Thermally configurable structural elements (e.g., aircraft components such as an aircraft winglet spar) capable of assuming at least first and second structural configurations are provided whereby the structural element includes an integral actuation mechanism may be formed of sintered shape memory alloy (SMA) particles and sintered non-SMA particles formed by an additive layer manufacturing (ALM) process, such as 3D printing. The ALM process thereby provides 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 assuming 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 assume the at least first and second structural configurations, respectively.
Thermally configurable structural elements especially useful for aircraft components
27.02.2024
Patent
Elektronische Ressource
Englisch
IPC: | B22F Verarbeiten von Metallpulver , WORKING METALLIC POWDER / B33Y ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING , Additive (generative) Fertigung, d. h. die Herstellung von dreidimensionalen [3D] Bauteilen durch additive Abscheidung, additive Agglomeration oder additive Schichtung, z. B. durch 3D- Drucken, Stereolithografie oder selektives Lasersintern / B64C AEROPLANES , Flugzeuge / C21D Veränderung der physikalischen Struktur von Eisenmetallen , MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS / F03G Feder-, Gewichts-, Trägheits- oder ähnliche Kraftmaschinen , SPRING, WEIGHT, INERTIA, OR LIKE MOTORS |
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