Parameter design for the space focus control mechanism using 1DCAE

In space development, design is proceeded by processes of conceptual design, trial model design, preliminary design, critical design and sustainment design. Detailed analysis using 3D models is performed in the preliminary design and critical design phases, but if a problem occurs in these phases, we have a large setback. Therefore, it is important to understand the overall design at an earlier phase. Recently, a concept of 1DCAE, which performs overall optimization by simply expressing the entire system or the entire product, has been proposed. The performance of optical telescope loaded on the satellite is affected by alignment between each mirror, but gravity release in the orbital environment, moisture exhaust and thermal distortion change the distance of the CFPR structure supporting each mirror and cause a deviation of focal position. For this reason, the focus is adjusted by focus control mechanism on orbit, but the driving accuracy required for this focus control mechanism is very high, or the order of submicron. In this paper, it is reported that the design method of 1DCAE is applied for the focus control mechanism, the result of driving accuracy is demonstrated, and the result in the modified design is very good.