Design of Integrated Navigation Algorithm of First Sub-Stage of Launch Vehicle

In (order to improve the navigation accuracy of launch vehicle in high dynamic, large airspace and high-speed flight conditions, a low-cost integrated navigation system based on GNSS/SINS in launch inertial coordinate system is proposed. In these flight conditions, influence of time synchronization on navigation accuracy is not negligible and it's difficult to obtain high-precision time synchronization information. Therefore, a novel algorithm to improve the time synchronization accuracy by using interpolation method is designed. Digital simulation and vehicle experiment illustrate that the position error is less than 5m, and velocity error is less than 0.2m/s. Thus, this GNSS/SINS integrated navigation algorithm can effectively improve navigation accuracy of launch vehicle.