Navier-Stokes investigation of blunt trailing-edge airfoils using O grids

Khalid, M.; Jones, D. J.

doi:10.2514/3.46416

Cited by 19 publications

(4 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Actuators 2023, 12, 350 7 of 29 aerodynamics part of the research project was provided by the NRC-IAR team [46,47]. Additionally, the obtained optimized shapes were stored in a computer database and further used during the project development.…”

Section: Morphing Wing Project Context and Description Of The Actuati...mentioning

confidence: 99%

“…The obtained optimized airfoil shapes provided the necessary initial data (Figure 3) to start the design of the actuation system. The laminar WTEA-TE1 reference airfoil used as a starting point for the aerodynamics part of the research project was provided by the NRC-IAR team [46,47]. Additionally, the obtained optimized shapes were stored in a computer database and further used during the project development.…”

Section: Morphing Wing Project Context and Description Of The Actuati...mentioning

confidence: 99%

See 1 more Smart Citation

A Self–Tuning Intelligent Controller for a Smart Actuation Mechanism of a Morphing Wing Based on Shape Memory Alloys

Grigorie,

Botez

2023

Actuators

View full text Add to dashboard Cite

The paper exposes some of the results obtained in a major research project related to the design, development, and experimental testing of a morphing wing demonstrator, with the main focus on the development of the automatic control of the actuation system, on its integration into the experimental developed morphing wing system, and on the gain related to the extension of the laminar flow over the wing upper surface when it was morphed based on this control system. The project was a multidisciplinary one, being realized in collaboration between several Canadian research teams coming from universities, research institutes, and industrial entities. The project’s general aim was to reduce the operating costs for the new generation of aircraft via fuel economy in flight and also to improve aircraft performance, expand its flight envelope, replace conventional control surfaces, reduce drag to improve range, and reduce vibrations and flutter. In this regard, the research team realized theoretical studies, accompanied by the development and wind tunnel experimental testing of a rectangular wing model equipped with a morphing skin, electrical smart actuators, and pressure sensors. The wing model was designed to be actively controlled so as to change its shape and produce the expansion of laminar flow on its upper surface. The actuation mechanism used to change the wing shape by morphing its flexible upper surface (manufactured from composite materials) is based on Shape Memory Alloys (SMA) actuators. Shown here are the smart mechanism used to actuate the wing’s upper surface, the design of the intelligent actuation control concept, which uses a self–tuning fuzzy logic Proportional–Integral–Derivative plus conventional On–Off controller, and some of the results provided by the wind tunnel experimental testing of the model equipped with the intelligent controlled actuation system. The control mechanism uses two fuzzy logic controllers, one used as the main controller and the other one as the tuning controller, having the role of adjusting (to tune) the coefficients involved in the operation of the main controller. The control system also took into account the physical limitations of the SMA actuators, including a software protection section for the SMA wires, implemented by using a temperature limiter and by saturating the electrical current powering the actuators. The On–Off component of the integrated controller deactivates or activates the heating phase of the SMA wires, a situation when the actuator passes into the cooling phase or is controlled by the Self–Tuning Fuzzy Logic Controller.

show abstract

Section: Morphing Wing Project Context and Description Of The Actuati...mentioning

confidence: 99%

Section: Morphing Wing Project Context and Description Of The Actuati...mentioning

confidence: 99%

A Self–Tuning Intelligent Controller for a Smart Actuation Mechanism of a Morphing Wing Based on Shape Memory Alloys

Grigorie,

Botez

2023

Actuators

View full text Add to dashboard Cite

show abstract

“…As a reference airfoil, the natural laminar flow airfoil, wind-tunnel experimental airfoil, was chosen. Its aerodynamic performance was investigated at the Institute for Aerospace Research, National Research Council Canada (IAR-NRC) in the transonic regime in [13]. Thirty-five flight conditions were studied during wind-tunnel tests: seven values for the angle of attack, which varied between 1 and 2 deg, and five Mach number values within the range of M0:2; 0:3.…”

Section: Introductionmentioning

confidence: 99%

Modeling and Testing of a Morphing Wing in Open-Loop Architecture

Попов¹,

Grigorie²,

Botez³

et al. 2010

Journal of Aircraft

View full text Add to dashboard Cite

This paper presents the modeling and experimental testing of the aerodynamic performance of a morphing wing in open-loop architecture. We show the method used to acquire the pressure data from the external surface of the flexible wing skin, using incorporated Kulite pressure sensors and the instrumentation of the morphing controller. The acquired pressure data are analyzed through fast Fourier transforms to detect the magnitude of the noise in the surface airflow. Subsequently, the data are filtered by means of high-pass filters and processed by calculating the root mean square of the signal to obtain a plot diagram of the noise in the airflow. This signal processing is necessary to remove the inherent noise electronically induced from the Tollmien-Schlichting waves, which are responsible for triggering the transition from laminar to turbulent flow. The flexible skin is required to morph the shape of the airfoil through two actuation points to achieve an optimized airfoil shape based on the theoretical flow conditions similar to those tested in the wind tunnel. Two shape memory alloy actuators with a nonlinear behavior drive the displacement of the two control points of the flexible skin toward the optimized airfoil shape. Each of the shape memory actuators is activated by a power supply unit and controlled using the Simulink/MATLAB® software through a self-tuning fuzzy controller. The methodology and the results obtained during the wind-tunnel test proved that the concept and validity of the system in real time are discussed in this paper. Real-time acquisition and signal processing of pressure data are needed for further development of the closed-loop controller to obtain a fully automatic morphing wing system.

show abstract

“…A first phase of this project involved the determination of optimized airfoils available for 35 different flow conditions expressed in terms of five Mach numbers and seven angles of attack combinations. The optimized airfoils, derived from a laminar WTEA-TE1 reference airfoil [19,20], were calculated and were used as a starting point in the actuation system design. Three steps were completed in the actuation system design phase: optimization of the number and positions of flexible skin actuation points, establishment of each actuation line's architecture, and the analytical modelling of the smart materials actuators used in this application.…”

Section: Introductionmentioning

confidence: 99%

On–off and proportional–integral controller for a morphing wing. Part 1: Actuation mechanism and control design

Grigorie

Попов

Botez

et al. 2011

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

The main objective of this research work is the development of an actuation control concept for a new morphing actuation mechanism made of smart materials, which is built from a shape memory alloy (SMA). Two lines of smart actuators were incorporated to a rectangular wing to modify the upper wing surface, made of a flexible skin, with the intention to move the laminar-to-turbulent transition point closer to the wing trailing edge. After a brief introduction of the morphing wing system architecture and requirements, the actuation lines' design and instrumentation are presented. The integrated controller controls the SMA actuators via an electrical current supply, so that the transducer position can be used to eliminate the deviation between the required values for vertical displacements (corresponding to the optimized airfoils) and their physical values. The final configuration of the integrated controller is a combination of a bi-positional (on–off) controller and a PI (proportional–integral) controller, due to the two heating and cooling phases of the SMA wires' interconnection. This controller must behave like a switch between the cooling and the heating phases, situations where the output current is 0 A, or is controlled by a PI type law. The PI controller for the heating phase is optimally tuned using integral and surface minimum error criteria (Ziegler–Nichols). The controller is numerically tested on the linear identified system in terms of time response, Bode diagram, amplitude and phase stability margins, and root-locus.

show abstract

Navier-Stokes investigation of blunt trailing-edge airfoils using O grids

Cited by 19 publications

References 3 publications

A Self–Tuning Intelligent Controller for a Smart Actuation Mechanism of a Morphing Wing Based on Shape Memory Alloys

A Self–Tuning Intelligent Controller for a Smart Actuation Mechanism of a Morphing Wing Based on Shape Memory Alloys

Modeling and Testing of a Morphing Wing in Open-Loop Architecture

On–off and proportional–integral controller for a morphing wing. Part 1: Actuation mechanism and control design

Contact Info

Product

Resources

About