本研究是運用超塑成形技術(Superplastic Forming Technology)實驗製作(原始工件尺寸及縮小版)中型民航機機翼前緣(Leading Edge)之整流罩(Fairing Cover)、研究探討其成形方式(如熱引伸輔助超塑成形及直接超塑成形)與模具輪廓對於成形後厚度分布的影響。
在執行超塑成形之前，先將超塑鋁合金5083材料進行預折彎加工，在依其所需之氣壓-時間成形曲線來完成工件，預折彎之目的在於使鈑材在執行超塑成形之前，可預先縮短鈑片與成形模具之間的距離，使其工件成形後之厚度分布均勻性更佳。
探討成形距離之重要性後，決定於模具設計熱引伸輔助的加工程序或是改變模具的輪廓設計，來進一步縮短該成形距離，以期此工件可以有更佳的厚度分布均勻性。

This paper is using superplastic forming technology to produce (original size and small size) medium-sized civil aircraft wing leading edge fairing cover. To analyze the influence of forming method (hot draw mechanical pre-forming and conventional superplastic forming) and die contour on thickness distribution.
Before doing the superplastic forming, first, we pre-bend the 5083 aluminum , then make the component according to the required pressure - time forming curves. The purpose of the pre-bend is to shorten the distance between the sheet and the die before doing the superplastic forming, As a results, the thickness of the component will more uniform.
After realizing the importance of shorten the forming distance, we decide to add a hot drawing mechanical pre-forming or change the contour of the die to shorten the distance. We hope that the thickness of the component will more uniform.

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