RU2783370C2 - Device for laying electrical power and interface cables of system for moving nuclear power plant away from spacecraft - Google Patents

Abstract

FIELD: space technology.

SUBSTANCE: invention relates to power equipment of spacecrafts (hereinafter – SC), namely to large-sized transformed farms for laying and arranging electrical cables connecting SC to a nuclear power plant (hereinafter – NPP). The farm contains lower and upper adapters and includes a standard section in the form of a doubled two-lever amplifier mechanism as a base element. A frame with diagonal overlaps is placed in the base of the standard section, combining adjacent sections, with side folded (inward) frames at two opposite faces with built-in sliders and with diagonal frames. On side folded frames, pads are fixed for fixation of cables laid in a loop shape. A pantograph mechanism with a ball-screw transmission is used for arranging and folding the farm.

EFFECT: creation between SC and NPP of a rigid structure of an unfolded farm with the possibility of laying the maximum number of cables with permissible bending radii.

1 cl, 6 dwg

Description

The proposed technical solution relates to devices for stacking (layout) electric power and interface (low-voltage) cables of large-sized transformable systems of spacecraft (SC), folding trusses and retraction systems, which in the folded (transport) position are placed in a small volume and have a small height and in further decomposed to the orbital (working) position with an increase in the occupied volume and height. The main problem with the use of trusses due to their large length and unchanged shape is that their length makes the truss practically impossible to transport under the head fairing (GO) of the launch vehicle (LV), since the total volume occupied is limited by the dimensions of the GO LV and the requirements for position center of mass of the product. Also an important problem is the possibility of laying and laying out the cable when transferring the folding structure to the orbital (working) position.

Classic examples are antenna support trusses, solar panels, antenna reflectors, and the like. However, the scope of truss structures goes far beyond the scope of these examples.

It is known that the device of a transformable truss structure according to the patent (US 5184444) is closest to the claimed invention in terms of technical essence in terms of the design of the base section, where the design of the base section implements a two-lever mechanism, a one-sided folding amplifier, the drive element of which is a pair of springs, only due to the operation of which and deployment is made by means of loosening the cables stretched through the rollers fixed on the sections. However, this technical solution does not provide a guaranteed deployment of the truss structure in the event of jamming of any elements or breakage of the springs, and there is also no possibility to create longitudinal forces on the opening by the drive to loosen the cables. In addition, the possibility of laying a large number of cables is not realized due to the one-sided laying of movable spars and, as a result, the small cross section of a typical section that fits into the transport cylinder together with the spar protruding in the folded position.

The objectives of the proposed technical solution are to ensure the layout of electrical power and interface (low-voltage) cables and the creation of a rigid structure after deployment with the possibility of placing the maximum number of cables of acceptable bending radii in the folded (unfolded) position, minimizing cable resistance during layout.

The technical result achieved when using the solution is to lay out the cables and create a rigid structure after deployment, which is ensured by the use of a folding truss structure in which the truss is placed in its transport position for storage and transportation, which occupies a relatively small volume and has a significantly shorter axial length in relation to the working position. This change in volume and axial length makes it possible to use a long truss in a small container and unfold when needed. The supporting structure of the invention is a collapsible truss. To place the farm in the transport position, a cylindrical container is used.

The specified technical result is achieved by the fact that the problem of adding a rigid structure was solved by introducing the mobility of the longitudinal and diagonal parts and the implementation of storage in the folded (transport) position. It also provides for the presence of elements for eliminating gaps in the hinges, in each of the typical sections, which are collapsible and have a telescopic design.

Structural elements necessary for the integrity of the truss during deployment are rigid elements made of a composite material that can withstand high temperatures, which prevents the entire structure from losing strength when heated.

The specified technical result is achieved by the fact that the device uses a loop-like cable laying scheme. Deployment of the collapsible truss and layout of cable bundles is provided by the use of four compression springs in each section, a drive and two pantographs. Automatic folding of the structure and cables in outer space is not provided. The truss folds up to about 30% of its extended length.

According to the technical solution, all elements and fittings are rigid and made of materials that can withstand high temperatures. The preferred material is a composite material known as carbon-carbon, on the basis of which the tubes of such assemblies are made: lower adapter, upper adapter and typical section. In FIG. 1 shows a general view of the device for moving the nuclear power plant (NPP) away from the spacecraft in the orbital (working) position. In FIG. 2 shows a view of the device in the orbital (working) and starting (transport) positions. In FIG. 1 shows a folding truss, which includes a lower adapter 1, typical sections 3 (the number is determined by the distance of retraction), an upper adapter 5, a drive 21, two pantographs 6 and cable fastening blocks 19 (two for each section of a typical 3 and one common with adjacent section). The root and end typical sections 3 are rigidly fixed on the lower adapter 1 and the upper adapter 5, respectively. Sections typical 3 are hinged to each other. Two pantographs 6 are hinged on the bottom frame 2, the top frame 4, standard sections 3 and two drive triangles 23. Two driving triangles 23 are fixed on the ball screw nut of the drive 21. The drive 21 is rigidly fixed on the drive bracket 22, which is also rigidly fixed on the lower adapter 1. In Fig. 3, fig. 4, fig. 5 and FIG. 6 explains the essence of the invention. In FIG. 4 and FIG. 5 shows the device in transport and intermediate positions, respectively. Sections typical 3 are a two-lever amplifier mechanism with inward folding. In FIG. 3 shows a general view of a typical section in the orbital (working) position. The design of a typical section 3 consists of a lower frame 2, an upper frame 4, two side folding frames with built-in sliders 11, four diagonal frames 12, two guides 13, four sliders 14, four compression springs 15, working position latches 16, four clearance tie rods in the hinges - small 17, two rods to eliminate gaps in the hinges - large 18, four anti-roll bars in the transport position 20 in the transport cylinder. For intended use, the folding truss is placed in a transport cylinder, in which the lower adapter 1 is rigidly fixed, and the upper adapter 5 is fixed with locks, since an element is fixed on the upper adapter 5 that requires the necessary retraction and supply of electric power and interface (low-current) cables 10 to it The folding truss functions as follows.

After launching the spacecraft into the calculated orbit, the locks are activated, the upper adapter 5 is unlocked, the drive 21 is turned on. The rotation of the drive output shaft 21 causes the ball screw nut located on it to move in the axial direction (the direction of expansion). Moving the nut through two drive triangles mounted on it pivotally activates the pantographs 6, which in turn lead to the deployment of all sections of the standard 3 at the same time. Pantographs 6 are hinged on frames with diagonal overlaps 2 and 4. In accordance with the peculiarity of the invention, in the process of deploying typical sections 3, sliders 14 begin to move along guides 13 in a direction perpendicular to the direction of deployment. The movement of the sliders 14 is made possible thanks to the hinged fastening on the diagonal frames 12, which are hinged on the frames with diagonal overlaps 2 and 4. Four compression springs 15 are located on two guides 13 and are fixed between the slider 14 and the side folding frame with built-in sliders 11. Movement of the sliders 14 caused by the operation of the pantograph 6 through the diagonal frame 12 leads to the unfolding of the side folding frame with built-in sliders 11. in the force of the folding farm deployment created by the drive 21 through the pantographs 6. The compression springs 15 begin to work on the deployment of the typical sections 3 in which they are installed, through the unfolding of the side folding frame with built-in sliders 11 at its opening angle of 40 °. The deployment of typical sections 3 leads to the layout of cables 10. The loop-like layout of cables 10 provides acceptable conditions for both transportation and guaranteed unfolding into the working position. The cables 10 are rigidly fixed in the cable fastening blocks 19. The presence of the drive 21, pantographs 6 and compression springs 15 guarantees high reliability of bringing all sections of the standard 3 into working position and the layout of the cables, and, accordingly, the deployment of the entire folding truss. The actuator 21 can be designed for any axial retraction force. In FIG. 6 shows the orbital (working) position of the device for moving the nuclear power plant away from the spacecraft. After bringing the folding truss to the working position, all standard sections 3 are blocked by the latches of the working position 16, which are placed in the sliders 14 and the sliders of the folding frames 11, the latches of the rods to eliminate the gaps in the hinges 17, 18 are also triggered.

The technical solutions used in the design of the retraction device provide the solution of two technically complex and important tasks at once, the relocation of the nuclear power plant from the spacecraft, as well as the layout of electrical power and interface (low-current) cables.

A feature of this invention is the use of a double double-lever mechanism of the amplifier folding inward with floating guides 13, which provides an increase in the cross-section of the folding truss that fits into the transport cylinder and the possibility of placing twice as many cables 10.

The invention can be used both independently and as part of retraction systems by embedding into the existing design and eliminating the drive 21, the drive bracket 22, two drive triangles 23, two pantographs 6 (which include the lower lever 7, the main lever 8 and the lever upper 9), thrust to eliminate gaps in the hinges - small 17 and thrust to eliminate gaps in the hinges - large 18.

Thus, the invention solves the problem of laying out electrical power and interface (low-current) cables of systems for retracting nuclear power plants from spacecraft and can be used both independently and by embedding into an existing structure, or using the invention as a combined system for retracting and laying out cables of antennas, solar panels batteries, antenna reflectors, etc.

Claims (1)

A device for retracting a nuclear power plant from a spacecraft for laying out electrical power and interface, in particular, low-current cables of the retraction system, which is a transformable spatial truss structure, the basic element of which is a typical section, at the base of which there is a frame with diagonal ceilings that unite adjacent sections, with side folding frames with built-in sliders and with diagonal frames that fold inward on two opposite faces, characterized in that on the side folding frames with built-in sliders there are cable blocks for fixing cables laid in a loop, and two cylindrical ones are placed on the other two faces, in particular, hollow guides fixed in sliders of folding frames, on which there are four sliders hinged to rigid diagonal frames, with compression springs installed between the sliders, four in each section and, as well as placed on these faces, on the frames, the lower and upper adapters with pantographs, which are pivotally connected to the triangles, pivotally fixed on the ball screw nut of the drive, which is fixed on the lower adapter through the bracket, and in the working position of the folding truss, all sliders locked on the rails with conical latches.

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