Trajectory Reconstruction Method for Launch Vehicles Under Non-Fatal Thrust Failure

For non-fatal thrust failure, a trajectory reconstruction method based on iterative guidance is proposed. In order to evaluate the capability assessment, iterative guidance and dynamic integration is used to accurately calculate the propellant consumption in this method. The relationship between the semi-major axis of the target orbit and the propellant consumption is analyzed, based on which a trajectory planning method is proposed to search a rescue orbit. The rescue orbit makes full use of the remaining energy and is the highest circular orbit that can be entered. Simulation results demonstrate that the launch vehicle could only enter an lower elliptical orbit with large eccentricity. After orbit reconstruction, the launch vehicle enters the rescue orbit, a higher circular orbit. Trajectory reconstruction significantly increases the orbital altitude and improves the reliability of launch vehicles.