Abstract:

The re-entry process of the lunar return vehicle is the key to the whole lunar exploration mission. To provide design reference and a validation method for the re-entry mission, a suit of digital simulation system for re-entry flight is developed. Firstly, the six degree of freedom dynamic model is constructed, and the system of the guidance, navigation and control (GNC) is proposed. The modeling of thrusters is also considered. Secondly, the framework of the simulation system including all working modules is developed. Finally, the working procedure of re-entry flight simulation which satisfies functional requirements is designed. Based on the Monte Carlo method, the simulation system can analyse the features of re-entry trajectories, and assess the GNC system and the design of the aerodynamic configuration. The validity and the function of the simulation system is validated through the Monte Carlore entry trajectory simulation of some lunarreturn vehicle.