본 연구에서는 주로 항공기의 구조물용으로 사용되고 있는 소위 초듀랄루민이 라 불리는 산업용 2024Al합금에 대하여 3~5kg/m $m^{2}$의 응력범위 및 0.6~0.7Tm의 온도범위에서의 고온크리이프 시험을 통하여 고온정상크리이프 변형속도 및 크리이프 파단수명에 대하여 살펴보고자 한다.
Constant load creep tests have been carried out over a range of stresses at high temperatures. The experimental equations of the steady-state creep rate and creep-rupture life were respectively found to be related to the normalized applied-stress and temperature as ln.epsilon.$_{s}$ =6.10 on.sigma./ $E_{T}$-12.81*10$^{3}$ 1/T+15.98 (h $r^{-1}$) ln $t_{R}$=-6.24ln.sigma./ $E_{T}$+15.08*10$^{3}$1/T-23.66 (hr) and the equation of creep-rupture life had a good agreement with the expression of the Minimum-Commitment Method (MCM). However, the relationship between the steady-state creep rate and the creep-rupture life, noted by Monkman and Grant, lnt/snb R/ = mln.epsilon.$_{S}$+b made a considerable deviation against the present creep-rupture data. It is believed that this problem is to be discussed and investigated continually.lly.lly..
