Simulated analysis platform for thermal disturbance responses of spacecraft

Abstract

The invention belongs to the technical field of design, and dynamics simulation and control of high-precision spacecraft, and in particular relates to a simulated analysis platform for thermal disturbance responses of the spacecraft. The platform comprises a data input modeling module, a flexible attachment on-orbit thermal analysis module, an equivalent thermal load derivation module, a modal analysis module, a coupling dynamics modeling module, a coupling dynamics model solution module and a post-processing module in sequence; the simulated analysis platform builds a coupling dynamics model of large flexible satellite-borne attachments and stars, and provides a special simulated analysis platform for coupling responses of the large flexible satellite-borne attachments and the stars. The simulated analysis platform can be used for solving posture variations of the spacecraft with complex flexible attachments caused by thermally induced dynamic deformations of the flexible attachments, can provide a simple and effective model, method and tool for forecast and assessment of thermally induced vibration responses of the spacecraft with the flexible attachments under actual conditions, and can serve as a reference for a satellite design process.

Description

technical field [0001] The invention belongs to the technical field of high-precision spacecraft design and dynamics simulation and control, in particular to a thermal disturbance response simulation analysis platform for spacecraft. Background technique [0002] When the spacecraft enters and exits the shadow area of ​​the earth, the space thermal environment changes, and the drastic temperature change will not only cause large thermal deformation of the flexible attachment, induce thermal vibration, but also transmit the disturbing force to the main body of the spacecraft. Due to the conservation of angular momentum, the vibration of the flexible attachment will cause the attitude of the main body of the spacecraft to shake, which will affect the pointing accuracy and attitude stability of the spacecraft payload, resulting in the failure of the spacecraft to work normally or function failure. [0003] NASA has observed the impact of thermally induced vibration on the orbit...

AI Technical Summary

Problems solved by technology

The disadvantage is that the flexible attachment is treated as a simple beam, and the complex structural form of the actual attachment is not discussed

[0005] For spacecraft with high requirements for pointing accuracy and attitude stability, if only a simplified model is used to approximate the complex flexible attachment structure, it is obviously not suitable for the simulation analysis of the coupling mechanical characteristics of the spacecraft attitude change induced by the thermal dynamic deformation of the flexible attachment. It is impossible to accurately predict and evaluate the influence of thermally induced vibration of spaceborne flexible components on spacecraft attitude

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