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EFFECTS OF PROCESSING AND LOADING ON EQUIATOMIC NITI FATIGUE LIFE AND LOCALIZED FAILURE MECHANISMS

机译:加工和加载对等量亚稳态疲劳寿命和局部失效机理的影响

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Shape Memory Alloys (SMAs) have many promising applications in the aerospace, automotive, and energy industries. However, due to a lack of understanding of their actuation fatigue, applications are sometimes limited to non-structural or non-critical components. This paper addresses the actuation fatigue characteristics of a specific SMA, equiatomic Nickel-Titanium (NiTi), with varying heat treatments, as well as different methods for assessing actuation fatigue response, including improved testing procedures and distributed extension measurement methods. Heat treatments ranged from 350°C to 400°C for one to three hours. Dogbone specimens processed from heat treated NiTi sheets were mechanically loaded on test frames which provided resistive heating and forced convective cooling with dry air via vortex tubes. Two mechanical loading schemes were utilized: constant uniaxial load (initial stress of 200MPa) and a linear or spring load centered at 200MPa (and ranging from approximately 150MPa to 250MPa). Linear loading schemes were introduced in order to better simulate actuation in an aerospace application, such as the morphing of semi-rigid surfaces. Specimens were thermally cycled to full actuation with a time-based control scheme developed in LabVIEW. Fatigue responses varied widely as a result of different heat treatments and loading schemes. Due to the main failure mechanism being high localized extension (necking) for the constant loading schemes, additional hardware and software were developed to visually capture extension distribution over specimen length. By analyzing actuation characteristics (e.g. transformation strain) and fatigue mechanisms, the ideal postprocessing for actuator applications was determined. Utilizing the local extension distribution evolution over the fatigue life of NiTi specimens as well as postmortem analysis of the failure surfaces allowed for the failure modes to be determined for each heat treatment.
机译:形状记忆合金(SMA)在航空航天,汽车和能源行业中具有许多有希望的应用。然而,由于缺乏对其致动疲劳的理解,因此有时将应用限制在非结构性或非关键性的组件上。本文介绍了特定SMA,等原子镍钛合金(NiTi)的致动疲劳特性,其变化的热处理方式以及评估致动疲劳响应的不同方法,包括改进的测试程序和分布式延伸测量方法。热处理的温度范围从350°C到400°C,持续一到三个小时。将经过热处理的NiTi板加工而成的狗骨标本机械加载到测试架上,该测试架通过涡流管提供电阻加热和干燥空气的强制对流冷却。使用了两种机械载荷方案:恒定的单轴载荷(初始应力为200MPa)和以200MPa(范围从150MPa至250MPa)为中心的线性或弹簧载荷。引入线性加载方案是为了更好地模拟航空航天应用中的致动,例如半刚性表面的变形。利用在LabVIEW中开发的基于时间的控制方案,将样品热循环至完全驱动。由于不同的热处理和加载方案,疲劳响应差异很大。由于恒定加载方案的主要失效机制是高度局部扩展(颈缩),因此开发了其他硬件和软件以可视方式捕获整个样本长度上的扩展分布。通过分析致动特性(例如变换应变)和疲劳机理,确定了致动器应用的理想后处理。利用NiTi试样在疲劳寿命上的局部延伸分布演变以及对失效表面的事后分析,可以确定每种热处理的失效模式。

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