The invention relates to a thermally configurable structural element especially useful for aircraft component. Concretely, a thermally configurable structural element (e.g., aircraft components such as an aircraft winglet spar) capable of adopting at least first and second structural configurations are provided. The structural element includes an integral actuation mechanism provided by at least one thermally configurable region, and at least one non-thermally configurable region which is unitarily contiguous with the at least one thermally configurable region. The at least one thermally configurable region is capable of adopting at least first and second positional orientations in response to the presence or absence of a thermal input to thereby cause the structural element to adopt the at least first and second structural configurations, respectively. The thermally and non-thermally configurable regions may be formed of sintered shape memory alloy (SMA) particles and sintered non-SMAparticles formed by an additive layer manufacturing (ALM) process, such as 3D printing.
本发明涉及特别适用于飞机构件的可热构造结构元件。具体地,提供了能够采取至少第一结构构造和第二结构构造的可热构造结构元件(例如,诸如飞机小翼梁的飞机构件),由此该结构元件包括一体致动机构,该一体致动机构由至少一个可热构造区域和与所述至少一个可热构造区域一体地毗邻的至少一个非可热构造区域提供。所述至少一个可热构造区域能够响应于是否存在热输入而采取至少第一位置定向和第二位置定向,从而使结构元件分别采取所述至少第一结构构造和第二结构构造。可热构造区域和非可热构造区域可以由通过诸如3D打印的加层制造(ALM)工艺形成的烧结形状记忆合金(SMA)颗粒和烧结非SMA颗粒形成。
THERMALLY CONFIGURABLE STRUCTURAL ELEMENTS ESPECIALLY USEFUL FOR AIRCRAFT COMPONENTS
特别适用于飞机构件的可热构造结构元件
2020-06-02
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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