RU1713221C - Large-sized flat film structure of spacecraft and method of its laying and unrolling in orbit - Google Patents

Abstract

FIELD: space technology. SUBSTANCE: large-sized flat film structure has a number of individual sections 1 manufactured in the form of sectors of circle with truncated vertexes coupled to coils 45 and intercoupled by external edges 7. In process of laying of structure each section of film is folded in pleats by bending of film by lines parallel to bisectrix of sector. After this sectors laid in strip are applied on to coils attached to body of spacecraft. Edges of two adjacent sectors are interconnected. Unrolling of flat film structure into working position is carried out at the cost of simultaneous gyration of spacecraft and unrolling of flat film reflector by rotation of coils. EFFECT: simplified process of laying of flat film structure when manufacturing large-sized unrolled reflector of round shape, reduced area required for its laying and increased reliability of unrolling of structure. 2 cl, 6 dwg

Description

 The invention relates to space technology, namely to deployable film structures.

 The closest known device is the folding surface of the solar cells of the spacecraft, containing a number of separate sections, each of which is connected at one end to a corresponding coil for storing it. The closest method is the method of laying and deploying in orbit a large-sized flat film design of the spacecraft, including dividing the film surface into a series of sections, winding the sections into a coil and rotating the coils simultaneously with the spinning of the spacecraft in orbit.

 The disadvantage of this device and the method of its installation and deployment are installation in the manufacture of large-sized flat film construction and the need for large production areas for the implementation of its installation.

 The purpose of the invention is to reduce the required floor space and simplify the laying of a flat film structure in the manufacture of a large deployable round reflector, increasing the reliability of deployment of the structure.

 This is achieved by the fact that in the large-sized flat film design of the spacecraft containing a number of separate sections, each of which is connected at one end to a corresponding coil for storing it, the film sections in it are made in the form of sectors with truncated vertices associated with the coils and with the outer edges interconnected. In this case, each section of the film is folded accordion into a tape with a width equal to the height of the coil, bending the film along lines parallel to the sector bisector, after which the tape is wound on a coil and the outer edges of neighboring sectors are connected to each other.

 In FIG. 1 shows a large-sized flat film structure in a deployed (working) position; in FIG. 2 is a diagram of laying sectors; in FIG. 3 - sector, laid in tape, side view; in FIG. 4 - the same front view; in FIG. 5 - sector wound on a reel; in FIG. 6 illustrates the deployment of a flat film structure to a working position.

 A large-sized flat film design consists of n separate identical sections in the form of sectors of a circle 1 with truncated vertices 2. Sectors 1 are assembled (by gluing or welding) from a roll of film material. Sectors 1 are connected by cords 3, fixed at the ends 4 of the truncated peaks of the sector, with coils 5 mounted rotatably on the spacecraft body 6. The outer edges 7 of the films of each two adjacent sectors 1 are connected by gluing or welding. Each sector 1 is laid in ribbons 8 with accordion folds, bending the film alternately along lines 9 parallel to the sector bisector. The width h of the folds is equal to the height of the coil. The tape is wound on coils 5 and the outer edges 7 of adjacent sectors 1 are connected to each other.

 The deployment of large-sized flat film construction in the working position is carried out by centrifugal forces through the rotation of the coils 5 simultaneously with the unwinding of the spacecraft body 6.

 The invention allows to simplify the laying of the structure, significantly reduce the required floor space during its manufacture and installation, as well as to increase the reliability of the deployment of the structure into position.

Claims (3)

 LARGE-SIZED FLAT FILM DESIGN OF THE SPACE VEHICLE AND METHOD FOR ITS LAYING AND DEPLOYMENT IN ORBIT.  1. A large-sized flat film design of the spacecraft, containing a number of separate sections, each of which is connected at one end to a corresponding coil for storing it, characterized in that, in order to reduce the required production area and simplify the laying of the film structure in the manufacture of a circular reflector, and also to increase the reliability of deployment of the structure, in it the film sections are made in the form of sectors with truncated vertices associated with coils, and the outer edges connected between do it yourself.  2. A method of laying and deploying in orbit a large-sized flat film design of a spacecraft, including dividing the film surface into a series of sections, winding the sections into coils and rotating the coils simultaneously with the unwinding of the spacecraft in orbit, characterized in that, in order to reduce the required production area and simplifying the laying of the film structure in the manufacture of a circular reflector, as well as to increase the reliability of the deployment of the structure, each section of the film is folded harmon Coy a tape with a width equal to the height of the coil, wherein the film is folded along lines parallel to the bisector of the sector, after which the tape is wound on the spool and connected to outer edges of the adjacent sectors with each other.

Images