A Multibody Dynamics Modeling and Overload Optimization Design Method for Rocket Landing

Abstract

This invention relates to a multibody dynamics modeling and overload optimization design method for rocket landing, comprising the following steps: determining the configuration of the outriggers and the input of rocket body shape and quality parameters; establishing a parametric model; constructing the overall multibody dynamics model of the rocket landing simulation test platform; and performing overload optimization design. Based on the geometric relationship of the outrigger configuration, by changing the length of the main and auxiliary supports, the vertical velocity of the footpads touching the ground is controlled to be consistent. The minimum axial force of the main support or the minimum axial overload of the test platform is set as the optimization design objective. The discrete functional relationship between the changed parameters and the optimization objective is obtained. Finally, combined with the outrigger mass requirements and the tail end ground clearance constraints, the optimal outrigger configuration for the overall scheme is obtained. This provides a simulation basis for calculating the outrigger load and rocket body load during the landing process, meeting the needs of rapid iterative demonstration of the project.

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