Simulation Analysis of Complex Spacecraft Separation Dynamics Considering Characteristics of Flexible Multi-Body.

In order to study the influence of the characteristics of the flexible multi-body spacecraft on its separating attitude, this paper considers the flexibility of the solar wing and the separation module and uses the separation dynamics and the rigid-flexible coupled dynamics analysis method to establish the spacecraft flexible multi-body dynamics model. Through the spacecraft flexible multi-body separation dynamics analysis, the influence of the flexible characteristics of the solar wing and the separation module on the spacecraft separation attitude can be solved. By using the method of optimization analysis to optimize and analyze the multi-parameter influence on the spacecraft separation, the limits of the spacecraft separation attitude can be obtained. The analysis results provide the theoretical reference for optimal design and separation safety of the spring separation mechanism, while laying a foundation for carrying out the national key programs such as space station, manned spaceflight, lunar exploration. [ABSTRACT FROM AUTHOR]