RU2818993C1 - Photoelectric concentrator module - Google Patents

Abstract

FIELD: cosmonautics.

SUBSTANCE: photoelectric concentrator module includes a Fresnel lens panel, a rectangular base located parallel to the plane of the Fresnel lens panel, and end walls in the form of rigid rectangular plates, connected to each other by eight cylindrical hinges, by one hinge at the corners of the base and the lens panel, with hinge axes installed parallel to the ends of the base. An electric motor and a reduction gear are attached to the base, to the shaft of which a rectangular plate is attached, the rotation of which provides the opening of the module in space.

EFFECT: higher efficiency and rigidity during module space orbit launch.

7 cl, 3 dwg

Description

The invention relates to photoenergy, in particular to solar photoenergetic and laser systems intended for generating electricity on spacecraft. Photoelectric conversion of concentrated solar and laser radiation is one of the most effective ways to obtain electrical energy from the Sun and laser radiation in outer space using highly efficient cascade solar cells, photoelectric converters of laser radiation and devices for orienting modules to the Sun or to a source of laser radiation.

A photoelectric concentrator module is known (see US20110017875, IPC B64G 1/44, HOIL 31/042, publ. 01/27/2011), containing a supporting structure of a spacecraft on which photoelectric concentrator modules are mounted, including a plurality of Fresnel reflectors that direct light to a panel of photovoltaic cells thermally connected to a central supporting structure via a heat pipe radiator. The heat pipe ensures the transfer of heat from the panel of photovoltaic elements and its dissipation on the heat pipe radiator and elements of the supporting structure.

The disadvantages of the known photovoltaic concentrator module are low specific energy consumption due to the lack of a solar tracking system for photovoltaic modules and a significant volume of the module when launched into space, due to the lack of a system for folding the module in a transport state.

A solar photovoltaic installation is known (see RU2286517 IPC 7F24J2/42, publ. October 27, 2006), including a rectangular housing containing photoelectric converters located at the foci of Fresnel lenses, and placed on a mechanical system for orientation to the Sun, containing drives for zenithal and azimuthal rotation, equipped with stepper gear motors, and a tracking system equipped with solar position sensors. The mechanical system includes two frames - a base frame, rotating around a vertical axis, and a suspended frame with fixed concentrator photovoltaic modules, providing rotation around a horizontal axis.

The known solar photovoltaic installation has insufficient overall energy efficiency due to the large area of the non-photoactive region and a significant volume of modules in the transport state, which does not ensure its compactness and efficient operation in space operating conditions.

A known thermal photovoltaic module with a parabolic cylindrical concentrator of solar radiation (see RU2554674, IPC H01L 31/054, published on June 27, 2015), including an asymmetric parabolic cylindrical concentrator with a mirror internal reflection surface and a linear photoelectric converter (PVC) located in the focal region with a uniform distribution concentrated radiation along the axis. The linear solar cell is equipped with a coolant flow device. The shape of the reflective surface of the concentrator is determined by a system of equations corresponding to the condition of uniform illumination of the surface of the solar cells, made in the form of a line of switched solar cells and located at an angle to the midsection of the concentrator.

The invention ensures the operation of a thermal photovoltaic module at high concentrations and uniform illumination of the solar cell, obtaining a technically acceptable voltage on one solar cell and increasing the conversion efficiency. The disadvantages of the known thermophotovoltaic module are the need to organize heat removal by circulation of the coolant, as well as the small compactness of the module in the absence of a folding design for the module for its transportation into space, which leads to an increase in the mass-dimensional parameters of the module when it is launched for deployment on a spacecraft.

A concentrator solar power plant is known (see RU2740437, IPC H01L 31/02, publ. 01/14/2021), including a number of concentrator photovoltaic modules with rectangular or square-shaped housings with flanges for attaching panels of Fresnel lenses with silicone sealant and with FEPs placed at the foci of Fresnel lenses. Photovoltaic concentrator modules are interconnected with overlapping flanges along the height in a checkerboard pattern. In this case, in the outer row of concentrator photovoltaic modules and in the rows of photovoltaic concentrator modules parallel to the outer row, the flanges of photovoltaic concentrator modules adjacent along the row are closely overlapped. In rows of modules perpendicular to this outermost row, the flanges of photovoltaic concentrator modules adjacent along the row are spaced in height from each other at a distance at least equal to the total thickness of the flange, silicone sealant and Fresnel lens panel.

The disadvantage of the known concentrator solar power plant is the insufficient compactness of the modules due to the lack of a design for folding the module in a transport state, as a result of which its transportation into space becomes more complicated and more expensive, which does not allow the use of a concentrator solar power plant on a spacecraft.

A folding photovoltaic concentrator module is known (see RU193323, IPC H02S10/40, H02S 30/20, F24H1/06, H02S 40/44, published 10/24/2019), containing a parabolic-cylindrical type concentrator, double-sided solar cells located in the photodetector, and a coolant . The concentrator is foldable, equipped with cylindrical hinges for folding and stands with holes for photovoltaic cells. When folded, the module has the function of protecting double-sided solar cells, and its profile provides illumination of one or two receiving surfaces of solar cells at the same time. The FEP body is made of metal, has combined cavities for various functions and provides its structure with cavities for coolant with inlet and outlet, with the possibility of direct heat removal from the coolant. Double-sided solar cells have p-n junctions parallel to the flow of concentrated solar radiation. Thermal insulation of the coolant and double-sided solar cells is made on both sides. The coolant directly washes sealed double-sided solar cells protected by transparent tempered glass.

A disadvantage of the known photovoltaic concentrator module is the insufficient rigidity of the concentrator structure. The presence of a joint between the folding elements of the concentrator leads to an increase in optical losses when concentrating solar radiation. Also, the selected placement of the PV leads to a shift in the focus of the concentrator relative to the PV, to a decrease in the uniformity of illumination of the PV and to an increase in the reflection of solar radiation.

A photovoltaic concentrator module is known (see US20140078607 IPC G02B 5/10, published 03/20/2014). The known concentrator module includes a base equipped with a rotational element, parabolic-cylindrical concentrators with a mirror internal reflection surface installed on the base, the cylindrical guides of which are parallel to the base and to each other, linear chains of solar cells installed on the upper edge of the back side of each subsequent concentrator in the focal line of each previous concentrator . In this case, the cross-section of each parabolic-cylindrical concentrator, perpendicular to the cylindrical guides, is half a parabola. The rear surface of the first concentrator and the rear surface of the second concentrator face the rotational element, and the front surfaces of the first and second concentrators face in different directions, so that the center of balance is on the rotational element.

The disadvantages of the known photovoltaic concentrator module are the increased mass-dimensional parameters of the module, due to the location of the rotational element on the light-receiving area of the module. In addition, the lack of a folding structure makes it difficult and expensive to deliver modules into space and place them on a spacecraft.

A photoelectric concentrator module is known (see patent US6111190, IPC H01L 31/045, IPC H01L 31/052, B64G 1/44, F24J 2/36, B64G 1/50, publ. 08.29.2000) based on an inflatable Fresnel lens. The module consists of a flexible Fresnel lens, flexible sides and a back surface that together enclose a cavity volume that can be filled with low-pressure gas to deploy the concentrator module in orbit. On the rear surface of the module there is a solar energy photoconverter located in the focal region of the Fresnel lens. In addition, the rear surface can serve as a heat dissipator. Before deployment, the deflated flexible lens and sidewalls are folded on the rear surface to form a flat, low-volume package for efficient launch into space. A photovoltaic concentrator module using an inflatable lens reduces the mass and volume of the module before launching it into space.

A significant disadvantage of the known inflatable concentrator module is its low efficiency due to the low optical efficiency of the inflatable Fresnel lens.

A photovoltaic concentrator module is known (see patent US6075200, IPC H01L 31/052, H01L 31/0232, B64G 1/22, F24J 2/08, B64G 1/44, publ. 06/13/2000), which coincides with the present technical solution to the greatest extent number of essential features and adopted as a prototype. The photovoltaic concentrator module includes a folding housing with folding end walls and a device for its deployment, a Fresnel lens panel housed in the folding housing and a parallel photogenerating panel with solar cells located at the foci of the Fresnel lenses on the front surface of the rectangular base of the photogenerating panel, the back side of which is fixed to solar orientation system. The Fresnel lens panel is flexible and attached to collapsible end walls, with the end walls stretching the Fresnel lens panel to maintain its correct position and shape in space. The housing includes a means for deploying the Fresnel lens panel in space. Before deployment, the flexible Fresnel lens panel and housing end walls are folded into a flat, compact package when launched into space.

The disadvantages of the known prototype photoelectric concentrator module are low efficiency and insufficient rigidity of the folding structure, leading to defocusing of the Fresnel lenses.

The objective of this technical solution is to develop a photovoltaic concentrator module that would have increased efficiency and increased rigidity when launching the module into space orbit.

The problem is solved in that the photoelectric concentrator module includes a folding housing with folding end walls and a device for its deployment, a Fresnel lens panel housed in the folding housing and a parallel photogenerating panel with solar cells located at the foci of the Fresnel lenses on the front surface of the rectangular base of the photogenerating panel , the back side of which is fixed to the solar orientation system. What is new in the photovoltaic concentrator module is that the end walls are made in the form of rigid rectangular plates attached to the corresponding end of the rectangular lens panel and the corresponding end of the rectangular base by means of cylindrical hinges attached to each corner of the base and lens panel. The hinge axes are installed parallel to the ends of the rectangular base. Attached to the rectangular base is an electric drive with a shaft, which is the axis of two cylindrical hinges at the corners of the base, fixed to the end of one of the rectangular plates. At the end of the base adjacent to the electric drive shaft, there is a flat rectangular magnet protruding above the base, on the upper face of which there is a normally open limit electric switch, and on the side face facing the rectangular plate there is a normally closed limit electrical switch. Both limit electrical switches are connected in series to the electrical power supply circuit of the electric drive.

In a photoelectric concentrator module, the electric drive can be made in the form of an electric motor equipped with a gearbox. The rectangular base can be made of a light alloy with high thermal conductivity, for example, aluminum-magnesium alloy AMg or aluminum-manganese alloy AMts to reduce the weight of the module and ensure effective heat removal from photocells located at the foci of Fresnel lenses.

A rectangular plate mounted on the gearbox shaft can be made of a light magnetic alloy, for example, from a permalloy alloy of grade 80НХС or 79НМ or from a permendur alloy of grade 49K2FA or 49КФ.

The second rectangular plate can be made of carbon fiber, which reduces the weight of the module while maintaining sufficient structural rigidity.

The essence of the invention is illustrated by drawings, where:

In fig. Figure 1 shows the design of the module in an open operating state during operation on a spacecraft: 1 - panel of eight Fresnel lenses; 2 - rectangular base; 3,4 - rectangular end walls; 5, 6, 7, 8, 9, 10, 11 - photocells at the foci of Fresnel lenses; 12, 13 - ends of the Fresnel lens panel; 14, 15 - ends of the rectangular base of 2 modules; 16, 17, 18, 19 - cylindrical hinges at the corners of the lens panel; 20, 21, 22, 23 - cylindrical hinges at the corners of the base of module 2; 24 - electric motor equipped with a gearbox; 25 - electric motor shaft 24; 26, 27 - ends of the rectangular base;

In fig. Figure 2 shows the design of the module in a folded transport state: 28 - magnet; 29 - final normally open switch; 30 - final normally closed switch;

In fig. 3 - Module design in a folded transport state: 32 - module protective casing; 33 - part of the spacecraft body or part of the photovoltaic battery structure.

This photovoltaic concentrator module includes a flat rectangular Fresnel lens panel 1 (Fig. 1), a flat rectangular base 2 located parallel to the plane of the rectangular Fresnel lens panel 1, made with a length and width equal to the dimensions of the rectangular panel 1, interconnected by rigid rectangular plates 3 ,4, installed perpendicular to the planes of panel 1 and base 2, and photocells 5, 6, 7, 8, 9, 10, 11, located on base 2 at the point foci of Fresnel lenses. Two rigid end rectangular plates 3, 4 are connected to two ends 12, 13 of the Fresnel lens panel 1 and to two ends 14, 15 of the base 2 by eight cylindrical hinges 16, 17, 18, 19, 20, 21, 22, 23, one hinge per each corner of the base 2 and the lens panel 1, while the axes of these cylindrical hinges are installed parallel to the mentioned ends of the base 2. This design of the module using eight cylindrical hinges 16-23 to connect the lens panel 1 with the base 2 allows for mutual horizontal and vertical movement of the lens panel 1 relative to the base 2, which is necessary for folding the module in a transport state when it is delivered to orbit as part of a spacecraft and for the subsequent deployment of the module in working condition. Attached to the base 2 of the module is an electric motor 24 equipped with a gearbox (Fig. 2), the shaft 25 of which is mounted on two cylindrical hinges 21, 23 coaxial with the shaft 25, to which a rectangular plate 3 is attached at its end. Using an electric motor 24 equipped with a gearbox (Fig. . 2), attached to the base 2, is necessary to ensure the opening of the module and bring it into the operating state shown in Fig. 1, after its delivery into space orbit. In this case, the opening of the module is ensured by the rotation of the shaft 25 and the rigid rectangular plate 3 of the module attached to the shaft 25 in the direction shown in Fig. 2 arrow. At the end 15 of the base 2 adjacent to the shaft 25, a flat rectangular magnet 28 protruding above the base 2 is installed, on the upper face of which there is a normally open limit electric switch 29, and on the side face facing the rectangular plate 3 there is a normally closed limit electric switch 30. Electrical switches 29 and 30 are connected in series to the electrical power supply circuit of the electric motor 24 (not shown in the drawing). Magnet 28 (Fig. 2), installed at the end 15 of the base 2, ensures fixation of the position of the rectangular plate 3 after completion of the module opening and bringing it into working condition (Fig. 1). The photovoltaic module in the folded transport state can be equipped with a protective casing 32 (Fig. 3) adjacent to the lens panel 1 and to the first normally open switch 29 (Fig. 3), configured to turn on the electric motor 24 when removing the protective casing 32, and the second a normally closed switch 30 (Fig. 2) is configured to turn off the electric motor 24 in the operating open state of the module with mechanical contact of the switch 30 and the magnet 28 with a rectangular plate 3 rotated by the shaft 25. The protective casing 32, covering the front surface of the module in a closed transport state, may be necessary to prevent damaging effects on the module under adverse environmental conditions during the launch and insertion of the spacecraft 33 into orbit. When installed, the protective casing 32 is adjacent to the normally open first switch 29, which prevents the electric motor 24 from being turned on in the transport state of the module. When removing (“shooting”) the protective casing 32, the electric motor 24 is turned on and the module opens. The normally closed switch 30 turns off the electric motor 24 as a result of mechanical contact of the rectangular plate 3 of the module with the switch 24 at the moment the module opens.

The use of aluminum-magnesium alloys AMg or aluminum-manganese alloys AMts, which have high thermal conductivity (160-178) W/m⋅K) and low density (2.64-2.78 g/cm ³ ) for the manufacture of the base of 2 modules, ensures effective removal heat from photocells during operation of the photovoltaic concentrator module and reduces the weight of the concentrator module.

Permalloy alloys of grade 80НХС or 79НМ and permendur alloys of grade 49K2FA or 49КФ, used for the manufacture of rectangular plate 3, have high magnetic permeability - (120-250)10 ³ GN/m and high strength and elasticity, which provides a high clamping force of plate 3 per due to magnetic attraction to the side surface of the magnet 28 and good structural rigidity in the operating position of the module

Example

A concentrator photovoltaic module was fabricated based on a panel with eight Fresnel lenses measuring 12 cm × 12 cm each and eight photocells measuring 0.5 cm × 0.5 cm each located at the foci of point Fresnel lenses. The dimensions of the module in the opened working state were 48 cm × 24 cm × 22 cm. The dimensions of the module in the closed transport state were 70 cm × 24 cm × 1 cm. The thickness of the base, made of AMg2 alloy, was 0.6 cm, the thickness of the lens panel was 0 .4 cm. The diameters of the cylindrical hinges, the thickness of the electric motor, magnet and switches were 1 cm each. The side plate adjacent to the magnet was made of permalloy alloy grade 80НХС. Thus, the manufactured module provided a reduction in the volume of the module by more than 15 times in the folded transport state compared to the volume of the module in the open operating state. The module had an efficiency of >32% solar radiation conversion, which exceeds the efficiency of photovoltaic modules with linear Fresnel lenses.

The developed folding photovoltaic concentrator module provides a more than 15-fold reduction in the volume of the module in the folded transport state, which, in turn, significantly reduces the cost of delivering it into space as part of a spacecraft.

Claims (7)

1. Photovoltaic concentrator module, including a folding housing with folding end walls and a device for its deployment, a Fresnel lens panel housed in the folding housing and a parallel photogenerating panel with solar cells located at the foci of the Fresnel lenses on the front surface of the rectangular base of the photogenerating panel, the back side which is fixed to the solar orientation system, characterized in that the end walls are made in the form of rigid rectangular plates attached to the corresponding end of the rectangular lens panel and the corresponding end of the rectangular base by means of cylindrical hinges fixed at each corner of the base and the lens panel, the hinge axes are installed parallel the ends of the rectangular base, an electric drive with a shaft is attached to the rectangular base, which is the axis of two cylindrical hinges at the corners of the base, fixed to the end of one of the rectangular plates; At the end of the base adjacent to the electric drive shaft, there is a flat rectangular magnet protruding above the base, on the upper face of which there is a normally open limit electric switch, and on the side face facing the rectangular plate there is a normally closed limit electric switch, connected in series to the electrical power supply circuit of the electric drive. . 2. The module according to claim 1, characterized in that the electric drive is made in the form of an electric motor equipped with a gearbox. 3. Module according to claim 1, characterized in that the rectangular base is made of a light alloy with high thermal conductivity. 4. The module according to claim 3, characterized in that the base is made of an aluminum-magnesium alloy or an aluminum-manganese alloy. 5. The module according to claim 1, characterized in that the rectangular plate mounted on the gearbox shaft is made of a light magnetic alloy. 6. The module according to claim 5, characterized in that the rectangular plate mounted on the gearbox shaft is made of permalloy alloy or permendur alloy. 7. Module according to claim 1, characterized in that the second rectangular plate is made of carbon fiber.

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