Abstract: A guidance control scheme based on strapdown laser detector and proportional navigation guidance (PNG) for rocket projectile was presented in details since the precise guidance improvement requirement. Because the strapdown detector can only measure the error angle between airframe axis and target directly and could not provide the inertial line-of-sight (LOS) angular rate necessarily to PNG, a LOS rate algorithm using detector's error angle and airframe attitude rate from onboard gyro was proposed. A two-loop acceleration autopilot was designed with respect to the autopilot-guidance match principle. The non-dimensional miss distance analysis and trajectory simulation results validate that the proposed approach is feasible.