The optical system characteristics and working index requirements of a certain type of space tracking remote sensing camera are considered. To save space and ensure the image quality of the camera, a two-dimensional scanning mirror suitable for small satellite platform is designed, and the light weight of the scanning mirror for the 300 mm space camera is realized. The thickness of mirror body, the cutting angle, the thickness of edge, the thickness of mirror surface and the thickness of lightweight reinforcement are taken as the design variables. The target value of peak PV is smaller than 63 nm and that of RMS is smaller than 12 nm. These two values are taken as the optimal boundary condition. A multi-objective optimization method is proposed to minimize the mass, surface peak PV and mean root RMS under certain equilibrium for the parameter design of single point support aperture. The weight of the optimized mirror is only 0. 84 kg, and the lightweight ratio reaches 76% . The single point flexible support structure uses three loop beams spaced 120° apart as the flexible hinge, and utilizes the integrated design with the mirror seat. The simple structure reduces the moment of inertia of the scanning mirror component and improves the response speed of the tracking camera. The space environment of the optimized scanning mirror component is checked. The RMS value of the surface shape of the scanning mirror is less than 6nm in XY microgravity; the RMS value of the surface shape of the scanning mirror is less than 12 nm in Z gravity, -50℃ load and 3. 5 rad / s rotational inertia load; the fundamental frequency of the component is 326 Hz. Finally, the experiment evaluation of the surface shape accuracy and the positioning accuracy of the scanning mirror proves the feasibility of the scheme.