Folding method of plane storage ratio folding and inflation unfolding structure for spacecraft

Abstract

The invention provides a plane storage ratio folding and inflation unfolding structure for a spacecraft. The plane storage ratio folding and inflation unfolding structure comprises a plurality of folding units; each folding unit comprises a main folding line (2), an auxiliary folding line (3) and a plurality of triangular folding lines (4); the multiple triangular folding lines (4) are located onthe side parts of the main folding lines (2) correspondingly; and the auxiliary folding lines (3) are located on one sides of the triangular folding lines (4). Based on the simplicity and practicability of a product, the high-rigidity large plane high-storage-ratio folding and inflation unfolding structure for the spacecraft is provided. According to the plane storage ratio folding and inflation unfolding structure for the spacecraft, through application of a simple folding line folding method or structure and thermocuring inflation supporting pipes, high-storage-ratio folding close-up of large planes, such as a solar sail, an antenna and a reflector, in the spacecraft can be realized, the unfolded planes have high rigidity and the high shape-preserving ability, and the high rigidity of the thermocuring inflation supporting pipes do not need to be maintained through the pressure difference in the pipe (that is, after the planes are unfolded in place, gas can be exhausted at any time, and the rigidity is not affected by gas leakage).

Description

technical field [0001] The invention belongs to the field of spacecraft structures, and in particular relates to a folding method or structure of a plane storage ratio folding and inflatable unfolding structure for a spacecraft, in particular to a high rigidity large plane high storage ratio folding and inflation deployment method or structure for a spacecraft. Background technique [0002] With the development of spacecraft technology, large-scale planes such as: solar sails, antennas, reflectors, etc. are widely used on spacecraft, and the requirements for size and stiffness after deployment are increasing. However, the storage ratio of conventional folding methods is small, and the deployment mechanism The weight is large and the reliability of joints is reduced, so it is not suitable for application on future spacecraft. Contents of the invention [0003] Aiming at the defects in the prior art, the object of the present invention is to provide a folding method for a sp...

AI Technical Summary

Problems solved by technology

[0002] With the development of spacecraft technology, large-scale planes such as: solar sails, antennas, reflectors, etc. are widely used on spacecraft, and the requirements for size and stiffness after deployment are increasing. However, the storage ratio of conventional folding methods is small, and the deployment mechanism Heavy weight, many joints and reduced reliability, so it is not suitable for application on future spacecraft

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