A nonlinear analysis method for dynamic loads of flexible solar cell wings

Abstract

The invention belongs to the technical field of structural dynamics and finite element simulation and particularly relates to a dynamic load nonlinear analysis method for a flexible solar cell wing. The invention discloses the following technologies: 1, a finite element modeling method of tensioning mechanisms, a guide mechanism and hanging steel wire ropes of the flexible cell wing; 2, a method for applying a pre-tightening force of the tensioning mechanisms and the guide mechanism in the nonlinear transient response analysis process; 3, simulation of a mechanical property that the hanging steel wire ropes only can bear a pulling force and cannot be pressed in the NASTRAN solving process; 4, a method for improving nonlinear iteration convergence by compensating difference in lengths of the hanging steel wire ropes, which is caused by deformation of storage boxes; and 5, a nonlinear transient response analysis technology under the combined action of a static pre-tightening force and a dynamic inertial force. The dynamic load nonlinear analysis method for the flexible solar cell wing has the beneficial effects of simple method and ingenious design.

Description

technical field [0001] The invention provides a method of using MSC.NASTRAN to perform nonlinear transient response finite element analysis on the dynamic load of the spacecraft flexible solar cell wing in orbital maneuvering process, including dynamic modeling of structure or mechanism, nonlinear static and Transient response analysis and other content, involving technical fields such as computational structural dynamics and finite element simulation. Background technique [0002] The structure of the flexible solar cell wing of the spacecraft is as follows figure 1 As shown, it includes: a storage box 1 at the far end, a suspension steel wire rope 2, a battery array 3, a main stretching mechanism 4, a guiding mechanism 5, a tensioning mechanism 6, a storage box 7 at the proximal end, a coil spring 8, and a steel wire rope 9. The mechanical modeling and analysis (including statics and dynamics) of conventional structures can be completed with MSC.NASTRAN. But for spacecra...

AI Technical Summary

Problems solved by technology

Without specialized modeling techniques, the calculation model of the battery array will warp after loading, causing the nonlinear iteration to diverge

②MSC.NASTRAN's nonlinear static analysis (SOL106) and nonlinear transient analysis (SOL129) do not support temperature loads, and the method of using temperature loads to simulate preload in finite element calculations is not applicable at this time

③MSC.NASTRAN does not provide "rope units" that are only tensioned but not compressed, so the mechanical properties of the wire ropes that hang the battery array cannot be directly simulated

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