RU186809U1 - Fold-down design for ultra-small spacecraft systems - Google Patents

Abstract

The utility model relates to the field of space technology, in particular, to the disclosing structural elements of antennas, solar panels (BS) and other devices operating on the periphery of an ultra-small spacecraft (SMKA).

A folding design is proposed on the basis of a multilayer flexible-rigid printed circuit board that combines the functions of a hinge and an electrical conductor between the rigid parts of the folding panels, while a torsion spring located at the bend and rigidly fixed to the ends of the circuit board is used as a drive; extreme position, the movable part of the folding panel is achieved by the configuration of the spring.

The technical result consists in increasing the rigidity of the structure in the open position without the use of additional nodes; improving reliability, by minimizing components, providing dynamic flexibility of electrical connections and using typical technological processes in the production of parts, as well as reducing overall dimensions.

Description

This utility model relates to the field of space technology, in particular, to the disclosing design elements of antennas, solar panels (BS) and other devices operating on the periphery of an ultra-small spacecraft (SMKA).

A significant difficulty in the design of remote components for the design of ultra-small satellites is often caused by the limited space between the transport and launch container designed to launch the SMKA and the body of the device. The placement of swivel joints, folding elements of the QMSA, in such cases, is difficult or not possible.

Known methods for disclosing structural elements of a satellite based on articulated joints, consisting of a dozen parts, for the manufacture of which many different technological operations are used. Such systems have several drawbacks: the electrical connection between the movable panels is made using separately soldered wires, the hinges have a relatively large mass and take up a significant amount of the SMCA.

As an example, we can consider the deployment device of transformable mechanical systems of a spacecraft (see patent RU 2636207).

The disadvantages of the mechanism include the following:

1. The overall dimensions of the mechanism are too large to be used on ultra-small satellites;

2. The impracticability of combining the functions of a swivel and an electrical conductor in one mechanism.

A device for deployment and coagulation of a flexible design of a spacecraft, which contains elastically transformable tapes ("roulettes"), bent U-shaped and fixed on a flexible film or web, (see patent RU 2641398).

The disadvantages of the device include the following:

1. Uncontrolled kinematics, which is due to the use of flexible tapes of U-shaped section as flexible connections;

2. Unreliability of the claimed device, due to the use of a large number of various parts technologically complex in production;

3. Mass and size characteristics, the device is not intended to be placed on the satellite’s body in excess of a small size, in particular, the CUBESAT class.

The task, to the solution of which this technical solution is directed, is to create a structure, using which the following technical result is achieved:

1. The increase in structural rigidity in the open position without the use of additional nodes;

2. Improving reliability, by minimizing components, providing dynamic flexibility of electrical connections and using typical technological processes in the manufacture of parts.

3. The decrease in weight and size characteristics.

The problem is solved through the use of a multilayer flexible-rigid printed circuit board, combining the functions of a swivel and an electrical conductor between the rigid parts of the folding elements. One or more layers of such a multilayer board is made of polyamide, which provides dynamic flexibility of the connections. As a drive, a torsion spring can be used located at the bend and rigidly fixed in the circuit board with its ends. Fixation in the extreme position, the movable part of the folding element, is achieved by the configuration of the spring. The number of parts of this design is minimized and the possibility of using standard technological operations for the production of printed circuit boards in the aggregate guarantees an increase in the reliability of the system and a decrease in overall dimensions.

A description of the utility model is illustrated in Figures 1-3.

Figure 1 shows a flexibly rigid printed circuit board folded by an "accordion" when folded.

Figures 2, 3 show a fragment of a multilayer flexible rigidly printed circuit board in a section.

In the figures:

1. Multilayer flexible-rigid printed circuit board;

2. Torsion spring;

3. The flexible part of the circuit board;

4. The hard part of the circuit board.

The device operates as follows.

The torsion spring 2 located at the bend, due to the forces of elastic deformation, transfers the rigid parts 4 of the multilayer flexible-rigid printed circuit board 1 with, for example, solar panels, from the folded position to the deployed one, while the angle between the rigid parts 4 is determined by the spring configuration 2, and the swivel is provided by the flexible part 3 of the multilayer flexible-rigid printed circuit board 1.

Claims (1)

Folding design for ultra-small spacecraft systems based on a multilayer flexible-rigid printed circuit board that combines the functions of a hinge and an electrical conductor between the rigid parts of the folding panels, with a torsion spring located at the bend and rigidly fixed to the ends circuit board, fixing in the extreme position, the movable part of the folding panel is achieved by the configuration of the spring.

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