Modeling of integrated shape memory alloy and Macro-Fiber Composite actuated trailing edge

In this paper, the experimental investigation into the enhancement of mechanical strength in shape memory alloy (SMA) fiber composites is made by using knotted fiber at the two ends instead of straight fiber. TiNi SMA fiber with both ends knotted is used for purpose of better ensuring stress transfer from the matrix to the fiber than straight fiber. Tension test is carried out above the austenitic finish temperature in air. Specimens are heated by means of electrical resistive lamplight heating. The results indicate that the mechanical strength is larger in the knotted fiber composite than in the straight fiber composite. Knotted fiber exerts the superiority of TiNi SMA fiber composite.

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Flight Test of a Shape Memory Alloy Actuated Adaptive Trailing Edge Flap

Volume 1: Multifunctional Materials; Mechanics and Behavior of Active Materials; Integrated System Design and Implementation; Structural Health Monitoring ◽

10.1115/smasis2016-9141 ◽

2016 ◽

Cited By ~ 7

Author(s):

F. T. Calkins ◽

J. H. Mabe

Keyword(s):

Shape Memory Alloy ◽

Shape Memory ◽

High Speed ◽

Flight Test ◽

Federal Aviation Administration ◽

Trailing Edge ◽

Loop Control ◽

Rotary Actuator ◽

Trailing Edge Flaps ◽

Improved Performance

The Boeing Company has a goal of creating aircraft that are capable of continuous optimization for all flight conditions. Recent advances in SMA actuation and a detailed understanding of wing design were combined to design, build, and safely demonstrate small trailing edge flaps driven by SMA actuation. As part of a 2012 full-scale flight test program a lightweight and compact Shape Memory Alloy (SMA) rotary actuator was integrated into the hinge line of a small flap on the trailing edge of a commercial aircraft wing. This Adaptive Trailing Edge program was part of a Boeing and Federal Aviation Administration (FAA) collaboration. Aerodynamic studies of these small trailing edge flaps show that improved performance requires multiple flap configurations that vary with flight regime. Configurations include small angles of deployment for reduced fuel burn and emissions during high speed cruise and larger angles of deployment for increased lift and lower noise during takeoff and approach. SMA actuation is an ideal compact solution to position these small flaps and increase aircraft performance by simply and efficiently altering the wings aerodynamic characteristics for each flight segment. Closed loop control of the flap’s position, using the SMA actuator, was demonstrated at multiple flight conditions during flight tests. Results of the successful flight test on a 737–800 commercial airplane and the significantly improved performance benefits will be presented. This is the first flight test of an SMA rotary actuator system, which was matured from TRL 4 to TRL 7 during the program.

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Design Analysis of Two Ways Shape Memory Alloy (SMA) Actuated Aerofoil

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.564.340 ◽

2014 ◽

Vol 564 ◽

pp. 340-345

Author(s):

Mohd Roshdi Hassan ◽

Yong Thian Haw ◽

Mohd Nasrisyam Asri

Keyword(s):

Shape Memory Alloy ◽

Shape Memory ◽

Initial Position ◽

Design Analysis ◽

Analysis Software ◽

Trailing Edge ◽

Element Analysis ◽

Rubber Material ◽

Length Width ◽

Simulation Results

This paper describes the design analysis of the behavior of a shape memory alloy (SMA) plate embedded into an aerofoil. Experimentation and simulation were done to fulfill this purpose. The aerofoil is made of silicone rubber material. The SMA plate which was embedded into the maximum chamber of aerofoil during the fabrication process was measured at approximately 175mm, 63mm and 3mm in length, width and thickness respectively. Experimentation was conducted to show that the SMA plate is able to produce two-way shape memory effect. Simulation was executed by using Abaqus 6.9-1 (finite element analysis software). The aerofoil profile was changed by the movement of SMA plate, which has subsequently changed the angle of aerofoil’s trailing edge. The result from the experiment shows that the aerofoil’s trailing edge has undergone a certain amount of displacement after heated. Upon cooling, the aerofoil’s trailing edge did not return to its initial position. Based on this analysis, it is clear that the simulation results are in agreement with the findings of experimental results.

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

Actuators ◽

10.3390/act10070160 ◽

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.

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Smart morphing based on shape memory alloy plate

Journal of Engineering Design and Technology ◽

10.1108/jedt-08-2014-0056 ◽

2016 ◽

Vol 14 (3) ◽

pp. 475-488 ◽

Cited By ~ 3

Author(s):

Velaphi Msomi ◽

Graeme John Oliver

Keyword(s):

Shape Memory Alloy ◽

Shape Memory ◽

Leading Edge ◽

Hydraulic Systems ◽

Trailing Edge ◽

Alloy Plate ◽

Content Type ◽

Niti Sma ◽

Heat Application ◽

Current Maximum

Purpose This article reports on the possibility of using nickel titanium shape memory alloy (NiTi SMA) plates rather than NiTi SMA wire for actuation application in the aerospace industries. Design/methodology/approach A scaled-down model of smart aileron was constructed based on NiTi SMA plate and aluminium plate. Prior to the manufacturing process, NiTi SMA plates had to be trained to suit our application. The leading edge was constructed using trained NiTi SMA plates, whereas the trailing edge was constructed using aluminium plates. Pop rivets were used in joining the parts or in the construction of the smart aileron, and riveting was preferred as it is mostly used in the aerospace industry for surface construction. The constructed smart aileron was tested for vertical upward and downward deflection using heat application, and the deflection was measured using deflection transducer. The heat was sourced from heater mat kits that were laminated inside the smart aileron. The temperature and the deflection data were recorded and analyzed. Findings It was found that NiTi SMA plates could give a deflection on the trailing edge of the smart aileron. The current maximum deflection was found to be 3 mm, which corresponds to aileron rotation of about 0.57 degrees. Originality/value The paper presents a hinge-less alternative in bringing the rolling motion of the flight. The constructed model of smart aileron can be used to replace the existing aileron, which is activated through hydraulic systems. So, the newly constructed smart aileron can be used with the benefit of reducing weight, because it does not use the hydraulic systems like the existing one.

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