In order to verify the dynamics characteristic of a space remote sensing camera

spacecraft and camera dynamics coupling test is needed. To improve the reliability of the camera

a coupling test should be carried out with a test model instead of the camera. So a test model of camera must be studied at first. Dynamics analysis of the space remote sensing camera was carried out at first

and then the demand for dynamics characteristics of the camera’s test model was put forward. The mass equivalence between test model and camera is realized with UnigraphicII software in this paper. Based on the sensitivity analysis of structural parameters of camera with respect to each mode of spacecraft and camera coupling system

stiffness equivalence was realized with classical theoretical analysis and natural frequency optimization. The dynamics coupling test between spacecraft and test model was similar to the test between spacecraft and camera. The method to develop a test model applied in this paper will be a reference to some other dynamics coupling test.