The invention provides a structure/damping integrated design method suitable for a novel spacecraft. The method comprises the following steps: (1) establishing a simulation model; (2) determining a response peak value when the spacecraft structure needs to reduce vibration; (3) determining principal oscillation corresponding to the response peak value when the spacecraft structure needs to reduce vibration; (4) determining optimal laying position of a spacecraft damping; (5) determining a damping material, damping thickness, and structural parameters of a restraint layer, to complete integrated design of structure/damping. The spacecraft structure/damping integrated design method is simple and feasible, and prevents development cost for repeated design and repeated tests, and can effectively develop damping buffer effect of an aircraft.