A parametric design method for flexure supporting of the optical space remote sensor is presented to raise the design efficiency. The demands of flexure supporting deformation in the cases of temperature changes and assembly error are analyzed separately. The compromise programming method is used to establish optimal function of flexure supporting. Taking the flexure supporting used in the primary mirror of optical space remote sensor as example, the parametric design is provided in detail. After parametric design, the fundamental frequency of the flexure supporting is 88.8 Hz, the root mean square (RMS) of the mirror surface is 5.3 nm, when the temperature rise 4 ℃. The RMS is 12.9 nm when the assembly error is 0.1 mm, the RMS is 5.0 nm when 1 g gravity worked. The performance of flexure supporting significantly develops and all the design meets the targets. Computer automation design is applied during the design process, which greatly reduces the investment of human beings and the cycle of design at the same time.