Adaptive optics (AO) are essential in ground-based telescopes to correct atmospheric distortions and achieve high-resolution imaging; adaptive secondary mirrors (ASMs) integrate deformable mirrors directly into telescope optics but typically require a wavefront sensor (WFS) for calibration and flattening. When a WFS is unavailable or nonfunctional, alternative methods are needed. This thesis explores the feasibility of flattening the convex ASM of the UH-88 telescope without a WFS, using only a natural guide star and focal plane imaging. By developing a numerical model of the UH-88 system—including the deformable mirror, Mauna Kea atmospheric aberrations, and focal plane camera characteristics—we employed an image metric based on the second moment of intensity to evaluate image quality, adjusting Zernike mode coefficients via the Nelder-Mead simplex optimization algorithm to control mirror shape. Experimental validation using a laboratory setup that replicated key aspects of the UH-88 system confirmed that the ASM could be flattened to within 100 nm RMS surface error, meeting passive mirror operation requirements. The flattening was achieved within a 10-minute timeframe using only focal plane images of a natural guide star distorted by atmospheric turbulence. This study demonstrates that flattening a convex ASM without a WFS is feasible using focal plane image metric optimization, offering a practical solution when the WFS is unavailable or calibrated commands are outdated, thereby ensuring continued high-quality telescope operation.

There is an ever-increasing demand for high data transfer rates. Laser satellite communication is a promising technology which offers high data rates and more secure links than the mature radio frequency (RF) communication. To make a laser communication terminal market viable it must be low size, weight and power (SWaP). The telescope drives the volume of the terminal. Making the telescope more compact with high magnification imposes stricter tolerances. A solution to alleviate these tolerances is to use a refocusing mechanism (RFM) to align the telescope in space after launch. In this project, a refocusing system is designed. This comprises of making system level choices like where to place the mechanism, how to close the loop and how to use the onboard detectors. All these choices lead to the requirements for the RFM. Further, a mechanism is designed that fulfills the requirements. In addition, mechanical and thermal FEM simulations are carried out to show that the RFM survives launch and can work in the challenging thermal environment.