The manoeuvrability performance of a twist morphing MAV has been the main interest for the past researches. 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. Therefore, the effect of a twist morphing wing mobility on the lift distribution of MAV wing is still remained unknown. Thus, present work was carried out to compare the lift performance between a twist morphing wing with membrane and rigid MAV wing design. 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. 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. 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. 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
TiCN and TiAlN coated twist drills were subjected to drilling tests to investigate the failure mechanisms during drilling operation. The drilling tests were performed on a carbon steel plate with a thickness of 25 mm and the depth of drill was set at 20 mm. The drill performance parameters were set at a spindle rotation of 1,600 rpm and feed rate of 20 mm/min. Each sample was then subjected to Scanning Electron Microscopy examination to investigate the wear mechanisms operated during drilling. Microstructural examination showed that the abrasion, adhesion and thermal wear mechanisms are operated during drilling process.
The geometric twist characteristic on twist morphing MAV wing has significant influence on its aerodynamic performances. Higher geometric twist magnitude induces higher lifts and drags generation. However, in order to determine the geometric twist performance, a detail analysis has to be carried out to extract the local angle of attack (AOA) value on each wing cross section. Thus, current works introduces a new method in extracting the local AOA value on a twist morphing MAV wing. The method manipulates the automated coordinate generation produced by Ansys software and combined the generated coordinates with manual determination of local AOA magnitude. Based on the analysis executed on a twist morphing wing sample, 30 local AOA values were obtained from 30 wing cross sections. By using the local AOA value at the root chord and wing tip, the geometric twist magnitude or twist intensity for a twist morphing wing is determined. Based on a selected twist morphing MAV wing sample, the local AOA extraction method able to calculate the wing geometric twist at ϵ = 12.5°.
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