Finish Cracking of Composite Flight Control Surfaces

1995 ◽  
Author(s):  
Russell G. Maguire
Keyword(s):  
Flight Control ◽  
Control Surfaces

Research on the ELAC Systems of A320 Family Aircrafts

2012 ◽  
Vol 546-547 ◽  
pp. 1562-1567
Author(s):  
Kai Yin ◽  
Gang Yin ◽  
Qin Zhen Li
Keyword(s):  
Computer System ◽  
Basic Principle ◽  
Flight Control ◽  
On Line ◽  
Control Surfaces ◽  
Driving Circuit

This document introduces the basic principle of the ELAC System (Elevator Aileron Computer System) working of A320 aircrafts, and mainly, analyzes the driving circuit of the ELAC computer for the flight control surfaces. Furthermore, introduces a real fault on line maintenance, analyze it and find out the reason, give some useful advice on A320 aircraft line maintenance.

Modeling and Analysis of a Digital Hydraulic Actuator for Flight Control Surfaces

2021 ◽  
Author(s):  
R. S. Lopes ◽  
M. P. Nostrani ◽  
L. A. Carvalho ◽  
A. Dell’Amico ◽  
P. Krus ◽  
...  
Keyword(s):  
Performance Analysis ◽  
Flight Control ◽  
Data Model ◽  
Flight Performance ◽  
Hydraulic Actuator ◽  
Hydraulic Power ◽  
Fighter Aircraft ◽  
Modeling And Analysis ◽  
Modeling Process ◽  
Control Surfaces

Abstract This paper presents the design and modeling process of a flight control actuator using digital hydraulics and a performance analysis that compares the proposed solution and the Servo Hydraulic Actuator (SHA) on a fighter aircraft model. The proposed solution is named Digital Hydraulic Actuator (DHA) and comprises the use of a multi-chamber cylinder controlled by on/off valves and different pressures sources provided by a centralized hydraulic power unit, as proposed in the Fly-by-Wire (FbW) concept. The analyses were carried out using the Aero-Data Model in a Research Environment (ADMIRE), which was developed for flight performance analysis. The actuators were modeled using the software Matlab/Simulink® and Hopsan. They were applied to control the aircraft elevons in a flight mission close to the aircraft limits, to evaluate the actuator’s behavior and energy efficiency. The results show a reduction in energy dissipation up to 22.3 times when comparing the DHA with the SHA, and despite the overshooting and oscillations presented, the aircraft flight stability was not affected.

NDE of Damage in Aircraft Flight Control Surfaces

2007 ◽  
Author(s):  
David K. Hsu ◽  
Daniel J. Barnard ◽  
Vinay Dayal
Keyword(s):  
Flight Control ◽  
Aircraft Flight ◽  
Aircraft Flight Control ◽  
Control Surfaces

Longitudinal Flight Control for a Novel Airborne Wind Energy System: Robust MIMO Control Design Techniques

2011 ◽  
Author(s):  
Nicholas Tierno ◽  
Nicholas White ◽  
Mario Garcia-Sanz
Keyword(s):  
Wind Energy ◽  
Wind Turbine ◽  
Flight Control ◽  
Synchronous Generator ◽  
Energy System ◽  
Polar Coordinate System ◽  
Additional Information ◽  
Wind Energy System ◽  
Aerodynamic Control ◽  
Control Surfaces

This paper deals with the longitudinal flight control for a novel Airborne Wind Energy (AWE) system: the EAGLE System. It is a tethered lighter-than-air flyer wind turbine composed of a blimp, several aerodynamic airfoils (wings) with specific aerodynamic control surfaces (ailerons, elevator, rudder), a counter-rotating aerodynamic rotor for the wind turbine (four identical sections, symmetrically arranged, with three blades each), an electrical synchronous generator attached to the counter-rotating rotors, and a tether to secure the airship and to transmit the generated power. Additional information can be found in US Patent, Provisional Application No. 61/387,432 developed by the authors. The designed system proposed here supports a 2.5 kW generator and flies at approximately 100 meters. The mathematical model developed for the AWE system incorporates a hybrid blimp-airfoil design, modeled using a hybrid Cartesian-polar coordinate system to capture the dynamics of both the airship and the tether, and includes the effect of the counter-rotating aerodynamic rotor of the wind turbine, as well as the aerodynamic control surfaces. This paper presents the design of a robust Multi-Input Multi-Output (MIMO) controller for the 3×3 longitudinal flight dynamics of the tethered airborne wind energy system. The control system is designed by applying sequential MIMO robust Quantitative Feedback Theory (QFT) techniques.

scholarly journals Flow Visualization Over an Airfoil with Flight Control Surfaces in a Water Tunnel

2017 ◽  
Vol 2017 (1) ◽  
pp. 63-78
Author(s):  
Daniel Filipiak ◽  
Robert Szczepaniak ◽  
Tomasz Zahorski ◽  
Robert Bąbel ◽  
Sebastian Stabryn ◽  
...  
Keyword(s):  
Flow Visualization ◽  
Control Systems ◽  
Flight Control ◽  
Injection System ◽  
Flow Visualisation ◽  
Water Tunnel ◽  
3D Printed ◽  
Control Surfaces ◽  
And Training

Abstract This paper demonstrates the feasibility of using-a water tunnel for the visualisation of flow in airfoils with flight control systems in the form of slots and flaps. Furthermore, the issue of using water tunnels for scientific and training purposes was explained. The technology of 3D printed models for practical tests in a water tunnel was also presented. The experiment included conducting flow visualisation tests for three airfoil models: with the Clark Y 11.7% as the base airfoil and the same airfoil with a slot and a flap. Moreover, a modification to dye injection system was introduced. The presented results of flow visualisation around models with the use of dye, confirmed the effectiveness of the applied methodology. The results and conclusions may be utilized to verify most flow-related issues in hydrodynamic tunnels and can also be used as a training element.

Use of Multiple SMA Wires for Morphing of Inflatable Wings

2010 ◽  
Author(s):  
Anthony D. McDonald ◽  
Scott J. I. Walker
Keyword(s):  
Flight Control ◽  
Control Method ◽  
Control Surface ◽  
Static Testing ◽  
Wing Model ◽  
Additional Control ◽  
Pulling Force ◽  
Wing Morphing ◽  
The University ◽  
Control Surfaces

The concept of inflatable wings has design heritage and they have recently seen renewed interest, largely due to the increased demand in unmanned aerial vehicles (UAVs). They offer design advantages over conventional wings, particularly with regard to stowage and portability, since they can be tightly packed when undeployed. Unfortunately current methods of flight control involve the use of additional control surfaces attached to the trailing edge of the wing, adversely affecting the stowage capabilities. One way of overcoming this restriction is to use the wing itself as a control surface, by morphing the very shape of the wing to achieve the desired results. This article outlines the research performed at the University of Southampton into differing configurations of Shape Memory Alloy (SMA) wires as a controllable actuator for the wing morphing. Specifically the use of multiple wires to further enhance this control was the focus of this work. A simple test rig was constructed in order to evaluate the pulling force achievable by combinations of SMA wires in a number of configurations. The most promising of these configurations was then attached to an inflatable wing model for further testing. Both static testing and wind tunnel testing was undertaken, evaluating the authority of flight control such a system could achieve. The test results are presented in this paper, giving an initial performance assessment of the proposed control method.

scholarly journals Computational Evaluation of Control Surfaces Aerodynamics for a Mid-Range Commercial Aircraft

Aerospace ◽  
2020 ◽  
Vol 7 (10) ◽  
pp. 139
Author(s):  
Nunzio Natale ◽  
Teresa Salomone ◽  
Giuliano De Stefano ◽  
Antonio Piccolo
Keyword(s):  
Flight Control ◽  
Realistic Model ◽  
Navier Stokes ◽  
Flight Control System ◽  
Commercial Aircraft ◽  
Virtual Experiments ◽  
Computational Evaluation ◽  
Aerodynamic Properties ◽  
The Mean ◽  
Control Surfaces

Computational fluid dynamics is employed to predict the aerodynamic properties of the prototypical trailing-edge control surfaces for a small, regional transport, commercial aircraft. The virtual experiments are performed at operational flight conditions, by resolving the mean turbulent flow field around a realistic model of the whole aircraft. The Reynolds-averaged Navier–Stokes approach is used, where the governing equations are solved with a finite volume-based numerical method. The effectiveness of the flight control system, during a hypothetical conceptual pre-design phase, is studied by conducting simulations at different angles of deflection, and examining the variation of the aerodynamic loading coefficients. The proposed computational modeling approach is verified to have good practical potential, also compared with reference industrial data provided by the Leonardo Aircraft Company.

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