RU2492124C1 - Space solar electric station and independent photo emitting panel - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: set of intentions relates to space power engineering and may be used for transmission of electric power in the form of laser radiation to Earth surface and for high-accuracy measurements in space, data transfer, etc. Proposed station comprises base module 1, system of mirrors 2, laser radiation summator 3 directed to system 2 and photo converter panel 4 arranged outside of module 1. Every panel 4 consists of two types: photoelectric panels 5 and independent photo emitting panels 6. The latter are connected in chain for self-opening and arranging in closed flat zigzag-like figure. Panels 5 are mounted at the start of chain 5, 6. Note here that the first panel is connected with base module 1. Said module 1 comprises the following systems: control system 8, cooling system 11 and supply system 12. Every panel 5 is connected with supply system 12. Every independent panel 6 is composed of a carcass with Fresnel lenses are carcass end with photo converters (not shown) aligned therewith and located there above. Carcass bottom part base accommodates power accumulators, control unit of panel 6 and fiber lasers with pumping units and laser radiation summator. Aforesaid photo converters of panel 6 are electrically connected via power accumulators with pumping and control units. Summators of independent panels 6 are connected to aforesaid summator via FO 30.

EFFECT: higher efficiency and reliability, longer life and expanded operating performances.

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Description

The invention relates to space technology and, in particular, to energy and can be used in space technology to convert solar energy into electrical energy and transmit it to the surface of the Earth, the Moon or other objects by laser radiation. At the same time, the second invention used in the first can have wider application, namely, in space technology objects for conducting high-precision angular and geometric and remote measurements with its help, for transmitting information, and also as a signal device for detecting or tracking space or descent vehicles, and on Earth in geodesy and cartography as a mark.

A known spacecraft for remote transmission of energy, which includes a solar power installation, an instrumentation compartment with control systems, a cooling system and a system for remote transmission of energy in the form of laser radiation (patent application RU No. 94032672/11 of 09.09.1994, B64G 9/00, publication date: 07/10/1996). The disadvantages of this design are: the implementation of the device for remote transmission of energy in the form of a single powerful laser, which leads to insufficient reliability and durability of the station, since a failure or malfunction of the laser and devices that ensure its operation leads to failure of the entire space power plants

A solar space power station (SKES) is also known, which includes a base module containing a control system with a control computer, a cooling system and a power system, photoconverting panels connected to it, and a remote energy transmission device including a mirror system (presentation materials from ASTRIUM , Prague, 10/01/2010 and the website of the specified company - www. Astrium.eads.net). The disadvantages of this design are: the implementation of the device for remote transmission of energy in the form of one powerful laser, which leads to insufficient reliability and durability of the station, since failure or malfunction of the laser and devices that ensure its operation (multi-circuit cooling system), leads to failure of the entire space power plant, in addition, the implementation of the photoconversion panel in the form of thin-film solar panels also has several disadvantages, such as low efficiency, large energy losses in the cable network, its large size and weight, which also leads to a decrease in the efficiency, reliability and durability of the station. The implementation of a multi-circuit cooling system necessary to ensure the operation of a powerful laser also reduces the reliability of the SCES due to the complexity and weight of the structure. This technical solution is the closest to the proposed space solar power station and is selected as a prototype.

The technical solution according to the invention is aimed at achieving a technical result, which consists in increasing the efficiency, reliability and durability of the SCES.

The specified technical result is achieved by the fact that, as in the well-known, taken as a prototype, solar space power plant, which includes a base module containing a control system with a control computer, a cooling system and a power system, photoconversion panels connected to the base module, and the device remote transmission of energy, including a mirror system, in the proposed solar space power plant, each photoconversion panel is made in the form of a system of two types of panels - photoelectric panels and autonomous photo-emitting panels (AFIP) interconnected with the possibility of self-disclosure, for example, in the form of metal drives with memory, and lining up in a closed flat zigzag shape. Photovoltaic panels are mounted first in a chain of panels and the first one is connected to the base module. Each photovoltaic panel is a photovoltaic battery mounted in a frame in the form of a hexagonal carbon fiber prism. The upper end of the frame is a mesh-rod structure, in the grid cells of which Fresnel lenses are mounted, with photoconverters located in their foci and electrically connected to the power supply system of the base module, mounted on the heat sink base of the frame, to which the rods of the upper end of the frame are connected. Each autonomous photo-emitting panel consists of a frame in the form of a hexagonal prism made of carbon fiber with a heat-removing base and an upper end made in the form of a mesh-rod structure, in the cells of which Fresnel lenses are mounted. The rods of the frame are connected to the heat sink system of the photoconverters coaxial to the Fresnel lenses. Moreover, this heat sink system is a mesh-rod construction made of carbon fiber with an admixture of silicon carbide in the amount of 20% -25%, on the nodes of which there are photoconverters, between which a layer of heat-insulating material is laid, and its rods mounted on nodes on the opposite side of the grid, connected to the heat sink base of the frame. In addition, inside the frame, on its base, a control unit for a photo-emitting panel with a transmitting and receiving antenna is mounted, a device for converting electric energy into light energy, in the form of fiber lasers with pumping units, an adder and energy storage devices. In this case, the photoconverters are electrically connected to the pumping units and the control unit through energy stores. The remote energy transfer device is also provided with a laser radiation adder, and the adders of each photo-emitting panel are connected to the adder of the remote energy transmission system via a fiber optic cable. The specified adder is directed to the mirror system. The control system of the base module includes a radio transmitter for controlling the operation of autonomous photo-emitting panels and a transmit-receive antenna for communication with the ground segment.

The refusal of one powerful laser due to the implementation of photoconverting panels in the form of a chain of photovoltaic panels that generate energy to power the base module, and autonomous photo-emitting panels, each of which includes several low-power fiber lasers with pumping units and photovoltaic batteries supplying them, allowed to increase the efficiency, reliability and durability of the XPS, since the photo-emitting panels are autonomous, the failure of lasers of one AFIP does not affect the work of the rest AFIP's and space power as a whole, there is only the loss of some of the power. The implementation of photoconversion panels in the form of a chain of photovoltaic and stand-alone photo-emitting panels interconnected by metal drives with memory and with the ability to form a flat closed zigzag shape upon opening allows a fairly compact design, unlike the prototype SCES, where the photoconversion panels are made according to thin-film technology and disclosed with the help of a long astromast, which also affects the efficiency, reliability and durability of SCES, since thin-film night technology provides low efficiency, large energy losses in the cable network, as well as the large size and weight to ensure rigidity. The placement of several low-power lasers in each AFIP made it possible to use a simpler instead of a complex multi-circuit cooling system for them, for example, the base of the AFIP frame in the form of a metal heat sink plate, which also affects the reliability and weight of the structure. In addition, the implementation of self-contained photo-emitting panels allows you to increase their number both after the assembly of the SCES and during its operation, which also affects its effectiveness.

A self-contained device is known that converts solar energy into light energy, consisting of a frame, a device for converting solar energy into electrical energy and mounted inside the frame on its base, a control unit, a device for converting electric energy into light energy and energy storage devices connected to these devices (patent for utility model RU No. 110857 dated 06/16/2011, B64G 3/00, H01L 33/00, G08G 1/09). In this device, the conversion of solar energy into electrical energy is carried out by means of solar panels mounted on the outer surface of the frame, and the device for converting electrical energy into light is made in the form of an assembly of laser diodes and a lens system, the device is used as a signal device for detecting or tracking space or descent devices, as well as in space geodesy for high-precision goniometric measurements. The disadvantages of this device are the impossibility of its use in space energy as photoconverting elements in SCES, since the conversion of solar energy into electrical energy is carried out by means of solar panels located on the outer side surface of the frame and the inability to assemble them into a large photoconverting panel, for example, for use in solar space power plants of the proposed design, in addition, this device forms a beam with a large angle of divergence and that can not be used for the transmission of electricity generated from user space.

The solution known from patent RU No. 110857, made as a prototype for the present invention relating to a standalone photo-emitting panel.

The present invention is aimed at achieving a technical result, which consists in expanding the functionality of the device and, accordingly, the field of its application, in particular in space solar power plants, in photoconversion panels.

The proposed stand-alone photo-emitting panel, as well as the device closest to it, contains a frame with a base, a device for converting solar energy into electrical energy and mounted inside the frame on its base, a control unit, a device for converting electrical energy into light energy and connected to these devices, energy storage devices.

To achieve the above technical result, a device for converting solar energy into electrical energy is mounted inside the frame, in its upper part, separated from the lower part by a layer of thermal insulation. The device for converting solar energy into electrical energy is a photovoltaic battery made in the form of a set of Fresnel optical lenses and photoconverters located in their foci with a heat sink system. The base of the frame is made of heat sink and connected to the heat sink of the photoconverters. The device converting electrical energy into light is a fiber lasers with pumping units and a laser radiation adder. The photoconverters located in the upper part of the frame are electrically connected through energy storage devices to the fiber laser pumping units and the AFIP control unit with a transmitting and receiving antenna.

The proposed technical solution allows it to be used both as a signal device and for navigation, and, for example, in space solar power plants in photoconversion panels. The implementation of the device for converting solar energy into electrical energy in the form of a photovoltaic battery and placing it in the upper part of the frame allows the processing of solar energy into electrical energy, while the side faces of the frame are free and can be connected to other autonomous photo-emitting panels (AFIPs), forming flat structures with large areas of any configuration, in particular in the SCES according to the first invention. At the same time, since each AFIP has its own low-power fiber lasers with their pumping units, respectively, each AFIP not only generates electric energy, but also converts it into light and can transmit it to the Earth or other object via optical fiber (use in navigation or signal devices), and when summing the flows from all AFIPs (use in SCES), it becomes possible to generate and transmit a large amount of energy from space to the consumer using a laser beam.

The proposed AFIP design allows its use not only in space but also on Earth, in geodesy and cartography as a mark with greater efficiency than the prototype, since the location of the photovoltaic battery for converting sunlight into electrical energy in the upper part of the frame, and not on its lateral sides as in the prototype, eliminates the shadowing of the battery, for example, by vegetation, while the transmission of light through a flexible fiber (fiber laser), allows you to direct the beam in any direction.

The use of Fresnel lenses as optical lenses in AFIPs, which have a lower mass with the same characteristics as compared to conventional conventional and higher concentrations, improves performance, increases the reliability and efficiency of AFIPs. Photoelectric converters are heterostructured solar cells, since they have significantly higher efficiency compared to thin-film photoconverting cells, and energy storage devices are made in the form of supercapacitors (the concept of a supercapacitor is common and is used in the technical literature, in particular, see the journal Electronics: Science , Technology, Business ”, No. 7, 2009). The frame is expediently made of carbon fiber in the form of a hexagonal prism, since this material is selected because of its distinctive properties: high strength, lightness, heat resistance, low heat conductivity, and execution in the form of a hexagonal prism allows, when used in SCES, to be compactly folded under a fairing, and in the unfolded one to form a figure of a large area with minimal gaps between the AFIP. When used in SCES, as one of the options, it is advisable to carry out the heat removal system of photoconverting elements through the heat sink base of the frame, for example, in the form of a mesh-rod structure made of carbon fiber with an admixture of silicon carbide in an amount of 20% -25% (this ratio provides the optimal ratio of stiffness and thermal conductivity of the structure), at the nodes of the grid to which the photoconverters are mounted, and the rods attached to the nodes on the opposite side of the grid are connected to the heat sink base sa.

The AFIP framework is expediently made in the form of a hexagonal prism made of carbon fiber, the upper end of which is a mesh-rod structure, in the cells of which Fresnel lenses are located, and the rods are connected to the heat transfer system of the photoconverters. In this case, these rods will act as structural stiffeners.

In addition, the AFIP control unit is equipped with a transmit-receive antenna for wireless communication, the use of a Wi-Fi system eliminates wires, which facilitates the design and increases its reliability.

The invention is illustrated by drawings of figure 1 - figure 13, which shows:

- figure 1 is a functional diagram of the SCES;

- figure 2 - photovoltaic panel;

- figure 3 is a photo-emitting panel;

- figure 4 is a top view of figure 3;

- figure 5 is a functional diagram of a photo-emitting panel SKES;

- figure 6 is a functional diagram of a photo-emitting panel;

- Fig.7 is a design of a photo-emitting panel in layers;

- on Fig-Fig.13 - the steps of the disclosure of photoconversion panels.

Figure 1 presents the functional diagram of the SCES, which includes the base module 1, the mirror system 2, the adder of laser radiation 3 of the remote energy transmission device, aimed at the mirror system 2 and photoconversion panels 4, mounted on the outer surface of the base module 1.

Each photoconverting panel 4 is made in the form of a system of two types of panels - photovoltaic panels 5 and autonomous photo-emitting panels 6, interconnected in a chain with the possibility of self-opening by means of actuators 7 made of metal with memory, and alignment when opening a flat closed zigzag shape (Fig. .8-Fig. 13). Photovoltaic panels 5 are mounted first by a chain of panels 5, 6 (Fig. 13) and the first one is connected to the base module 1.

The basic module 1 includes a control system 8 with a control computer (not shown), a radio transmitter 9 for controlling the operation of autonomous photo-emitting panels 6, and a transmit-receive antenna 10 for communication with the ground segment, as well as a cooling system 11 and a power system 12 with energy storage devices (not shown) (Fig. 1).

In more detail, the design of the photovoltaic panel 5 is presented in figure 2.

Each photovoltaic panel 5 is a photovoltaic battery mounted in a frame 13 in the form of a hexagonal prism made of carbon fiber, the upper end of which is a mesh-rod structure, in the mesh cells of which are mounted Fresnel lenses 14, located in their foci and electrically connected to the power system 12 of the base module 1 by photoconverters 15 mounted on the heat sink base 16 of the frame 13, to which the rods of the upper end of the frame are connected. The energy generated by the photoconverters 15 is directed to the power of the control computer of the control system 8. The frame 13 of the last in the chain of the photovoltaic panel 5 is connected to the frame 17 (Fig.13) of the first stand-alone photo-emitting panel 6.

In more detail, the design of the photo-emitting panel 6 is presented in figure 3.

Each autonomous photo-emitting panel 6 consists of a frame 17 in the form of a hexagonal prism made of carbon fiber with a heat-removing base 18 and an upper end made in the form of a mesh-rod structure (Fig. 4), in the cells of which Fresnel lenses 19 are mounted, the rods of which are connected to the heat sink system 20 photoconverters 21, coaxial with Fresnel lenses 19, while this heat sink system 20 is a mesh-rod structure made of carbon fiber with an admixture of silicon carbide in the amount of 20% -25%, on the nodes of which are located s photoconverters 21, between which a layer of heat-insulating material 22 is laid, and its rods 23 are connected to the heat-removing base 18 of the frame 17, in addition, inside the frame 17, on its base 18, energy storage devices 24, a control unit 25 of the photo-emitting panel 6 with a receiving transmitting antenna 26, a device for converting electrical energy into light, in the form of fiber lasers 27 with pumping units 28 and an adder 29 (see 5), while the photoconverters 21 are electrically connected to the pumping units 28 and the control unit 25 through energy stores 24, in addition, the remote energy transmission device is also provided with an adder 3 of laser radiation, and adders 29 of each photo-emitting panel 6 are connected to the adder 3 of the system remote transmission of energy by means of a fiber optic cable 30, and the specified adder 3 is directed to the mirror system 2, while the control system of the base module 8 includes a radio transmitter 9 for controlling the operation of the autonomy mnyh fotoizluchayuschih panels 6 and the receiving-transmitting antenna 10 communication with a ground segment.

Space solar power station operates as follows.

After the SCES is put into a given orbit, on command from the ground control point, the photoconversion panels 4 are opened according to a certain algorithm and each of them is arranged in a flat closed zigzag shape. Then, information is transmitted to the base module 1 via wireless (Wi-Fi) on the opening state of each photoconversion panel 4, as well as information on the internal state of each AFIP 6 (Fig. 5) is transmitted (temperature - temperature sensors 31, cable integrity - current sensors 32 , the charge of supercapacitors 24-capacitive sensors 33, the integrity of the optical fiber - photosensors 34 and the serviceability of the control unit 25 AFIP 6). Then there is the installation of the radio channel through the transmit-receive antenna 10 with the ground segment and the transmission of information about the state of the SCES.

When the SCES is located on the illuminated part of the orbit, the electric current generated by the AFIP 6 photoconverters 6 charges the supercapacitors 24 and, in parallel, feeds the pump units 28, for example, in the form of a line of diode lasers used to pump fiber lasers 27. Number of fiber lasers 27 may vary, based on the conditions of the optimal ratio of the amount of transmitted energy and the provision of sufficient heat sink base 18 for the normal operation of AFIP. Further, in the adder 29 of each photo-emitting panel 6, the flux from each laser 27 is summed. By optical fiber 30 from each photo-emitting panel 6, the radiation arrives at the adder 3, directed to the mirror system 2 of the SKES remote energy transmission device, from where it is transmitted to the ground segment for receiving and converting laser radiation into electrical energy.

When the solar space power station is located in the unlit part of the orbit, the electric current necessary to power the AFIP control unit 25 and pump units 28, made, for example, in the form of a line of diode lasers, is generated from energy storage devices 24, such as supercapacitors.

The photoconverters 15 of the photovoltaic panels 5 convert the solar energy into electrical energy and are electrically connected to the power system 12 with energy stores (not shown) of the base module 1 and the energy generated by them is directed to the power of the control computer of the control system 8.

In the process of operation of the SCEC upon requests from the Earth to the base module 1 to check the status of autonomous photo-emitting panels 6, the request is transmitted to the control unit 25 of the AFIP 6 via wireless communication (the radio transmitter 9 of the base module 1 is the transmit-receive antenna 26 of each AFIP 6), in the case of if one of the AFIP 6 (or several) fails, then the control unit 8 will give a command to turn them off, and the whole SKES will continue to work, albeit with less efficiency, due to the implementation of the photo-emitting panels 6 autonomous. Since several low-power lasers 27 are installed on each AFIP, the heat removal provides the base 18 of the frame 17 (for example, in the form of a metal plate), the heat removal system will be correspondingly more reliable and lightweight, and the exclusion of a powerful laser from the base module eliminates the need for a complex system heat sink of the base module, which also affects the efficiency of the SCES.

The proposed stand-alone photo-emitting panel, the functional diagram of which is shown in Fig.6, and the construction in layers in Fig.7, consists of a frame 1 with a base 2, a device 3 converting solar energy into electrical energy (Fig.6) and mounted inside the frame 1, on its base 2, control unit 4, device 5 (Fig.6) converting electrical energy into light energy and connected to the indicated devices 3, 5 and control unit 4 of energy storage 6. The device 3 for converting solar energy into electrical energy is mounted inside to frame 1, in its upper part and is separated from the lower part by a thermal insulation layer 7. Device 3 is a photovoltaic battery made in the form of a set of Fresnel optical lenses 8 and photoconverters 9 located in their foci with a heat sink system 10. The base 2 of the frame 1 is made of heat sink, for example, in the form of a metal plate and connected to the heat sink system 10 of the photoconverters 9. The device 5 for converting electrical energy into light is installed on a heat sink base 2, in curl lasers 11 pump units 12 and the adder 13 of laser radiation. The control unit 4 includes a transmitting and receiving antenna 14 (Fig.6) and is also mounted on a heat sink 2. The number of installed lasers is selected taking into account the specific problem being solved. The photoconverters 9 located in the upper part of the frame 1 are electrically connected through energy storage devices 6 mounted on the heat sink 2, to the pumping units 12 of the fiber lasers 11 and the control unit 4. As one of the possible variants, the heat removal system 10 of the photoconverters 9, which is made in in the form of a mesh-rod structure made of carbon fiber with an admixture of silicon carbide in an amount of 20% -25%, at the nodes of the grid, which are mounted photoconverters 9, and the rods mounted on nodes with the opposite Torons grid connected to the heat dissipating base 2. The frame 1 is made of carbon fiber, since the active material is selected because of its distinctive properties: high strength, light weight, heat resistance, low thermal conductivity. Execution in the form of a hexagonal prism is presented as one of the options for execution. Photoelectric converters 9 are heterostructured solar cells, since they have significantly higher efficiency compared to other photoconverting cells. Energy storage 6 is made in the form of supercapacitors.

The frame 1 of the self-contained photo-emitting panel is made in the form of a hexagonal prism made of carbon fiber, the upper end of which is a mesh-rod structure 15, in the mesh cells of which are Fresnel lenses 8, and the rods are connected to the heat transfer system of the photoconverters and serve to ensure structural rigidity.

Autonomous photo-emitting panel operates as follows.

AFIPs are oriented in space so that the sun's rays fall perpendicular to the surface of the Fresnel lens 8. After focusing, the rays of light fall on the active surface of the photoconverters 9, which directly convert the energy of solar radiation into electrical energy and transfer it through energy storage 6 to the pump units 12. The pumping units 12 activate fiber lasers 11, the light energy from which is transmitted by means of optical fiber to the adder 13. A part of the energy from the energy storage devices 6 is received powered control unit 4. By means of the receiving-transmitting antenna 14 to the control unit 4 commands come about the verification status AFIP. (temperature - temperature sensors 16, cable integrity - current sensors 17, charge of supercapacitors 6 - capacitive sensors 18, fiber integrity - photo sensors 19 and serviceability of the AFIP control unit 4). After the control unit 4 has polled all the systems to be checked, the information is transmitted back to the control point. If all systems work normally, then a command to turn on the AFIP is issued from the control point. If problems occur during the operation of the AFIP, the control unit 4 automatically transmits information about the AFIP fault to the control point, after which a command is sent from the control point to disable the faulty AFIP.

As a signal device, the proposed AFIP will work similarly to the device taken as a prototype, i.e. when the spacecraft on which AFIP is installed as a signaling device is in the illuminated part of the orbit, sunlight focused by Fresnel lenses is converted into electric current by AFIP photoconverters 9, which charges supercapacitors 6 and, in parallel, powers the pump units 12, for example , in the form of a line of diode lasers, used to pump fiber lasers 11. Next, in the adder 13, the summation of the fluxes from each laser 11 occurs.

When the spacecraft is on the unlit part of the orbit, the electric current necessary to power the AFIP control unit 4 and pump units 12, made, for example, as a line of diode lasers, is generated from energy storage devices 6, for example, supercapacitors.

High-precision determination of the angular coordinates of spacecraft is carried out as follows: after the start of the operation of the AFIP, the signal of the device included in the control unit (formed depending on the tasks being solved) is pulsed signal modulation. The nature of the light signal of the device can be supplemented by coding for the duration and frequency of flashes (provided by the encoder of the control unit), which will ensure reliable identification of a space object of artificial origin.

Modern ground-based optical surveillance tools allow you to confidently observe the encoded signals of this device.

The installation on board a spacecraft of a source of optical radiation directed at the observer can guarantee both the detection of an object and its qualitative positional measurements. For example, AFIP as a light source mounted on an irradiator of a pointed antenna (ON) of a spacecraft will shine in the same direction that the antenna is directed, and an optical instrument located, as a rule, near a ground radio communication point, will receive a sufficiently strong light flux so that his registration is sure.

All spacecraft in the radio channels have IT. With the typical size of the radiation pattern IT about an degree, an orientation system of the same accuracy is required for its operation, therefore, the installation of the proposed AFIP on the external (non-working) part of the irradiator as an autonomous signal device allows the use of a narrow light beam.

Claims (7)

1. A solar space power plant, including a base module, comprising a control system with a control computer, a cooling system and a power system, photoconversion panels connected to the base module, and a remote energy transmission device comprising a mirror system, characterized in that each photoconversion panel made in the form of a system of panels of two types: photovoltaic panels and stand-alone photo-emitting panels, interconnected in a chain with the possibility of self-opening and shots in a closed flat zigzag shape, while the photovoltaic panels are mounted at the beginning of the panel chain and the first one is connected to the base module, each photovoltaic panel is a photovoltaic battery mounted in a frame in the form of a carbon hexagonal prism, the top end of which is mesh-rod structure, in the mesh cells of which Fresnel lenses are mounted with their foci located and electrically connected to the base power system it was fired by photoconverters mounted on the heat sink base of the frame, to which the rods of the upper end of the frame are connected, and each autonomous photo-emitting panel consists of a frame in the form of a hexagonal prism made of carbon fiber with a heat-removing base and an upper end made in the form of a mesh-rod structure, in the cells of which are mounted Fresnel lenses and rods of which are connected to a heat sink system of photoconverters coaxial with Fresnel lenses, wherein said heat sink system is the net-rod structure made of carbon fiber with an admixture of silicon carbide in an amount of 20% -25%, on the nodes of which there are photoconverters, between which a layer of heat-insulating material is laid, and the rods of this design, mounted on nodes on the opposite side of the grid, are connected to the heat sink base of the frame in addition, inside the frame on its base, a control unit for a photo-emitting panel with a transmitting and receiving antenna is mounted, a device for converting electric energy into light energy in the form of a fiber laser lasers with pumping units, a laser radiation adder and energy storage devices, while the photoconverters are electrically connected to the pumping unit and the control unit via energy storage devices, in addition, the remote energy transmission device is also equipped with a laser radiation adder, and the adders of each photo-emitting panel are connected to the system adder remote transmission of energy via fiber optic cable, with the specified adder directed to the mirror system, and the control system of the base module I includes a radio transmitter for controlling the operation of autonomous photo-emitting panels and a transmitting and receiving antenna for communication with the ground segment. 2. Solar space power plant according to claim 1, characterized in that the frames of the photo-emitting and photoelectric panels are interconnected by means of metal drives with memory. 3. A stand-alone photo-emitting panel consisting of a frame with a base, a device for converting solar energy into electrical energy and a control unit mounted inside the frame on its base, a device for converting electrical energy into light energy and energy storage devices connected to these devices and a control unit, characterized in that a device for converting solar energy into electrical energy is mounted inside the frame, in its upper part, separated from the lower part by a layer of thermal insulation and is a photovoltaic battery made in the form of a set of Fresnel lenses and photoconverters located in their foci with a heat sink system, while the base of the frame is made of heat and connected to the heat sink of the photoconverters, the device converting electrical energy into light is a fiber laser with pump units and a laser radiation adder, while the photoconverters located in the upper part of the frame are electrically connected through energy stores installed on t plootvodyaschem base with pumping fiber lasers and blocks fotoizluchayuschey panel control unit which includes a receiving-transmitting antenna. 4. The stand-alone photo-emitting panel according to claim 3, characterized in that the heat transfer system of the photoconverters is a mesh-rod structure made of carbon fiber with an admixture of silicon carbide in an amount of 20-25%, on the grid nodes of which photoconverters are mounted, and the rods mounted on the nodes with opposite side of the grid, connected to the heat sink base of the frame. 5. The stand-alone photo-emitting panel according to claim 3, characterized in that the frame is made in the form of a hexagonal prism made of carbon fiber, the upper end of which is a mesh-rod structure, in the cells of which Fresnel lenses are located, and the rods are connected to the photoconverter heat sink system. 6. The stand-alone photo-emitting panel according to claim 3, characterized in that the photoelectric converters are heterostructured solar cells. 7. The stand-alone photo-emitting panel according to claim 3, characterized in that the energy storage devices are made in the form of supercapacitors.

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