A mechanism for a deployable optical structure of a small satellite

In this paper, we present a deployment mechanism that is applicable to a deployable optical structure where the focus is on satellite miniaturization. It is designed with a passive deployment mechanism that utilizes a spring hinge. In order to confirm the feasibility of the designed deployable mechanism, we theoretically analyze the alignment errors (de-space, tilt, and de-center) that influence the optical performance of the structure. The theoretical results are as follows: a de-space of 180.0 µm, a tilt of 1941.3 µrad, and a decenter of 45.3 µm. In addition, we measure alignment errors to evaluate the actual alignment errors for a manufactured deployable mechanism. The experimental results are as follows: a de-space of 180.2 µm, a tilt of 218.8 µrad, and a de-center of 617.5 µm. Finally, we investigate the factors causing the differences between the theoretical and experimental values, and we suggest a method for improving the alignment errors.