Model constructing method based on dynamic characteristic test of spacecraft

Abstract

The invention relates to a model constructing method based on a dynamic characteristic test of a spacecraft. The model constructing method comprises the following steps: dismantling a target spacecraft into a plurality of section substructures according to all section connecting surfaces of the target spacecraft, acquiring modal parameters of the plurality of section substructures in a fixed state, and constructing dynamic models of all the upper-stage section substructures according to the modal parameters; preliminarily correcting the dynamic models of all the section substructures; determining a combination preliminary model of the spacecraft according to the dynamic models of all the section substructures; determining a tooling matched with an upper-stage combination of the target spacecraft in size and interface; carrying out the dynamic characteristic test of an integral structure fixed boundary of the target spacecraft based on the target spacecraft so as to acquire structural modal parameters; correcting the combination preliminary model according to the structural modal parameters so as to obtain a final spacecraft dynamic model. According to the model constructing method disclosed by the invention, the construction accuracy of the dynamic model of the spacecraft can be improved, and the complexity of a ground test of a large-scale structure can be effectively reduced.

Description

technical field [0001] The invention relates to the technical field of spacecraft dynamics, in particular to a method for constructing a dynamic model of a spacecraft. Background technique [0002] With the development of aerospace technology and the demand for exploration of extraterrestrial planets, human beings need to design spacecraft with greater carrying capacity to realize the dream of exploring the vast universe. Increasing the transport capacity will inevitably increase the size of the spacecraft structure. Taking my country’s new generation of large launch vehicles as an example, its diameter has reached 5m; and the development and design of heavy-duty launch vehicles in the future may be even larger. The increase in the size of the structure will bring some new problems and difficulties to the design and implementation of the ground test. [0003] During the structural design of some on-orbit spacecraft as the top load of the launch vehicle, the combined state o...

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Problems solved by technology

[0004] However, due to a series of problems such as the unknown stiffness of the connecting section of the spacecraft, structural nonlinearity,

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