In contrast, the in-plane stiffness is relatively high however, the necessary deformations that are required to change the aerodynamic response can still be attained while maintaining the surface area constant. The partially active surface is designed to have sufficient bending stiffness in the chordwise and spanwise directions to sustain shape under aerodynamic loading.
An experimental evaluation of the wing which employs a continuous inextensible surface, continuous boundary conditions, and surface-bonded piezoelectric actuators is presented. However, twist morphing wing had slightly suffered from (at least 1°) earlier stall angle and produced almost similar maximum lift coefficient magnitude to the membrane wing.Ī solid-state piezocomposite variable-camber morphing wing is proposed for fixed-wing aircraft that operate in the low Reynolds number regime. The lift results show that twist morphing wing able to produce (5% to 20%) higher lift magnitude compared to the membrane and rigid wing for every angle attack cases at pre-stall angle. Each MAV wing has identical wing dimension except for twist morphing wing where a 3N morphing force was imposed on the wing to produce the twist mobility. A quasi-static aeroelastic analysis by using the Ansys-Fluid Structure Interaction (FSI) method is utilized in current works to calculate the lift performance for each MAV wing design. Thus, present work was carried out to compare the lift performance between a twist morphing wing with membrane and rigid MAV wing design. Therefore, the effect of a twist morphing wing mobility on the lift distribution of MAV wing is still remained unknown.
However, aerodynamic behaviour of a twist morphing wing is not fully explored due to limited MAV wing size, limited energy budgets, complicated morphing mechanism, and complex aerodynamic-wing structural interaction. The manoeuvrability performance of a twist morphing MAV has been the main interest for the past researches. The method offers simpler mechanism to replace those active control devices implementation on actual aircraft design. Such wing will enable the aircraft to accommodate multiple flight regimes and obtain better flight performance. The concept is inspired from bird flight which able to change its wing depends on different situation. Morphing wing surfaces change its geometry during flight with view to improve the aerodynamics performances of aircraft. Each morphing concept has the idea in improving the aircraft performance in multiple mission flight.
Morphing wing can be categorized into three solutions such as wing planform alteration, wing out of plane transformation and airfoil adjustment.
The review highlighted the previous researchers works on morphing wing type, its applications and advantages. This method recently known as morphing wing. Thus the wing shape demanded to evolve or change with view to adapt with different flight condition. However fixed wing design has disadvantages since the aircraft's wing unable the to achieve maximum flight performance in all flight condition. Aircraft flight performance can be increased by optimizing the wing design.
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