Abstract
Additive manufacturing technology in metals allows for the design and fabrication of integrated satellite structures that reduce part counts and improve performance. This paper, proposes the application of the design for additive manufacturing (DfAM) process in the space environment. The small lightweight deployment mechanism structure was investigated for the strength and stiffness performance. The weight reduction was maximized through shape optimization by applying a topology optimization technique. In addition, a validation of the deployment mechanism structure design was confirmed under strength and vibration conditions through structural analysis. The mechanical properties of Ti64 Grade23 were compared and evaluated by the test of specimens and products manufactured using the power bed fusion (PBF) method.
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