Numerical design of an adaptive aileron

Advances in aircraft and spacecraft science, 2014

The paper presents the development of numerical models referred to a morphing actuated aileron. The structural solution adopted consists of an internal part made of a composite chiral honeycomb that bears a flexible skin with an adequate combination of flexural stiffness and in-plane compliance. The identification of such structural frame makes possible an investigation of different actuation concepts based on diffused and discrete actuators installed in the skin or in the skin-core connection. An efficient approach is presented for the development of aeroelastic condensed models of the aileron, which are used in sensitivity studies and optimization processes. The aerodynamic performances and the energy required to actuate the morphing surface are evaluated and the definition of a general energetic performance index makes also possible a comparison with a rigid aileron. The results show that the morphing system can exploit the fluid-structure interaction in order to reduce the actuation energy and to attain considerable variations in the lift coefficient of the airfoil.

Aeronautical Journal, 2018

A new wing-tip concept with morphing upper surface and interchangeable conventional and morphing ailerons was designed, manufactured, bench and wind-tunnel tested. The development of this wing-tip model was performed in the frame of an international CRIAQ project, and the purpose was to demonstrate the wing upper surface and aileron morphing capabilities in improving the wing-tip aerodynamic performances. During numerical optimisation with 'in-house' genetic algorithm software, and during wind-tunnel experimental tests, it was demonstrated that the air-flow laminarity over the wing skin was promoted, and the laminar flow was extended with up to 9% of the chord. Drag coefficient reduction of up to 9% was obtained when the morphing aileron was introduced. Copyright © Royal Aeronautical Society 2018.

Journal of Engineering Research and Reports, 2024

The preliminary structural design of ailerons in regional jet liners is essential because ailerons are critical control surfaces that enable the pilot to roll the airplane across its longitudinal direction. Ailerons are located on the trailing edge of the wing and are designed to create a differential lift between the wing's upper and lower surfaces, which generates a rolling moment that allows the aircraft to turn. The preliminary structural design of ailerons involves determining the appropriate size, shape, and material for the aileron structure, ensuring that it is strong enough to withstand the loads that it will experience during flight. The design must also consider factors such as weight, aerodynamics, and maneuverability. Ailerons are subjected to significant aerodynamic forces and loads during flight, so their structural design must be robust enough to withstand these loads without failing. If ailerons are not properly designed, they can fail, which can result in a loss of control of the aircraft, leading to a potentially catastrophic situation. Therefore, the preliminary structural design of ailerons is critical to ensure that the aircraft is safe to fly, and the pilot can control it effectively during all phases of flight

32nd AIAA Applied Aerodynamics Conference, 2014

In this paper the authors present an analysis of the boundary layer behavior, mainly concerning its transition from laminar to turbulent and its detachment, using morphing techniques applied to wing upper-surface airfoil and aileron airfoil. Morphing of the wing upper surface is achieved using two control points, and the original rigid aileron shape is changed using two methods; one method is based on the morphing technique used on the upper surface of the wing, the second method is based on rotations at different articulation points along the chord of the aileron. The upper-surface morphing coupled with either of the two aileron morphing methods use an 'in-house' genetic algorithm software which is here described. The ability of the morphing method to advance or delay the transition from laminar to turbulent flow on the upper surface of the wing is analyzed. The aileron shape changing methods are evaluated according to their improvement of the lift coefficient and their delay of the boundary layer detachment. This analysis is a prerequisite for the validation of the wing-with-aileron prototype, which will take place at the NRC wind tunnel.

Journal of Mechanical Engineering Science and Technology, 2020

Aileron is a control surface that functions as a regulator of roll motion. The movements of the ailerons are opposite to the left and right sides. Previous studies have shown that graphs of hinge moment coefficient (Chm) values increases with increasing angle of attack. This study is to determine the aerodynamic characteristics of aileron by combining the surface area of the vane into the aileron by varying the aileron's deflection. The calculation is performed using a numerical method in two dimensions (2D) commercial CFD simulation software. The results of the study concluded that the hinge moment coefficient for modified airfoil at δA =-20°, 0°, and 20° was-0.071, 0.078, and 0.177, respectively. These values are smaller when compared to Chm value in basic aileron that was-0.094, 0.095, and 0.201, respectively.

Composite Structures, 2009

The current full depth aluminium aileron installed on the P180 AVANTI aircraft has been selected, as reference baseline, for the design of a new CFRP aileron developed within the VITAS project (Vector for Innovative Sustainable Air Transportation). This new composite laminate structure, manufactured by using the RTM process, has been designed maintaining the same geometry, functional performances and attachment fittings of the aluminium component. An iterative design methodology, developed by using both simplified and detailed design approach, has led to an optimized aileron concept characterised by a strong reduction of the number of the structural subparts and by a considerable increase of the weight/ costs ratio. Finally, the effectiveness of the developed full scale demonstrator has been successfully proved at the ultimate static load, satisfying the same test performed for the certification of the aluminium aileron.

Journal of Guidance, Control, and Dynamics, 1990

AIAA Modeling and Simulation Technologies Conference, 2015

This paper offers an introduction to the concept of system modeling to validate the feasibility of a multidisciplinary actuation solution with the constraints of concrete research applications. To explain the modeling procedure, the case of a morphing wing aileron actuation solution is presented. The requirements and limitations for the design are presented, then a detailed solution is elaborated. Finally the modeling of this solution is developed in the Matlab/Simulink environment to validate its practicality. This approach generates a simple but representative model with a relatively high degree of accuracy without requiring detailed information about the internal system parts. The modeling system is a cornerstone of a morphing wing aileron control project with potential industrial applications.

WIT Transactions on the Built Environment, 2004

This work describes the structural design of a composite material aileron of a business aircraft with the target of weight reduction with respect to the metallic reference baseline. It proposes a multi-step procedure for the design and analysis of a composite material structure. A carbon-epoxy material is used for the structural item. An integrated procedure (FEM/analytical and computational formulations) for the design and analysis is developed. In the first level the structural item is considered as concentrated elements. The internal loads are evaluated by elementary theory and a preliminary layup configuration for the structural components (skin, spar, etc.) is chosen by means of a stand-alone approach using a structural sizing software. In the next step a finite element model of the structural item is developed with the preliminary layups, and a general-purpose finite element software is used to evaluate the internal FEA loads acting on the different structural components. Fina...

INCAS BULLETIN, 2016

In this project, a wing tip of a real aircraft was designed and manufactured. This wing tip was composed of a wing and an aileron. The wing was equipped with a composite skin on its upper surface. This skin changed its shape (morphed) by use of 4 electrical in-house developed actuators and 32 pressure sensors. These pressure sensors measure the pressures, and further the loads on the wing upper surface. Thus, the upper surface of the wing was morphed using these actuators with the aim to improve the aerodynamic performances of the wing-tip. Two types of ailerons were designed and manufactured: one aileron is rigid (non-morphed) and one morphing aileron. This morphing aileron can change its shape also for the aerodynamic performances improvement. The morphing wing-tip internal structure is designed and manufactured, and is presented firstly in the paper. Then, the modern communication and control hardware are presented for the entire morphing wing tip equipped with actuators and sensors having the aim to morph the wing. The calibration procedure of the wing tip is further presented, followed by the open loop controller results obtained during wind tunnel tests. Various methodologies of open loop control are presented in this paper, and results obtained were obtained and validated experimentally through wind tunnel tests.

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, 2013

Smart materials have been widely applied in morphing aerospace structures, improving performance and reducing weight and mechanical complexity when compared to conventional actuators. However these novel components also have intrinsic limitations that restrict the capabilities of the resultant structures. This paper introduces the Synergistic Smart Morphing Aileron (SSMA), which overcomes the individual limitations of the constituent materials. Independent control surfaces mechanisms, driven by shape memory alloy and micro-fiber composite actuators are presented, culminating in a fused design of both technologies that improves the overall actuation range and bandwidth. The concept of synergetic use of smart material is not widely diffused in the scientific community and it is added upon by this study.

AIAA Atmospheric Flight Mechanics Conference 2012, 2012

The paper presents a smart way to actuate and to control the airfoil shape of a morphing wing. The actuation system development is based on some smart material actuators like Shape Memory Alloys, disposed in two parallel actuation lines, and its control is performed by using a fuzzy logic PD controller of Mamdani type.

2000

The subject of this investigation is the application of CFD computations to flows around airplane ailerons combined with flight mechanical simulations to study the impact on airplane rolling maneuvers and aileron dynamics. The practical application is on Saab 2000 commuter airplane. In the validation of CFD computations the low speed airfoils FX 61-163 and FX 6617AII-182 were investigated with the 2D Navier-Stokes code ns2d by comparing the computations with selected wind tunnel experiments. The medium speed MS(1)-0313 and the transonic DLBA032 airfoils with plain ailerons were investigated with ns2d and NSMB codes in selected wind tunnel cases representative for the ailerons of Saab 2000 aircraft. One algebraic and three k-e turbulence models were used in the calculations at different aileron deflections. The effects of local mesh refinement and grid convergence were studied on the aerodynamic coefficients. Two-dimensional CFD computations were made on Saab 2000 aileron to compare ...

AIAA Atmospheric Flight Mechanics Conference, 2011

The main objectives of this research work are: the design and the wind tunnel testing of a controller for a new morphing mechanism using smart materials made of Shape Memory Alloy (SMA) for the actuators, and the aero-elasticity studies for the morphing wing. The finally obtained configuration for the controller is a combination of a bi-positional controller (on-off) and a PI (proportional-integral) controller, due to the two phases (heating and cooling) of the SMA wires' interconnection. Firstly, the controller is used for the open loop development step of a morphing wing project, while, further, it is included as an internal loop in the closed loop architecture of the morphing wing system. In the controller design procedure four step are considered: 1) SMA actuators model numerical simulation for different loading force cases; 2) linear system approximation in the heating and cooling phases using Matlab's System Identification Toolbox and the numerical values obtained in the first step; 3) selecting the controller type and its tuning for each of the two SMA actuators' phasesheating and cooling; and 4) integration of the two controllers just obtained into a single controller. For the controller validation three actions are taken: 1) numerical simulation; 2) bench testing; and 3) wind tunnel testing. For the third part of this study, aeroelastic studies, the purpose is to determine the flutter conditions in order to be avoided during wind tunnel tests. These studies show that aeroelastic instabilities for the morphing configurations considered appears at Mach number 0.55, which is higher than the wind tunnel Mach number limit speed of 0.3.