复合材料加筋板在冲击作用下的损伤容限尺寸

H. Dalir
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引用次数: 0

摘要

飞机复合材料加筋结构在动力和冲击载荷作用下的设计需要在全尺寸结构上进行多种试验测试。本文研究了基于有限元模型的加劲肋无翼缘在竖向和侧向冲击下采用分尺寸试样的可行性。对从全尺寸(26.4 × 48.4 × 2.4英寸)冲击试验板上仔细提取的亚尺寸试样进行了模拟。还确定了内部落锤冲击试验机的主要要求规格,讨论了所需的夹具/夹具配置。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Damage tolerance coupon sizing of composite stiffened panels under impact
The design of aircraft composite stiffened structures subjected to dynamic and impact loadings requires several experimental testing scenarios on the full-size structure. The present paper deals with investigating the feasibility of the use of sub-size test specimens under vertical and lateral impacts on the stiffener free flange based on finite element (FE) models. Simulations were performed on sub-size specimens carefully extracted from the full-size (26.4 × 48.4 × 2.4 in3) impact test panels. The main required specifications of an in-house falling weight impact tester were also determined, discussing the required fixture/jig configuration.
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