fly by wire


Fly-by-wire is a system that replaces the conventional manual flight controls of an aircraft with an electronic interface

Flying and handling qualities of a fly – by – wire blended-wing-body civil transport aircraft
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The blended-wing-body (BWB) configuration appears as a promising contender for the next generation of largc transport aircraft. The idea of blending the wing with the fuselage and eliminating the tail is not new, it has long been known that tailless aircraft can suffer from

Fly – by – wire Control of a Monocopter
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Monocopters are single winged, all-rotating powered flight vehicles modeled after falling maple seeds. In this project we evaluate monocopters to determine if they are suitable for indoor flight in confined spaces such as building corridors. As a potential new Unmanned

Airbus fly – by – wire : a process toward total dependability
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This paper deals with the digital electrical flight control system of the Airbus airplanes. This system is built to very stringent dependability requirements both in terms of safety (the systems must not output erroneous signals) and availability. System safety and availability

UH-60M upgrade fly – by – wire flight control risk reduction using the RASCAL JUH-60A in-flight simulator
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Abstract The US Army Aeroflightdynamics Directorate (AFDD), Sikorsky Aircraft Corporation (SAC), and the US Army Utility Helicopter Program Office (UHPO) have completed rapid risk reduction development for the UH-60M Upgrade fly – by – wire flight control system using the

Fly – by – wire augmented manual control-basic design considerations
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After the introduction of Fly – by – Wire (FBW) flight control in the late eighties, several thousands of commercial FBW aircraft are in service today. Looking back, it can be concluded that FBW has brought an impressive improvement to handling qualities and flight

Real-time hardware-in-the-loop simulation of fly – by – wire flight control systems
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The paper deals with the development and the set-up of a real-time/hardware-in-the-loop simulation system of the Fly – By – Wire flight control system of a modern aircraft. The plant is designed as a virtual iron-bird, which integrates a parallel computing PC network with

Biodynamic tests for pilots characterization on the BA 609 fly – by – wire tiltrotor
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The paper presents the results of a preliminary test campaign made on the BA609 tiltrotor for the in-flight measurement of the biodynamic response of the pilot. The objective of the test campaign was to verify the feasibility of this type of measures during flight tests, and to

Approaches to assure safety in fly – by – wire systems: Airbus vs. boeing.
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ABSTRACT Fly – by – wire (FBW) is a flight control system using computers and relatively light electrical wires to replace conventional direct mechanical linkage between a pilots cockpit controls and moving surfaces. FBW systems have been in use in guided missiles and

V-22 tiltrotor fly – by – wire flight control system
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This paper describes the flight control system for the V-22 Osprey tiltrotor aircraft (formerly JVX). V-22 is a multimission, multiservice program to develop a common aircraft for amphibious assault (US Marine Corps), combat search and rescue/special warfare (US

Flexible platform approach for CS27/29 fly – by – wire systems
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Due to high complexity and development costs, implementations of fly – by – wire systems are rarely found in class CS27/CS29-helicopters. This paper presents an approach which is aimed at reducing the development effort and hence allows more cost-effective system

Constrained notch filter optimization for a fly – by – wire flight control system
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Abstract Alenia Aeronautica SpA developed high skills in Notch Filter design and assessment processes. A fundamental step was taken in the integration of existing software and procedures with a new tool that allows Notch Filter optimization, enhanced with an extra

Fly – by – wire control of a helicopter: Multibody main rotor model
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The paper presents the multibody modeling of a helicopter fully articulated main rotor developed within a research program relevant to fly – by – wire architectures for the actuation of rotary wing aircrafts. The main aim of the model is to provide the force feedbacks on the

Requirements definition and qualification for a HEAT fly – by – wire system
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Abstract The Helicopter Electro-mechanical Actuation Technology (HEAT) programme seeks to embody novel electro-mechanical main and tail rotor actuation on to the EH101 helicopter. In combination witJ1 a new quadmplex fly – by – wire flight control system, HEAT will

Robust pressure control improves the performance of redundant fly – by – wire hydraulic actuators
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Aircraft primary flight control surfaces are typically driven by two linear hydraulic actuators accepting the controlled flows from two independent hydraulic systems. When the actuators are part of a fly – by – wire system, actuators flows are controlled by valves, and a key issue is to

A dual-duplex electrohydraulic system for the fly – by – wire control of a helicopter main rotor
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This paper presents a study relevant to a fly -bywire flight control system for the main rotor of a helicopter, aimed at ensuring the maximum level of system safety while keeping the wiring complexity as little as possible. The system is quadruplex electrical, dual hydraulic, arranged

Design and development of a two-fail-operate fly – by – wire flight control rotor actuation system utilizing integrated three-function valves
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For typical fixed-wing commercial aircraft, flight control system redundancy can be provided through the application of multiple independently actuated surfaces. An example of this methodology is the use of two or three ailerons per wing. Configured in this manner, continued safe flight is

The Development of a civilian fly by wire flight control system
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Within a national research and development program funded by the german ministry of education and research (BMBF) new fly by wire flight control system has been developed and is in the process of certification according to JAR 25. Technology readiness was

Design and development of prognostic and health management system for fly – by – wire primary flight control electrohydraulic servoactuators
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Abstract Electro-Hydraulic Servo Actuators (EHSA) is the principal technology used for primary flight control in new aircrafts and legacy platforms. The development of Prognostic and Health Management technologies and their application to EHSA systems is of great

In Flight Simulation for Flight Control Law Evaluation of Fly – by – Wire Aircraft
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The paper presented here covers the work associated with the flight control law validation with the ground based and in flight simulation techniques for the handling quality assessment of the pre-prototyping stage of Fly – by – Wire type Aircraft (FBWA). The FBWA is

Study of fly – by – wire system stability
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ABSTRACT A study of three problems about the stability for a fly – by – wire system, gain changing low, har-moniC oscillation and phase Compensation has been completed. Based on the research of the variation in sta-bilator effectiveness with different flight conditions, the