RU2560213C2 - Fastener of large-size flat structures on spacecraft - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to means of docking of spacecraft and their equipment, particularly, spacecraft radar antennas. Claimed device comprises load-bearing pins (LBP) arranged in mirror axes and coupling units (CU). LBPs are provided with spring-loaded rollers enclosed by yokes secured at radar antenna. CUs are arranged at bearing belts and secured at radar antenna (7) via heat-insulation spacers (6). Stiff coupling between radar antenna (7) and frame (1) is realized at intersection of radar antenna mirror axes. CUs are composed of cranks (16) with pins (17, 18) in rolling bearings (19, 20) running in housings (21, 22). One of said housings is secured at frame (1) while another one is fixed at radar antenna (7). Radii of cranks are selected proceeding from permissible strains in radar antenna.

EFFECT: enhanced performances, simplified design and higher reliability.

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Description

The invention relates to space technology and is intended for fastening large-sized flat structures on a spacecraft (KA), for example, fixed flaps of solar batteries (BS), fixed flaps of disclosed radar antennas (RLA), stationary radar, etc.

A problematic issue when attaching these structures to a spacecraft is the distortion of the plane of their working surfaces when exposed to large temperature drops. For some designs, for example for BS, these distortions do not significantly affect the reliability of their work, for others, for example, for radar, even a slight distortion of the plane of the working surface greatly reduces the reliability of their work.

The well-known "Container tank for liquid cryoproducts" according to the patent for invention RU No. 2208568, which describes a fastening device containing a frame in the form of a supporting structure, support nodes, communication nodes containing hydraulic cylinders placed on power belts connected with an arm, with heat insulating gaskets.

The disadvantages of the known technical solution are its limited use, since ensuring the tightness of hydraulic cylinders with a long lifetime of a spacecraft in orbit is problematic, and their presence complicates the fastening structure, and installation at the joints of elements with sliding friction (in pairs of centering protrusion-bracket) does not exclude the possibility of jamming in contact points.

The objectives of the claimed technical solution are to expand its ability to use, simplifying the design and improving reliability.

The objectives of the claimed technical solution are solved in that in the device for attaching large-sized flat structures to the spacecraft, comprising, a frame in the form of a supporting structure, rigidly mounted on the spacecraft, support nodes and communication nodes located on power belts and equipped with heat-insulating spacers, characterized in that that at the point of intersection of the axes of symmetry of a large-sized flat design, for example, a radar antenna, there is a rigid connection of the radar antenna with the frame, while e nodes located along the symmetry axes of the radar antenna are made in the form of spring-loaded rollers covered by forks mounted on the radar antenna, while the rollers interact with the grooves of the plates rigidly mounted on the radar, and the communication nodes are made in the form of cranks, the axes of which interact with the bearings rolling elements fixed in the cases, one of which is fixed on the frame, and the other on the radar antenna.

The inventive design of the device shown in the drawings:

FIG. 1. General view of the device;

FIG. 2. Section AA in FIG. one;

FIG. 3. View B in FIG. one;

FIG. 4. The extension member B in FIG. 2;

FIG. 5. View G in FIG. four;

FIG. 6. The remote element D in FIG. 3;

FIG. 7. The remote element E in FIG. 3;

The device consists of a frame 1 in the form of a supporting structure, rigidly fixed to KA 2, support nodes (OS) 3 and communication nodes (CSS) 4 located on power belts 5 and equipped with heat-insulating spacers 6, while at the point of intersection of the symmetry axes (TPOS ) radar antenna (RLA) 7 there is a rigid connection between the RLA 7 and the frame 1, OS 3 are located along the symmetry axes of the RLA 7 and are equipped with rolling bearings 8 and spring-loaded packages of disk springs 9 forks 10 rollers 11 interacting with the grooves 12 of the plates 13 mounted on the radar 7, pr this, the forks 10 of the spring-loaded rollers 11 are fixed by technological nuts 14 before the assembly of the spacecraft 2, and the US 4 are located on the lines 15 and are made in the form of cranks 16 oriented perpendicular to the lines 15, while the axes 17, 18 of the cranks 16 interact with the rolling bearings, 19, 20 fixed in the hulls 21, 22, one of which is mounted on the frame 1, and the other on the radar 7 at distances X, Y, while the values of the radii of the cranks are selected constructively, based on the permissible voltages in the radar antenna.

The claimed technical solution allows to simplify the design, increase reliability and expand its capabilities.

Claims (1)

A device for attaching large-sized flat structures to a spacecraft, comprising a frame in the form of a supporting structure, rigidly fixed to the spacecraft, support nodes and communication nodes located on power belts and provided with heat-insulating gaskets, characterized in that at the point of intersection of the symmetry axes of the large-sized flat structure, for example, a radar antenna (RLA), there is a rigid connection between the RLA and the frame, while the support nodes located along the symmetry axes of the RLA are made in the form of spring-loaded p oaks covered by forks mounted on the radar, the rollers interacting with the grooves of the plates rigidly fixed on the radar, and the communication nodes are made in the form of cranks, the axes of which interact with the rolling bearings mounted in the housings, one of which is mounted on the frame, and the other on RLA.

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