基于SINS/GBAS组 ? 导航的高精度进近 ? 陆导航技术

Reusable launch vehicles have high accuracy requirements for position deviation during the approach-and-landing phase. However, the existed combined navigation methods have a large fluctuation of the navigation error, which cannot meet the navigation requirements of the launch vehicle in the landing approach section. In this paper, we establish a combined navigation method based on the precise position information output form the ground based augmentation system (GBAS) and the nonlinear error propagation model of the combined navigation strap-down inertial navigation system (SINS). We provide a composite correction structure of "output+feedback" for the launch vehicle navigation based on SINS/GBAS combined navigation. By introducing ionospheric and tropospheric errors into GBAS, the precise positioning of the vehicle positioning errors at the centimeter scale is achieved and the inertial guidance error drift problem is effectively suppressed by the extended Kalman filter algorithm. The simulation results show that the horizontal and elevation positioning error of the combined SINS/GBAS navigation is no more than 0.05 m; the velocity error is no more than 0.05 m/s. We verify the feasibility of the combined SINS/GBAS approach for the vehicle approach-and-landing navigation system.