Numerical analysis on shape memory alloy–based adaptive shock control bump

2018 ◽  
Vol 29 (15) ◽  
pp. 3055-3066 ◽  
Author(s):  
Lin Hao ◽  
Jinhao Qiu ◽  
Hongli Ji ◽  
Rui Nie
Keyword(s):  
Shape Memory Alloy ◽  
Shape Memory ◽  
Angle Of Attack ◽  
Aerodynamic Characteristics ◽  
Wave Drag ◽  
Initial Shape ◽  
Thermally Activated ◽  
Bump Height ◽  
Shock Control Bump ◽  
Shock Control

A three-dimensional adaptive shock control bump made of shape memory alloy is proposed for transonic wings. The methodology to adaptively change the configuration of the airfoil using the shape memory alloy bump to reduce the shock strength and wave drag is numerically demonstrated using an airfoil RAE2822. The shape memory alloy bump is trained to have a flat initial shape with certain initial strain and can swell up when thermally activated. Boyd–Lagoudas phenomenological model is implemented in finite element method and used to compute the two-dimensional profile and the height of the shape memory alloy bump during thermal activation. The results show that the shape memory alloy bump can generate a considerable deflection due to the reverse phase transformation when thermally activated. The dependence of aerodynamic characteristics of the wing on the height of the shape memory alloy bump and the angle of attack is investigated using computational fluid dynamics method. The results show that there is an optimal bump height for a given angle of attack and the bump with a given height is effective only in certain range of angle of attack. Optimization of bump height and the corresponding driving temperature are carried out under variable angles of attack with the lift-to-drag ratio as the objective function.

scholarly journals Effects of Trailing Edge Deflections Driven by Shape Memory Alloy Actuators on the Transonic Aerodynamic Characteristics of a Super Critical Airfoil

Actuators ◽  
2021 ◽  
Vol 10 (7) ◽  
pp. 160
Author(s):  
Binbin Lv ◽  
Yuanjing Wang ◽  
Pengxuan Lei
Keyword(s):  
Mach Number ◽  
Shape Memory Alloy ◽  
Shape Memory ◽  
Angle Of Attack ◽  
Aerodynamic Characteristics ◽  
Smart Structure ◽  
Trailing Edge ◽  
Edge Based ◽  
Constant Deformation ◽  
Transonic Wind Tunnel

A smart structure to actuate a morphing trailing edge based on the super critical airfoil NASA sc-0714(2) was designed and verified in a transonic wind tunnel. The pressure distribution over the wing was measured to evaluate the structure ability and effects of trailing edge deflections on the aerodynamic characteristics. In the experiment, Mach number was from 0.4 to 0.8, and the angle of attack was from 0° to 6°. The results showed that the smart structure based on shape memory alloy could carry aerodynamic loads under transonic flow and deflect the trailing edge. When the driving force was constant, deformation would be influenced by the Mach number and angle of attack. Increasing the Mach number weakened the actuation capability of the smart structure, which decreased the deflection angle and rate of the trailing edge. The influence of the angle of attack is more complex, and couples with the influence of the Mach number. The higher the Mach number, the stronger the influence of the angles of attack. Additionally, the trailing edge deflection would dramatically change the flow structure over the airfoil, such as the shock wave position and strength. If separation was caused by the trailing edge deflection, the limitation of the smart structure would be further found.

Use of shape memory alloy for active shock control bump application

2021 ◽  
pp. 1045389X2110386
Author(s):  
Jinhao Qiu ◽  
Lin Hao ◽  
Hongli Ji ◽  
Chen Zhang ◽  
Rui Nie
Keyword(s):  
Shape Memory Alloy ◽  
Shape Memory ◽  
Mechanical Response ◽  
Shape Change ◽  
Operating Conditions ◽  
Training Procedure ◽  
Scanning Calorimetry ◽  
Mechanical Responses ◽  
Shock Control Bump ◽  
Shock Control

A shape memory alloy (SMA) with composition of Ni50.1Ti49.9 (at. %) was used for fabrication of a 3-D bump structure intended for use as an active shock control bump (SCB) into a transonic wing. This kind of bump is a variable-geometry structure designed to reduce the drag induced by shock wave ensure wing’s aerodynamic performance over the entire range of operating conditions. To meet this target, the SMA bump requires to exhibit two-way shape memory effect (TWSME) so that it can yield continuous shape change by properly changing the driving temperature. Result from differential scanning calorimetry was first presented to provide material’s phase transformation temperatures. To obtain the TWSME, a thermo-mechanical training procedure was proposed and a set of training devices were designed for training SMA bump. The SMA bump in this paper is trained to have a relatively flat shape in high temperature and can swell up when cooling. After more than 80 times training, the TWSME of the material tends to be stable. Then the thermo-mechanical responses of the SMA bump which is subjected to about 100 times training was tested. The result shows that the trained SMA bump can generate about 1.2 mm maximum recoverable deformation during martensitic transformation, which is about 3% of the ratio of the deformation region. Finally, the influence of external load on the thermo-mechanical response of the trained SMA bump were also studied.

scholarly journals Thermally activated iron-based shape memory alloy for strengthening metallic girders

2019 ◽  
Vol 141 ◽  
pp. 389-401 ◽  
Author(s):  
Mohammadreza Izadi ◽  
Ardalan Hosseini ◽  
Julien Michels ◽  
Masoud Motavalli ◽  
Elyas Ghafoori
Keyword(s):  
Shape Memory Alloy ◽  
Shape Memory ◽  
Thermally Activated ◽  
Iron Based

Shape Memory Alloy Materials and Exercise-Induced Bone Injury

2013 ◽  
Vol 454 ◽  
pp. 257-262
Author(s):  
Jian Wei Zhou ◽  
Jiang Yuan Hou ◽  
Yong Tao Shi
Keyword(s):  
Shape Memory Alloy ◽  
Shape Memory ◽  
Sports Injuries ◽  
Special Functions ◽  
Nickel Titanium ◽  
Initial Shape ◽  
Bone Injury ◽  
Novel Material ◽  
Shape Memory Materials ◽  
Exercise Induced

Shape memory materials are materials with special functions set of sensing and actuation in one. The shape memory alloy is one of the most important materials in shape memory materials. Shape memory alloy is a kind of alloy that alloy with initial shape in low temperature by the plastic deformation and fixed into another shape, by heating to a temperature above the critical, can be restored into the initial shape. The characteristic of shape memory alloy mainly has the shape memory effect and super elastic effect. Nickel titanium memory alloy is not used in the fracture of limbs, in recent years are also used in the spine and femoral head fracture. Nickel titanium memory alloy has good biocompatibility, and has the characteristics of super elasticity, low magnetic, wear resistance, fatigue resistance, corrosion resistance, as a novel material for internal fixation in the treatment of sports injuries are widely used.

DESIGN OPTIMIZATION OF C-SHAPED SUPERELASTIC SMA SHEET WITH CONSTANT FORCE

2018 ◽  
Vol 18 (01) ◽  
pp. 1750064 ◽  
Author(s):  
MINGHUI WANG ◽  
HONGLIU YU ◽  
BAOLIN LIU ◽  
LIANGFAN ZHU ◽  
YUN LUO
Keyword(s):  
Shape Memory Alloy ◽  
Shape Memory ◽  
Large Deformation ◽  
Soft Tissues ◽  
Alloy Sheet ◽  
Experimental Results ◽  
Constant Force ◽  
Force Component ◽  
Element Analysis ◽  
Initial Shape

Constant force component is very useful in medical device, such as forceps with constant force, which may prevent soft tissues from injures due to overloading. This paper studied the optimization procedure in constant force component for superelastic shape memory alloy, and tried to find the rule of obtaining constant force within a relatively large deformation range for superelastic C-shaped shape memory alloy sheet. The optimization concept of combing finite element analysis in ANSYS with genetic algorithm in MATLAB was presented for designing constant force component using superelastic SMA. The computational optimization and experimental results of the C-shaped shape memory alloy sheet showed that the proposed optimization method was potential for superelastic shape memory alloy. The optimization results were consistent with the experimental results. It was demonstrated that constant force could be obtained within a relatively large deformation range by varying the initial shape of the superelastic SMA component.

Overview of Boeing’s Shape Memory Alloy Based Morphing Aerostructures

2008 ◽  
Author(s):  
F. T. Calkins ◽  
J. H. Mabe ◽  
R. T. Ruggeri
Keyword(s):  
Shape Memory Alloy ◽  
Shape Memory ◽  
Rotor Blade ◽  
Continuous Optimization ◽  
Engine Performance ◽  
Flight Test ◽  
Aerodynamic Characteristics ◽  
System Level ◽  
Variable Geometry ◽  
Boeing Company

The Boeing Company has a goal of creating aircraft that are capable of continuous optimization for all flight conditions. Toward this goal we have developed morphing-capable, adaptive structures based on Shape Memory Alloy (SMA) technology that enable component and system level optimization at multiple flight conditions. The SAMPSON Smart Inlet program showed that fully integrated SMA wire bundles could provide a fighter aircraft with a Variable Engine Inlet capability. The Reconfigurable Rotor Blade program demonstrated the ability of highly robust, controlled 55-Nitinol tube actuators to twist a rotor blade in a spin stand test to optimize aerodynamic characteristics. The Variable Geometry Chevrons program, which was the first use of 60-Nitinol for a major aerospace application, included a flight test and static engine test of GE90–115B engine fitted with controlled morphing chevrons that reduced noise and increased engine efficiency. The Deployable Rotor Tab employed tube actuators to deploy and retract small fences which are capable of significantly reducing blade vortex interaction generated noise on a rotorcraft. Most recently, the Variable Geometry Fan Nozzle program has built on the VGC technology to demonstrate improved jet engine performance. The Boeing Company continues to mature SMA technology in order to develop innovative applications and support their commercialization.

Morphing of an adaptive shock control bump using pressurized chambers

2020 ◽  
Vol 31 (15) ◽  
pp. 1821-1837
Author(s):  
Nuno Alves de Sousa ◽  
Markus Kintscher ◽  
Afzal Suleman
Keyword(s):  
Three Dimensional ◽  
Wave Structure ◽  
Wave Drag ◽  
Geometrical Parameters ◽  
Shock Control Bump ◽  
Shock Control ◽  
Interaction Control ◽  
Design Changes ◽  
Viscous Losses ◽  
Boundary Layer Interaction

The dawn of research on shock and boundary layer interaction control dates back to the 1970s, when humped transonic aerofoils were first studied as a means to improve the performance of supercritical aerofoil technology at off-design conditions. Since then, shock control bumps have been found to be promising devices for such kind of flow control. They have a smearing effect on the shock wave structure achieved through isentropic pre-compression of the flow upstream of the main shock and can significantly lower wave drag without incurring unacceptable viscous losses. However, their performance is strongly dependent on a set of geometrical parameters which must be adjusted according to the ever-changing flight conditions. A concept for an adaptive shock control bump is therefore presented. The proposed actuation mechanism aims at a compact, lightweight and simple structure which could be integrated into the spoiler region of near-future aircraft without major design changes required. Numerical optimization of a simplified analytical model of the structure is used to investigate the shock control bump adaptation to various aerodynamic target shapes. Compromises between geometrical conformity and both structural and actuation related requirements are studied. Furthermore, an outlook is given on design issues related to three-dimensional effects on a finite span shock control bump.

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