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

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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Computational Evaluation of Aerodynamic Loading on Retractable Landing-Gears

Aerospace ◽

10.3390/aerospace7060068 ◽

2020 ◽

Vol 7 (6) ◽

pp. 68 ◽

Cited By ~ 2

Author(s):

Giuliano De Stefano ◽

Nunzio Natale ◽

Giovanni Paolo Reina ◽

Antonio Piccolo

Keyword(s):

Landing Gear ◽

Navier Stokes ◽

Governing Equations ◽

Commercial Aircraft ◽

Aerodynamic Loading ◽

Computational Evaluation ◽

The Mean ◽

Landing Gears ◽

Gear Systems ◽

Dynamic Meshing

Computational fluid dynamics is employed to evaluate the mean aerodynamic loading on the retractable landing-gears of a regional transport commercial aircraft. The mean turbulent flow around simplified landing-gear systems including doors is simulated by using the Reynolds-averaged Navier–Stokes approach, where the governing equations are solved with a finite volume-based numerical method. Using a dynamic meshing method, the computational grid is automatically and continuously adapted to the time-changing geometry, while following the extension/retraction of the landing-gear systems. The temporal evolution of the aerodynamic forces on both the nose and the main landing-gears, along with the hinge moments of the doors, is numerically predicted. The proposed computational modeling approach is verified to have good practical potential when compared with reference experimental data provided by the Leonardo Aircraft structural loads group.

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Computational Evaluation of Shock Wave Interaction with a Cylindrical Water Column

Applied Sciences ◽

10.3390/app11114934 ◽

2021 ◽

Vol 11 (11) ◽

pp. 4934

Author(s):

Viola Rossano ◽

Giuliano De Stefano

Keyword(s):

Shock Wave ◽

Water Column ◽

Wave Interaction ◽

Navier Stokes ◽

Plane Shock ◽

Governing Equations ◽

Computational Evaluation ◽

Air Water Interface ◽

The Mean ◽

The Impact

Computational fluid dynamics was employed to predict the early stages of the aerodynamic breakup of a cylindrical water column, due to the impact of a traveling plane shock wave. The unsteady Reynolds-averaged Navier–Stokes approach was used to simulate the mean turbulent flow in a virtual shock tube device. The compressible flow governing equations were solved by means of a finite volume-based numerical method, where the volume of fluid technique was employed to track the air–water interface on the fixed numerical mesh. The present computational modeling approach for industrial gas dynamics applications was verified by making a comparison with reference experimental and numerical results for the same flow configuration. The engineering analysis of the shock–column interaction was performed in the shear-stripping regime, where an acceptably accurate prediction of the interface deformation was achieved. Both column flattening and sheet shearing at the column equator were correctly reproduced, along with the water body drift.

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FLIGHT CONTROL SYSTEM DESIGN FOR COMMERCIAL AIRCRAFT USING NEURAL NETWORKS

IFAC Proceedings Volumes ◽

10.3182/20020721-6-es-1901.01226 ◽

2002 ◽

Vol 35 (1) ◽

pp. 1-6 ◽

Cited By ~ 1

Author(s):

Madjid HAOUANI ◽

Maarouf SAAD ◽

Ouassima AKHRIF

Keyword(s):

Neural Networks ◽

Control System ◽

System Design ◽

Flight Control ◽

Control System Design ◽

Flight Control System ◽

Commercial Aircraft

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Performing co-ordinated turns with articulated wing-tips as multi-axis control effectors

The Aeronautical Journal ◽

10.1017/s0001924000003511 ◽

2010 ◽

Vol 114 (1151) ◽

pp. 35-47 ◽

Cited By ~ 8

Author(s):

P. Bourdin ◽

A. Gatto ◽

M. I. Friswell

Keyword(s):

Flight Control ◽

Vortex Lattice ◽

Bending Moment ◽

Navier Stokes ◽

Objective Functions ◽

Flight Control System ◽

Secondary Objective ◽

Novel Method ◽

Wing Tips ◽

Wing Tip

Abstract This paper investigates a novel method for the control of aircraft. The concept consists of articulated split wing-tips, independently actuated and mounted on a baseline flying wing. The general philosophy behind the concept was that adequate control of a flying wing about its three axes could be obtained through local modifications of the dihedral angle at the wing-tips, thus providing an alternative to conventional control effectors such as elevons and drag rudders. Preliminary computations with a vortex lattice model and subsequent wind tunnel tests and Navier-Stokes computations demonstrate the viability of the concept for co-ordinated turns, with individual and/or combined wing-tip deflections producing multi-axis, coupled control moments. The multi-axis nature of the generated moments tends to over-actuate the flight control system, leading to some redundancy, which could be exploited to optimise secondary objective functions such as drag or bending moment.

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Future Trends in Flight Control Systems

Journal of Navigation ◽

10.1017/s0373463300041199 ◽

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.

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Preview Display - The Mean of Decreasing Pilot Workload and Suppressing Nonlinear Effects in The Flight Control System

IFAC-PapersOnLine ◽

10.1016/j.ifacol.2021.04.112 ◽

2020 ◽

Vol 53 (5) ◽

pp. 350-355

Author(s):

Aleksandr V. Efremov ◽

Iliyas Kh. Irgaleev ◽

Mikhail S. Tyaglik

Keyword(s):

Control System ◽

Flight Control ◽

Nonlinear Effects ◽

Flight Control System ◽

The Mean

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Results of a Feasibility Study of a Prognostic System for Electro-Hydraulic Flight Control Actuators

International Journal of Prognostics and Health Management ◽

10.36001/ijphm.2021.v12i3.2935 ◽

2021 ◽

Vol 12 (3) ◽

Author(s):

Sylvain Autin ◽

Andrea De Martin ◽

Giovanni Jacazio ◽

Jérôme Socheleau ◽

George Vachtsevanos

Keyword(s):

Control Systems ◽

Feasibility Study ◽

Flight Control ◽

The Novel ◽

Flight Control System ◽

Commercial Aircraft ◽

Prognostic System ◽

Effective Technology ◽

Hydraulic Servo ◽

Commercial Aircrafts

Electro-Hydraulic Servo-Actuators (EHSA) are currently the most used actuation technology for primary flight control systems of civil and military aircrafts. Although some alternatives have emerged in the last decade, such as electromechanical or electro-hydrostatic solutions, electrohydraulic systems are still considered the most effective technology in flight-critical application of new commercial aircrafts. Moreover, the vast majority of aircraft currently in service are equipped with this technology. Considering the number of actuators typically employed in a primary flight control system and the expected service life of a commercial aircraft, the development of an effective PHM system could provide significant benefits to fleet operators and aircraft maintenance. This paper presents the results of a feasibility study of such a system for electro-hydraulic actuators used in fly-by-wire primary flight control systems, considering the actuator of a wide body commercial aircraft as use case. Aim of the research is the implementation of a PHM system without the addition of dedicated sensors, solution which would allow for the application of the proposed prognostic solution on both new and existing platforms. This paper describes the methodology and the results of the feasibility study through simulation and experimental activities, which shows how the novel PHM technologies proposed for a PHM system for the EHSAs of primary flight control actuators can allow the migration from scheduled to condition-based maintenance.

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New methodology for flight control system sizing and hinge moment estimation

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1177/09544100211063110 ◽

2021 ◽

pp. 095441002110631

Author(s):

Carlos Cabaleiro de la Hoz ◽

Marco Fioriti

Keyword(s):

Control System ◽

Design Process ◽

Flight Control ◽

Aircraft Design ◽

Flight Control System ◽

System Architectures ◽

Precise Control ◽

Moment Estimation ◽

Electric Aircraft ◽

Control Surfaces

Flight control surfaces guarantee a safe and precise control of the aircraft. As a result, hinge moments are generated. These moments need to be estimated in order to properly size the aircraft actuators. Control surfaces include the ailerons, rudder, elevator, flaps, slats, and spoilers, and they are moved by electric or hydraulic actuators. Actuator sizing is the key when comparing different flight control system architectures. This fact becomes even more important when developing more-electric aircraft. Hinge moments need to be estimated so that the actuators can be properly sized and their effects on the overall aircraft design are measured. Hinge moments are difficult to estimate on the early stages of the design process due to the large number of required input. Detailed information about the airfoil, wing surfaces, control surfaces, and actuators is needed but yet not known on early design phases. The objective of this paper is to propose a new methodology for flight control system sizing, including mass and power estimation. A surrogate model for the hinge moment estimation is also proposed and used. The main advantage of this new methodology is that all the components and actuators can be properly sized instead of just having overall system results. The whole system can now be sized more in detail during the preliminary design process, which allows to have a more reliable estimation and to perform systems installation analysis. Results show a reliable system mass estimation similar to the results obtained with other known methods and also providing the weight for each component individually.

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