wire system. The development of flight control systems, from human control with mechanical links to a wire-driven computer, is a remarkable representation of the development of aeronautical technologies. The fly-by-wire system constitutes a fast-forwarding in aircraft design, from mechanical linkage to large hydraulic actuators to computer-assisted fly-by-wire system. The use of the fly-by-wire system has generated huge satisfaction for the aircraft industry by lessening the weight of the flight control system, by creating multiple redundancy flight control systems, which increases the flight safety of all aircraft equipped with the fly-by-wire system. The passage from analog to digital is another fast-forwarding in the development of fly-by-wire systems.

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.

scholarly journals New trends in aircraft design

2021 ◽  
Author(s):  
Mária Jabrocká ◽  
◽  
Martin Bugaj
Keyword(s):  
Control System ◽  
Dynamic Stability ◽  
Flight Control ◽  
Aircraft Design ◽  
Hydrogen Fuel ◽  
Flight Control System ◽  
Aircraft Control ◽  
Near Future

Automation, robotic, unconventional arrangement hydrogen are the hallmarks of new trends in aircraft design. The implementation of hydrogen fuel in aircraft appears to be one of the biggest advances in the near future. Automation in aircraft control is based on the reduction of runway requirements. Among the main conclusions of the paper we include the finding that the aircraft does not have to have a classic conventional arrangement of vertical tail surfaces in order to achieve static/dynamic stability of the aircraft. The complexity of the elements of the aircraft stability and flight control system is directly depended on the weight of the aircraft. Upcoming trends in aircraft design should only based on existing concepts.

Evaluation of Novel Concepts for Takeover Control Using Electronically Coupled Sidesticks

2020 ◽  
Vol 65 (1) ◽  
pp. 1-15
Author(s):  
Rodolfo S. Sampaio ◽  
Michael Jones ◽  
Christian Walko
Keyword(s):  
Control Systems ◽  
Flight Control ◽  
The State ◽  
Loss Of Control ◽  
Simulation Environment ◽  
Low Level ◽  
Level Flight ◽  
Mechanical Linkage ◽  
Workload Reduction ◽  
A Priority

The state of the of art in flight control systems geared toward dual-pilot helicopters is the use of active inceptor systems to replace the traditional mechanical linkage between pilot and copilot inceptors. This work investigates the introduction of priority functions, which act to actively decouple inceptors in one control station. This approach has the potential to assist pilots to take over control in low-level flight and aid to mitigate loss-of-control accidents that occur in such conditions. Takeover control maneuvers are tested in a dual-pilot helicopter simulation environment to evaluate two inceptor decoupling methods, namely a priority pushbutton (manual) and a priority force threshold (automatic). Results indicate that the takeover maneuvers were successfully performed in low-level flight without over control (inaccurate control inputs) when using both priority functions. The priority functions led to a workload reduction when compared to a benchmark configuration without inceptor decoupling. Positive ratings in usefulness and satisfaction scales indicate pilot acceptance of the priority functions tested.

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.

From Analog to Digital Implementation

1975 ◽  
Vol 28 (4) ◽  
pp. 379-398
Author(s):  
J. C. Hall
Keyword(s):  
Control System ◽  
Flight Control ◽  
Flight Control System ◽  
Analog To Digital ◽  
Digital Implementation ◽  
Analog System

Some discussion of the L-1011 analog system will be given before discussing the problems and advantages of digital implementation. It is the most advanced flight control system in operation today and one for which Category III certification was achieved simultaneously with the airframe certification. All L-1011s have been delivered with a full Category III system and all operators are performing automatic landings in service.

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.

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