The working principles of traditional inertial/celestial integrated navigation are generally divided into two types. The ψ angle output from astrometry analyzes and corrects the velocity and position of inertial navigation directly. Or the ψ angle is used to measure and estimate the velocity and position of inertial navigation indirectly. Aiming at the problem of unsatisfactory integrated navigation effect due to insufficient use of the gyro constant zero bias estimation information with large observability in the two principles， an all-solid-state strapdown inertial/celestial integrated navigation technology is proposed in the paper. The technology fixes the strapdown inertial navigation system with the large field of view star sensor， and uses the Euler error angle as the measurement information of the Kalman filter to estimate and feed back the gyro constant zero offset in real time to correct the strapdown inertial navigation system. It can quickly and effectively suppress various errors caused by gyro drift. The simulation results of measured data show that it can make longitude error， latitude error， heading error and gyro constant bias error stable and convergent quickly using Euler error angle as the measurement information of Kalman filter. In the long endurance test， the longitude error can be no more than 0.5 nautical miles， latitude error can be no more than 0.2 nautical miles， heading angle error can be no more than 30 arcsec. And in the short endurance test， the longitude error can be no more than 0.5 nautical miles 25 nautical miles， latitude error not more than 0.15 nautical miles， heading angle error not more than 20 arcsec. Therefore， the technology has good adaptability for both long-term navigation and short-term navigation， and has practical value and research significance.