CAJ | 학술논문

本文立足于工程实际，对无人机机翼的静强度进行了计算，并针对机翼的肋板，求解了其应力强度因子，得到了裂纹长度与应力强度因子的关系。随着裂纹的增长，应力强度因子不断增长，结构最终破坏失效。本文目的是为无人机机翼结构的后续断裂性能研究提供分析方法和数据，为结构选型提供基础数据。
본문립족우공정실제，대무인궤궤익적정강도진행료계산，병침대궤익적륵판，구해료기응력강도인자，득도료렬문장도여응력강도인자적관계。수착렬문적증장，응력강도인자불단증장，결구최종파배실효。본문목적시위무인궤궤익결구적후속단렬성능연구제공분석방법화수거，위결구선형제공기출수거。
In this article, based on the practical engineering, the static strength of the UAV has been calculated, and for the wing’s rib, solving the stress intensity factor, get the crack length relationship with the stress intensity factor. With the growth of the crack, the stress intensity factor is growing, structure ultimately fail. The purpose of this article is providing a method for analysing the fracture properties of the UAV wing structure, and providing datum for selecting structure type.