A multi-rigid body dynamics modeling method for a variable-configuration spacecraft

Abstract

The invention discloses a multi-rigid-body dynamics modeling method for a variable configuration spacecraft. According to the topological configuration analysis of the variable configuration spacecraft, the topological structure model of the variable configuration spacecraft is established, and a coordinate system is established for the variable configuration. Carry out kinematics analysis of the spacecraft, according to the kinematic parameters of a single variable-configuration spacecraft cabin, establish the kinematic recursive relationship of adjacent cabins, and describe the motion of the variable-configuration spacecraft. Based on the recursive relationship of adjacent compartments obtained in , establish the dynamic equation of the variable configuration spacecraft system, integrate the system dynamic equation of the variable configuration spacecraft, and take the external force of the variable configuration spacecraft as a known constraint condition, find The dynamic parameters of the variable configuration spacecraft must be described, and the multi-rigid body dynamic model of the variable configuration spacecraft should be established. The invention can reduce manual topological analysis and is convenient for computer programming to realize topological configuration analysis.

Description

technical field [0001] The invention belongs to the field of spacecraft dynamics, and relates to a topological configuration description and dynamic modeling method of a variable-configuration spacecraft. Background technique [0002] With the complexity, diversification, and suddenness of space missions, the requirements for low-cost, multi-task, and high-maneuverability are put forward for spacecraft, and the configuration-changing spacecraft has become the mainstream development direction of future spacecraft. [0003] A variable configuration spacecraft refers to a multi-chamber spacecraft that uses a large-scale cabin module stack design and can be deployed in space and self-reconfigured. It is a high-dimensional multi-degree-of-freedom dynamic system. Due to the thermal environment, the simultaneous rotation of cabin modules, and the addition of control forces, multiple field strength couplings are formed, which aggravates the difficulty of attitude control for spacecr...

AI Technical Summary

Problems solved by technology

This will seriously limit the spacecraft's autonomy, rapidity, real-time control and other on-orbit operational performance

[0005] In general, in the existing variable configuration spacecraft flexible multibody dynamics modeling methods, there is no clear method and solution for reducing manual topology analysis work.

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