Abstract: To address the issue in traditional SINS/DVS integrated navigation methods that is required a spacecraft to simultaneously carry three sensors to observe three navigation stars for comprehensive velocity error correction, an inertial/time-segmented astronomical Doppler velocity integrated navigation method based on sensor maneuvering (SINS/TS-DVS) was proposed. By periodically changing the optical axis pointing through sensor maneuvering, DVS measurements in different directions were acquired. This method ensured navigation accuracy while reducing the burden on the spacecraft. Simulation results demonstrate that the position errors of the SINS/TS-DVS integrated navigation in longitude, latitude, and altitude directions were significantly improved compared to the traditional Strapdown Inertial Navigation System (SINS) and the SINS/DVS method observing only one star. It can effectively enhance spacecraft positioning accuracy.