A kinematic mount based on the statically determinate principle is designed using a single-axis right circular flexure hinge. The main role of this support structure is to reduce the influence the satellite platform on the space camera, thereby ensuring the thermal stability of the space camera in orbit. The mathematical model of the compliance of the single-axis right circular flexure hinge is derived based on the Castigliano’s second theorem. According to the index requirements and the compliance equations, the initial structure of kinematic mount is obtained. The optimization design is conducted with the initial structure as the optimization object and the natural frequency as the optimization objective to obtain the optimal structure. The finite element analysis shows that the optimal structure meets the index requirements. Compared with the initial structure, the natural frequency of the optimal structure is increased by 4.2%, the optimal structure in Rx, Ty, and Tz are better than the initial structure 13.3%, 21%, and 12.8%. Experiment verifications of compliance equation C33 of single-axis right circular flexure hinge and the compliance of the bipod are carried out. The experiment results indicate that the compliance equation C33 is correct, and the compliance of the bipod meets the design value. Therefore, it is concluded that all the compliance equations are correct, and the kinematic mount can meet the requirements of the thermal stability of the space camera in orbit.