Double-omega-shaped carbon fiber composite material expansion arm and stretching method thereof

Abstract

The invention relates to a double-omega-shaped carbon fiber composite material expansion arm and a stretching method thereof, in particular to the expansion arm and the stretching method thereof. The invention aims to solve the problems of the traditional inflatable stretching member as follows: the flexural rigidity is low, and the structure rigidity can be maintained in need of continuously inflating gas or solidifying the structure, the member is not easy to unfold and the traditional stretching method has a low control precision, the retroaction impact force on a main satellite is great in the stretching process and the like. A carbon fiber composite material cylinder is composed of two omega-shaped thin-wall shells by buckling and splicing, two ear edges are respectively formed at the connection part of the expansion arm cylinder, and the two ear edges are oppositely arranged and are located on the outer side wall of the expansion arm cylinder. Through holes are uniformly distributed at two sides of the expansion arm cylinder along the length direction; the expansion arm cylinder is wounded on a roller, the ear edges at two sides of the expansion arm cylinder are respectively engaged with a chain wheel at the corresponding position, and two chain wheels are controlled to rotate, and therefore, the controllable stretching of the expansion arm cylinder is realized.

Description

technical field [0001] The invention relates to a stretching arm and a deploying method thereof. Background technique [0002] Due to the limitation of the effective launch load and launch volume of the launch vehicle, the requirement for the carried payload is to have a smaller weight and a smaller launch volume. Large-scale space structures are in a folded state when launched, and after being launched into orbit, they are unfolded to form the state required by their design and realize their design functions. The expandable support structures of large spacecraft mainly include hinged, sleeve, and inflatable structures according to their different deployment mechanisms. The hinged expandable support structure has low deployment reliability due to many components and many control links. The expandable tube of the sleeve tube is limited by the length and number of the sleeve tube, and its expanded length is relatively short, which is not suitable for preparing super-large sp...

AI Technical Summary

Problems solved by technology

[0003] The present invention solves the problem that the existing inflatable unfolding member is deployed in an inflatable manner. When the pressure in the tube decreases, the cross-sectional shape will change, so that the bending stiffness will decrease. It is necessary to continuously inflate the gas or solidify the structure to maintain its structure. Rigidity, the problem of difficult deployment operation; and the existing inflatable deployment method needs to rely on system reliability and structural airtightness, there are problems such as low control accuracy, large reaction impact force on the main satellite during the deployment process, and then provides a dual- Omega-shaped carbon fiber composite extension arm and deployment method thereof

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