RU2094949C1 - Method and device for lunar space power supply - Google Patents

Abstract

FIELD: power supply by means of space lunar power antenna in the form of multibeam active phased antenna array radiating microwave energy obtained by conversion of energy from solar batteries. SUBSTANCE: according to invention, lunar power transmitting antenna is divided into two separate parts. One of them is used to transmit microwave energy to ground receiving power stations (rectennas) installed on Earth's side invisible from Moon and other part is used to transmit microwave energy to space near-earth orbital secondary reflector to be transmitted from them due to secondary reflection to ground receiving power stations (rectennas) installed on Earth's side invisible from Moon. EFFECT: provision for compatibility of rectennas mounted on Earth's sides visible and invisible from Moon as well as between them and space solar-electric power stations of earlier design as far as their dimensions are concerned; reduced size of near-earth space orbital secondary reflectors retaining high efficiency of microwave energy transmission from Moon to ground and near-earth space power consumers, simplified functioning and phasing procedures, reduced scanning angles of two newly introduced parts of common lunar power antenna. 2 cl, 3 dwg

Description

 The invention relates to solar space power systems and power plants (SCES), intended for power supply of ground consumers of electric energy from space and various space means and consumers located in near-Earth space.

 Known methods and means of space energy saving using SCES, for example [1 5] The disadvantages of these methods and tools currently include the huge technical difficulties of creating such SCES and placing them in low Earth orbit, since it requires the creation of new, more powerful than existing rockets -carriers for launching into the near-earth geostationary orbit a huge amount of cargo, up to several tens and hundreds of thousands of tons, for relatively short periods of time, as well as a large number of trans It is for carrying out assembly, installation, construction and maintenance, repair work, which in turn is associated with frequent launches of such heavy-duty rocket carriers for the frequent delivery of goods and people to orbits, and the deterioration of the already difficult environmental situation on Earth due to the destruction of ozone layer of the Earth’s atmosphere, burning of huge amounts of fuel in the first super-powerful stages of launch vehicles, additional severe pollution in connection with this of the Earth’s atmosphere.

 The closest in technical essence to the proposed method of lunar space energy supply and the means for its implementation is a US patent [5] according to which the Moon, being a natural satellite of the Earth, is a fairly large space platform suitable for hosting large solar energy and radio-frequency microwave systems significantly exceeding the power of SCES, and possessing at the same time huge mineral resources favorable as a result of open-pit mining at Moon for the production of such elements of energy objects as, for example, solar panels, solid-state and semiconductor generator and amplifier devices made of silicon, antennas and other structural elements from aluminum, various composite materials from silicon oxide, etc.

 The disadvantages of the known method [5] of lunar space power supply and means for its implementation include the incompatibility of the characteristic linear dimensions of receiving ground power stations (rectennes) operating in the direct mode of receiving microwave energy from a transmitting lunar energy antenna (PAR) located on the visible from the Moon side of the Earth, and in the mode of receiving microwave energy through space near-Earth orbital re-reflectors of microwave energy, i.e. rectennes located on the side of the Earth invisible from the Moon, as well as overestimated characteristic linear dimensions of space near-Earth orbital re-reflectors exceeding 1 km, underestimated rectennes, which, as indicated in the patent [5], amount to about 400 m and low microwave transmission efficiency -energy from the Moon to terrestrial and near-Earth space energy consumers.

 Therefore, the aim of the invention is to ensure compatibility of the characteristic sizes of receiving ground power stations (recten) operating in the mode of direct reception of microwave energy from a transmitting lunar energy antenna (PAR) and in the mode of receiving microwave energy through space near-Earth orbital re-reflectors, and reducing the characteristic size of space near-Earth reflectors while maintaining high efficiency of microwave energy transmission from the Moon to terrestrial and near-Earth space energy consumers.

 This goal is achieved by the fact that according to the proposed method of lunar space energy saving at each lunar energy station (base) located on the surface of the western and eastern extremities of the moon’s side visible from the Earth, during periods of lunar days, solar radiation is accumulated and concentrated using each array of surface-type collectors energy, converting it in each grid of solar cells into energy of direct or alternating current of low frequencies, convert this energy into C The RF energy in each ensemble of microwave energy transmitters emit it in the form of a plurality of generated composite microwave energy rays using each one transmitting lunar energy antenna such as a multi-beam active phased array antenna (PAR) of the modules emitting for each one microwave energy beam in the direction of each of the receiving ground-based energy stations (rectennes) located on the side of the Earth visible from the Moon, and for each one microwave energy beam in the direction of each of the space circuits of terrestrial orbital re-reflectors of microwave energy, with the help of which they reflect microwave energy to receiving ground power stations (rectenes) located on the side of the Earth invisible from the Moon, convert microwave energy received by rectenes into low-frequency direct or alternating current energy and transmit it to consumers, at the same time, to obtain the phasing of microwave energy rays from each of the PAR modules at receiving ground power stations (rectennes) located on the Earth’s side visible from the Moon, and space the collozemic orbital re-reflectors of microwave energy in the direction to each of the PAR modules emit pilot signals from the receiving ground power stations (rectenn) located on the visible side of the Earth from the Moon and from the space near-earth orbital re-reflectors, along which all the phased array modules are phased, the phasing of energy microwave rays from each of the modules of space near-Earth orbital re-reflectors of microwave energy at receiving ground-based energy stations (rectennes) located on an invisible The Moon’s side of the Earth, in the direction of each of the modules of the space near-Earth orbital re-reflectors, emits pilot signals from the receiving ground power stations (rectenn) located on the side of the Earth that is invisible from the Moon.

 Significant differences of the proposed method are that to ensure compatibility of the characteristic sizes of the receiving ground power stations / recten / operating in the mode of direct reception of microwave energy from the transmitting lunar energy antenna / headlight / and the mode of operation / reception of microwave radiation / through space near-Earth orbital reflectors and reduction of the characteristic size of space near-Earth orbital deflectors while maintaining high efficiency of the transfer of microwave energy from the moon to the ground near-Earth space energy consumers: at each lunar energy station / base / located within the side visible from the Earth / hemisphere / Moon, direct microwave energy is transmitted to receiving ground-based power stations / rectennes / located on the side of the Earth visible from the Moon, from a separate transmitting lunar antenna (PAR), which is a separate part of the common transmitting lunar energy antenna (PAR), the transfer of microwave energy to space near-Earth orbital re-reflectors is carried out from the entire at the same time, at each lunar transmitting energy station (base) located within the visible side of the moon (hemisphere) of the Moon during periods of lunar days using each additionally introduced array of surface-type collectors accumulate and concentrate solar radiation energy, including reflected solar energy from near-moon solar orbital reflectors, transform it in each additionally introduced grid solar batteries into energy of direct or alternating current of low frequencies, convert this energy in the ensemble of transmitters into microwave energy and bring it to a separately introduced transmitting lunar energy antenna (PAR), which is a separate part of the common lunar energy antenna (PAR), for microwave radiation energy in the form of a set of generated composite microwave energy rays for each one microwave energy beam in the direction of each of the receiving ground-based energy stations (rectennes) located on the visible from the Moon to the Earth’s side, and to obtain the phasing of microwave rays from each of the modules of the introduced separate part of the transmitting lunar energy antenna (PAR) at the receiving ground power stations (rectennes) located on the Earth’s side visible from the Moon, towards each of the modules of the introduced separate part transmitting lunar energy antenna (PAR), emit pilot signals from receiving ground power stations (rectenn) located on the visible side of the Earth from the Moon, to obtain the phasing of microwave rays from to zhdogo module entered the rest of the Moon's transmit power antenna (PAR) on Earth orbital space pereotrazhatelyah, towards each of the rest of the modules introduced lunar energy transmitting antenna (PAR) emit pilot signals from Earth orbital space pereotrazhateley.

 Means for implementing the method of lunar space power supply contain on each lunar energy station (base) located on the surface of the western and eastern extremities of the moon side (hemisphere) visible from the Earth, a grid of surface-type collectors for the accumulation and concentration of solar radiation energy, a grid of solar batteries, connected to a grid of surface-type collectors to convert solar radiation energy into direct or alternating current energy of low The frequency of connected energy to direct or alternating current energy of low frequencies, an ensemble of microwave transmitters connected to a solar array to convert the energy of direct or alternating current of low frequencies to microwave microwave energy, connected to an ensemble of transmitters of microwave energy, one transmitting lunar energy antenna of a type of multipath active phased array antenna (PAR) of the modules for emitting by it in the form of a plurality of generated composite energy microwave beams for each one near the energy ray in the direction of each of the receiving ground-based energy stations (rectennes) located on the side of the Earth visible from the Moon and for each one microwave energy beam in the direction of each of the space near-Earth orbital re-reflectors of microwave energy, with which microwave energy is reflected to receiving ground power stations (rectennes) located on the side of the Earth invisible from the Moon to convert microwave energy into direct or alternating current energy of low frequencies and supply it to the consumer m, a system (lattice) for controlling the guidance, tracking and phasing of each module of the transmitting lunar energy antenna (PAR) and, accordingly, each microwave energy beam directed to receiving ground power stations (rectenes) located on the Earth’s side visible from the Moon, and to space near-Earth orbital re-reflectors, and each microwave energy ray reflected by the corresponding space near-Earth orbital re-reflector to the corresponding receiving ground-based energy an antenna (rectenna) located on the side of the Earth that is invisible from the Moon, with sources of pilot signals for phasing all the PAR modules from the pilot signals emitted to the PAR modules from receiving ground power stations (recten) located on the side of the Earth visible from the Moon and from space near-Earth orbital re-reflectors, and sources of pilot signals for phasing all modules of space near-Earth orbital re-reflectors based on pilot signals emitted from receiving ground power stations (recten) x on the side of the Earth invisible from the Moon, to the modules of space near-Earth orbital re-reflectors.

 Significant differences in the means for implementing the proposed method of lunar space energy saving are that to ensure compatibility of the characteristic sizes of the receiving ground power stations (rectenn) located on the visible side of the Earth from the moon, and the receiving ground power stations (rectenn) located on the invisible from the Moon side of the Earth, and reducing the characteristic dimensions of space near-Earth orbital re-reflectors of microwave energy while maintaining high transmission efficiency of the microwave energy gii from the Moon to terrestrial and near-Earth space energy consumers, at each lunar energy station (base) located within the visible side (hemisphere) of the Moon from the Earth, for transmitting microwave energy to receiving terrestrial energy stations (rectennes) located at visible Moon side of the Earth, introduced a separate transmitting lunar energy antenna (PAR), which is a separate part of the common transmitting lunar energy antenna (PAR), the rest is a separate part of the common transmitting moon energy antenna (PAR) unit for transferring microwave energy to space near-Earth orbital re-reflectors and its reflection to receiving ground power stations (rectennes) located on the invisible side of the Earth from the Moon, while an additional array of surface-type collectors is introduced for additional accumulation and concentration of solar radiation energy, in tons h. and reflected solar radiation energy from the lunar solar orbital re-reflectors, introduced connected to an additionally introduced array of collectors The surface type is an additional solar array for converting solar radiation energy into direct or alternating current energy of low frequencies, connected to an ensemble of transmitters for converting this energy into microwave energy, connected to a separate, additionally introduced part of a common transmitting lunar energy antenna (PAR), for radiation of microwave energy in the form of a plurality of composite microwave energy rays for each one energy beam in the direction of each one of the receiving ground-based energies stations (rectennas) located on the visible side of the Earth from the Moon, and sources of pilot signals were introduced at receiving ground power stations (rectennas) located on the visible side of the Earth from the Moon for phasing all the modules of a separate introduced transmitting lunar energy antenna (PAR) , which is a separate part of the common transmitting lunar energy antenna (PAR), and the sources of pilot signals have been introduced on space near-Earth orbital re-reflectors for phasing all the modules of the remaining separate the introduced part of the transmitting lunar energy antenna (PAR).

 In FIG. 1 shows a schematic representation of the relative position of the lunar energy station (LES) relative to the receiving ground power stations (rectenn) located on the visible and invisible sides of the Earth from the moon, and space near-Earth orbital re-reflectors (COS) of microwave energy; figure 2 generalized functional diagram of the lunar energy station (LES); figure 3 is a schematic representation of the relative position of the lunar energy stations (LES) located on the western and eastern extremities of the side (hemisphere) of the moon respectively visible to the Earth relative to the receiving ground power stations (recten) (NER) located on the sides visible and invisible from the Moon Earth, and space near-Earth orbital re-reflectors (CPO) of microwave energy.

 Means for implementing the proposed method of lunar space power supply at each lunar (transmitting) power station (LES) 1 and 2 / cm 1-3 / located on the surface of the western and eastern ends of the Moon 4 side visible from Earth 3, respectively, include a surface-type array of collectors 5 for the accumulation and concentration of solar radiation energy, including reflected solar radiation energy from near-moon orbital re-reflectors 6.7 located in the lunar orbit 8.

In the simplest case, the lattice of collectors 5 of the surface type is a lattice of flat traps of solar energy without its concentration. In focusing collectors, solar energy is concentrated, i.e. increases in density of the incoming radiation flux. The most common type of collector is a flat solar energy collector (SSC), characterized by a low concentration coefficient K _e , being a low-potential solar energy concentrator. The concentration coefficient of solar energy (degree of concentration or concentrating ability) is defined as the ratio of the average density of concentrated radiation to the density of the radiant flux incident on the reflective surface provided that the latter is accurately oriented to the Sun [2] Low-potential concentrators (collectors) (K _e ≅100) of solar radiation can be of two types with a curved or rectangular generatrix of the reflective surface. Conventional concentrators of the first type are parabolic cylinders, which provide K _e 20 40. Conical and wedge-shaped concentrators are attractive for use on the Moon, which can be structurally combined with converting devices and allow the use of both direct and reflected solar radiation. Such reflectors with a parabolic generatrix are called focons (focusing cone) and foclines (focusing wedge) [7] Focons and foclins with a parabolic generatrix have two positive properties: they do not require high precision manufacturing of the reflector’s surface and, what is especially important, maintain the initial level radiation concentration at low accuracy of the orientation of the axis of the reflector on the Sun. Under stationary conditions on the moon, they can work efficiently, remaining stationary for a long time in relation to the sun. This determines the feasibility of using stationary solar power stations located on the moon, where the inclination of the equatorial plane to the ecliptic plane is small. Focusing collectors have a high degree of concentration (high K _e ). In the context of the widespread use of semiconductor, for example, silicon photovoltaic solar cell converters, low levels of solar radiation concentration are appropriate, and therefore a surface array of collector arrays 5 is applicable. The array of solar panels 10 is connected to the array of collectors 9 of the surface type and is used to convert solar radiation energy into direct or alternating current energy; the array of transmitters of microwave energy 11 connected to the array of solar panels 10 is used to convert low-frequency direct or alternating current energy to microwave microwave energy. The ensemble of transmitters 11 is a combination of master oscillators and microwave amplifiers. The most promising are converters on semiconductor microwave devices. In semiconductor microwave devices, the conversion of low-frequency direct or alternating current energy to microwave energy occurs in a solid, the mass and dimensions of which are usually small, and the physical properties are very sensitive to temperature and current parameters. This limits the power of semiconductor devices to values of the order of units, tens of V, their permissible operating temperature does not exceed 200 ^o , and the DC voltage of tens of watts. Despite the fact that devices of this class are sensitive to the effects of operational factors in comparison with electric vacuum devices, they are gaining wider development and application in microwave technology and represent a serious alternative to high-power electric vacuum devices for use in space energy. This is due to their important advantages such as high reliability and durability, compactness, relatively low cost in mass production, ease of assembly and, most importantly, good compatibility with semiconductor photovoltaic converters of solar batteries, the possibility of widespread use of new technologies for manufacturing in the form of integrated circuits large integrated circuits (LSI). Since the basis of the array of solar cells is the array of photovoltaic converters for converting solar energy into electrical energy by semiconductor photoelectric converters (PECs), it becomes possible to constructively combine the array of solar cells 10 with semiconductor integrated photoconverters with the array of integrated semiconductor energy converters of direct or alternating current low-frequency energy in microwave the energy of the microwave array of the transmitters 11. This allows you to apply sandwich type construction and minimize energy loss when transferring it from a direct current source (solar battery) 10 to the microwave devices of the transmitter array 11. Since the efficiency of two energy conversions: solar energy into direct current (variable low frequency) current and the last energy in microwave energy is accompanied by heat loss, then to protect against overheating of the semiconductor elements of solar cells 10 and microwave transistors of the array of transmitters 11, a refrigerator emitter 12 is introduced between them. of the active area of solar panels, an additional array of solar panels 13 was introduced. An transmitting lunar energy antenna 15 of the type of multi-beam active phased array antenna (PAR) of the modules 16 (with semiconductor vibrators) is connected to the transmitter assembly 11 (grating) of the phase shifters 14 (control system (grating)) sprayed onto the plane of collectors 9 (surface type) for emitting by it in the form of a plurality of generated composite microwave energy rays for each single microwave energy beam, for example 17, 18, in the direction of each of the receiving ground power stations (rectenn), for example 19, located on the 20 side of Earth 3 visible from the Moon 4, and for each one microwave energy beam, for example 21, 22, in the direction of each of the space near-Earth orbital rereflectors, for example 23, 24 microwave energy, with which microwave energy is reflected to receiving ground power stations (rectenes), for example 25, 26, located on the invisible side of the Moon 4 from the Moon 4 of Earth 3 to convert the received microwave energy into constant energy about or alternating current of low frequencies and supplying it to consumers, a control grid (lattice of phase shifters 14 with adaptive processor computing means) by pointing, tracking and phasing each of the modules 16 of the transmitting lunar energy antenna 15 and, accordingly, of each microwave energy beam directed to the receiving ground energy stations (rectenn), for example 19, located on the 20 side of Earth 3 visible from the Moon 4, and on space near-Earth orbital re-reflectors, for example 23, 24, and each energy A microwave microwave beam reflected by the corresponding space near-Earth orbital re-reflectors, for example 23, 24, to the corresponding receiving ground power stations (rectenes), for example 25, 26, located on the 27 side of the Earth 3, invisible from the Moon 4, with sources of pilot signals for phasing of all PAR modules 15 according to the pilot signals emitted to the PAR modules from receiving ground power stations (rectenn), for example 19, located on the 20 side of Earth 3 visible from the Moon 4, and from space near-Earth orbital reflector lei, for example, 23, 24, and sources of pilot signals for phasing all the modules of space near-Earth orbital re-reflectors by pilot signals emitted from receiving ground power stations (rectenn), for example 25, 26, located on the side 27 of the Earth invisible from the Moon 4 3 , to the modules of space near-Earth orbital re-reflectors, for example 23, 24.

 Significant features of the means for implementing the proposed method of lunar space power supply are that, to ensure compatibility of the characteristic sizes of the receiving ground power stations (rectenn), for example 19, located on the 20 side of the Earth 3 visible from the Moon 4, and the receiving ground power stations (recten) , for example 25, 26, located on the invisible side of the Moon 4 from the side 27 of Earth 3, and the reduction in the characteristic size of space near-Earth orbital re-reflectors, for example 23, 24, while maintaining high efficiency of transmitting microwave energy from the moon to terrestrial and near-Earth space energy consumers, at each lunar energy station (base), for example 1, 2, located within the visible side (hemisphere) of the moon 4 from the Earth, for transmitting microwave energy to receiving ground power stations (rectennam), for example 19, located on the 20 side of Earth 3 visible from the Moon 4, introduced a separate transmitting lunar antenna (PAR) 28, which is a separate part of the common transmitting moon energy antenna (PAR) 15, the rest is a separate part A general transmitting lunar energy antenna (PAR) 15 is introduced for transmitting microwave energy to space near-Earth orbital re-reflectors, for example 23, 24, and for re-reflecting microwave energy to receiving ground power stations (rectennes), for example 25, 26, located on the invisible from the Moon 4 to the side 27 of Earth 3, while an additional array of surface-type collectors 9 was introduced for additional accumulation and concentration of solar radiation energy, including reflected solar radiation energy from near-moon solar orbits total reflectors 6, 7, an additional solar array 13 connected to an additional array of surface-mounted collectors 9 is introduced to convert solar radiation energy into direct or alternating current energy of low frequencies, connected to an ensemble of transmitters 11 for converting this energy into microwave energy connected with a separate additionally introduced transmitting lunar energy antenna (PAR), which is a separate introduced part of the common transmitting lunar energy antenna s (PAR), for the emission of microwave energy for each one microwave energy beam in the direction of each one of the receiving ground power stations (rectenn), for example 19, located on the 20 side of Earth 3 visible from the Moon 4, and a source of pilot signals has been introduced at receiving ground power stations (rectennas), for example 19, located on the 20 side of the Earth 3 visible from the Moon 4, for phasing all the modules of the separate introduced transmitting lunar energy antenna (PAR) 28, which is a separate introduced part of the common transmitting lunar th energy antenna (PAR) 15, and the sources of pilot signals were introduced on space near-Earth orbital re-reflectors, for example 23, 24, for phasing all the modules of the remaining separate introduced part of the common transmitting moon energy antenna (PAR) for microwave radiation in the form of many composite microwave energy rays for each one microwave energy beam emitted in the direction of each of the space near-Earth orbital re-reflectors, for example 23, 24.

 The principle of operation of the means for implementing the proposed method of lunar space energy supply is that at each lunar energy station (base) 1, 2 located on the surface of the western and eastern extremities of the sides of the Moon 4 visible from Earth 3, respectively, during lunar days using each gratings of collectors 5 of the surface type accumulate and concentrate solar radiation energy, convert it in each grating of solar cells 10 into direct or alternating current energy of low frequencies, pre generate this energy into microwave microwave energy in each ensemble of microwave energy transmitters 11, radiate it in the form of a plurality of generated composite microwave energy rays using each one transmitting lunar energy antenna 15 of the type of multi-beam active phased array antenna (PAR) of the modules 16 emitting for each one microwave energy beam, for example 17, 18, in the direction of each of the receiving ground power stations (recten), for example 19, located on the 20 side of Earth 3 visible from the Moon 4, and for each one microwave energy beam, for example 21, 22, in the direction of each of the space near-Earth orbital re-reflectors, for example 23, 24, microwave energy, with which microwave energy is reflected to receiving ground power stations (rectenes), for example 25, 26, located on the invisible side of the Moon 4 from the Moon 4 of the Earth 3, they convert the microwave energy received by the rectennes into low-frequency direct or alternating current energy and transmit it to consumers, in order to obtain the phasing of microwave energy rays, for example 17, 21 (Fig. 1), from each of the PAR modules at receiving power ground stations (rectennes), for example 19, located on the 20 side of Earth 3 visible from the Moon 4, and space near-Earth orbital re-reflectors, for example 23, 24, microwave energy in the direction to each of modules 16 of the HEADLIGHT 15 emit pilot signals from receiving ground power stations (rectenn), for example 19, located on the 20 side of Earth 3 visible from the Moon 4, and from space near-Earth orbital re-reflectors, for example 23, 24, along which all the HEADLAY modules are phased, for sphazirs of microwave energy rays from each of the modules of space near-Earth orbital re-reflectors, for example 23, 24, microwave energy at receiving ground power stations (rectennes), for example 25, 26, located on the invisible side of the Moon 4 from side 4 of Earth 3, in the direction each of the modules of space near-Earth orbital re-reflectors, for example 23, 24, is emitted by pilot signals from receiving ground power stations (recten), for example 25, 26, located on side 27 of Earth 3, invisible from the Moon 4.

 Significant differences of the proposed method of lunar space power supply are that to ensure compatibility of the characteristic sizes of the receiving ground power stations (rectenn), for example 19, operating in the mode of direct reception of microwave energy from the transmitting lunar energy antenna (PAR) 15 and the operating mode (reception Microwave energy) of receiving ground power stations (rectenn), for example 25, 26, through space near-Earth orbital re-reflectors, for example 23, 24, and reduction of the characteristic size of near-Earth orbital re-reflectors, for example 23, 24, while maintaining high efficiency of microwave energy transfer from Moon 4 to terrestrial and near-Earth space energy consumers, at each lunar energy station (base), for example 1, 2, located within the limits of visible from Earth 3 side (hemisphere) of the Moon 4, direct transfer of microwave energy to receiving ground power stations (rectennes), for example 19, located on the 20 side of Earth 3 visible from the Moon 4, is carried out from a separate transmitting lunar energy antenna (PAR) 28, which is 0 separate part of the common transmitting lunar energy antenna 15, microwave energy is transmitted to space near-Earth orbital re-reflectors, for example 23, 24, from the rest of the entered individual part of the common transmitting lunar energy antenna (PAR) 15, at the same time, at each lunar energy station (base) 1, 2, located within the boundaries of the moon 4 visible from the Earth 3, during lunar days using each additionally introduced array of surface collectors 9 und accumulate and concentrated solar radiation energy, including and reflected solar radiation energy from near-moon solar orbital reflectors, for example 6, 7, convert it in each additionally introduced array of solar cells 13 into direct or alternating current energy of low frequencies, convert this energy in the ensemble of transmitters 11 into microwave energy and bring it to a separate input transmitting lunar energy antenna (PAR) 28, which is a separate input part of a common lunar energy antenna (PAR) 15, for radiating microwave energy in the form of a plurality of generated positional microwave energy rays, for example 17, 18, for each one microwave energy beam, for example 17, 18, in the direction of each one of the receiving ground power stations (rectennes) located on the 20 side of Earth 3 visible from the Moon 4, and for obtaining the phasing of microwave rays, for example 17, 21, from each of the modules of the introduced separate part of the transmitting lunar energy antenna (PAR) 28 at the receiving ground power stations (rectennes), for example 19, located on the 20 Earth 3 side visible from the Moon 4, in direction to each Pilot signals from receiving ground power stations (rectenn), for example 19, located on the 20 side of Earth 3 visible from the Moon 4, emit from the modules of the introduced separate part of the transmitting lunar energy antenna (PAR) 28 to obtain the phasing of microwave rays from each of modules of the introduced remaining separate transmitting lunar energy antenna (PAR) on space near-Earth orbital re-reflectors, for example 23, 24, in the direction to each of the modules of the introduced remaining separate lunar transmitting energetic Coy antenna (PAR) 15 emit pilot signals from Earth orbital space pereotrazhateley, e.g. 23, 24.

 By a composite (complex) energy microwave beam is meant a microwave beam formed by a plurality of microwave rays, for example 21 (Fig. 1), from each of the modules 16 of the active phased array antenna (PAR) 15 of the modules 16, i.e. each of the microwave energy rays of the radiation pattern of the multipath active phased array antenna (PAR) of the modules 16, for radiation either in the direction of each receiving ground power station (rectenna), for example 19, or in the direction of the space near-Earth orbital re-reflector, for example 23 or 24 .

где l_фар, l_коп, l_нэр характерные размеры соответственно передающей лунной энергетической антенны (ФАР), например 15, космического околоземного орбитального переотражателя (КОП), например 23, и наземной энергетической ректенны (НЭР) (станции), например 19 и 25;
τ₁, τ₂, τ₃ - волновые коэффициенты передачи СВЧ-энергии соответствующих апертурных пар: КОП и НЭР, ФАР и НЭР, ФАР и КОП, изменяющиеся, например, в пределах τ 1 3 и определяющие КПД передачи СВЧ-энергии этих апертурных пар, соответственно в пределах h 0,6 1,0;
L₁ 36000 км среднее расстояние между КОП и НЭР при расположении КОП на геостационарной (геосинхронной) орбите;
L₂ 360000 км среднее расстояние между ФАР и НЭР, определяемое по среднему расстоянию Земля Луна;
L₃ 400000 км среднее расстояние между ФАР и КОП;
l длина волны СВЧ-излучения.Using examples of specific calculations, we prove the essence of the proposed method of lunar space power supply. For the generalized lunar energy system shown in figure 3, a system of the following three equations is characteristic:

where l _headlight , l _cop , l _{ner are the} characteristic sizes of the respectively transmitting lunar energy antenna (PAR), for example 15, the space near-Earth orbital re-reflector (CPC), for example 23, and the ground energy rectenna (NER) (stations), for example 19 and 25;
τ ₁ , τ ₂ , τ ₃ - wave transmission coefficients of microwave energy of the corresponding aperture pairs: CPC and NER, PAR and NER, PAR and CPC, changing, for example, within τ 1 3 and determining the transmission efficiency of microwave energy of these aperture pairs , respectively, in the range of h 0.6 1.0;
L ₁ 36000 km the average distance between the CPC and the NER at the location of the CPC in geostationary (geosynchronous) orbit;
L ₂ 360000 km average distance between the PAR and NER, determined by the average distance of the Earth Moon;
L ₃ 400000 km average distance between the PAR and CPC;
l wavelength of microwave radiation.

The solution of the system of equations (1), for example, at L ₂ L ₃ 400,000 km with respect to the characteristic dimensions gives their following values: at τ = 1.4
l _headlamp 26.2 km, l _cop 2.62 km, l _ner 2.62 km, λ = 12.25 cm, η = 0.8.
l _headlamp 23.6 km, l _cop 2.36 km, l _ner 2.36 km, λ = 10 cm, η = 0.8.
l _headlamp 17.1 km, l _cop 1.71 km, l _ner 1.71 km, λ = 5.2 cm, η = 0.8.
Higher values of τ ≥ 1.4 / η ≥ 0.8 / give higher values of the characteristic sizes.

At present, it is considered impractical to choose the characteristic size of the space reflector more than one km, i.e. l _kop ≅1 km should be due to its complex feasibility in a geostationary orbit, the difficulty of controlling it and stabilizing its position in a non-geostationary orbit, as well as for other specific reasons. Therefore, we choose a fixed value of the characteristic size of the space orbital reflector l $\genfrac{}{}{0ex}{}{\text{fix}}{\text{cop}}$ equal, for example 1 km.

Из второго уравнения системы уравнения (1) с учетом (2) величина

И, наконец, из третьего уравнения системы уравнений (1) с учетом (2)

При фиксированной величине l $\genfrac{}{}{0ex}{}{\text{abrc}}{\text{коп}}$ = 1,0 км технически обоснованной величине для реализации, величина характерного размера ректенн численно равна эффективной площади S_эф.1
l_нэр = τ₁•λ•L₁ = S_эф.1
А величина

При этом l_фар = τ₃•λ•L₃ = S_эф.3 численно равна эффективной площади S_эф.з в (км).From the first equation of system (1), the characteristic rectenne size is determined as

From the second equation of the system of equation (1), taking into account (2), the quantity

And finally, from the third equation of the system of equations (1), taking into account (2)

For a fixed value of l $\genfrac{}{}{0ex}{}{\text{abrc}}{\text{cop}}$ = 1.0 km of a technically sound value for implementation, the value of the characteristic rectennal size is numerically equal to the effective area S _eff.
l _ner = τ ₁ • λ • L ₁ = S _{eff. 1}
And the value

Moreover, l _headlights = τ ₃ • λ • L ₃ = S _{eff. 3 is} numerically equal to the effective area S _eff. S in (km).

10 км составляет только часть от l_фар порядка 10 20% на самых благоприятных длинах волн (λ 12,25 см и 10 см), являясь характерным размером введенной части передающей лунной энергетической антенны (ФАР) 28 для передачи СВЧ -энергии к приемным наземным энергетическим станциям (ректеннам), например 19, расположенным на видимой с Луны 4 стороне 20 Земли 3. От всей остальной введенной части с характерным размером l_фар общей передающей лунной энергетической антенны (ФАР) 15 производят передачу СВЧ-энергии к космическим околоземным орбитальным переотражателям, например 23,24, с сокращенным характерным размером l_коп 1 км, с помощью которых переотражают СВЧ-энергию с высокой эффективностью (h 0,95 при t 2,0) на приемные наземные энергетические станции (ректенны), например 25,26, расположенные на невидимой с Луны 4 стороне 27 Земли 3.Estimates of the characteristic sizes at τ ₁ = τ ₂ = τ ₃ = τ and l $\genfrac{}{}{0ex}{}{\text{fix}}{\text{cop}}$ = 1 km give the following values
l _headlight 68.6 km, l _cop 1 km, l _ner 6.2 km, λ = 12.25 cm, τ = 1.4 / η = 0.8 /
l _headlight 56 km, l _cop 1 km, l _ner 5.04 km, λ = 10 cm, τ = 1.4 / η = 0.8 /
l _headlight 29 km, l _cop 1 km, l _ner 2.62 km, λ = 5.2 cm, τ = 1.4 / η = 0.8 /
l _headlight 98 km, l _cop 1 km, l _ner 8.8 km, λ = 12.25 cm, τ = 2 / η = 0.95 /
l _headlight 80 km, l _cop 1 km, l _ner 7.2 km, λ = 10 cm, τ = 2 / η = 0.95 /
l _headlight 41.6 km, l _cop 1 km, l _ner 3.7 km, λ = 5.2 cm, τ = 2 / η = 0.95 /
From a comparison of the presented results it follows that

10 km is only a fraction of l _{headlights of the} order of 10 20% at the most favorable wavelengths (λ 12.25 cm and 10 cm), being the characteristic size of the introduced part of the transmitting lunar energy antenna (PAR) 28 for transmitting microwave energy to receiving ground energy stations (rectenna) for example 19 disposed on the visible side of the moon 20 4 Earth 3. from the rest of the introduced part with a typical size _range l lunar common transmitting antenna power (PAR) 15 transmits microwave energy to Earth orbital space pereotrazhatelya For example 23,24, with reduced characteristic dimension l _cop 1 km, whereby pereotrazhayut microwave energy with high efficiency (h 0,95 at t 2,0) for receiving ground station energy (rectenna), for example 25.26, located on the invisible from the Moon 4 side 27 of Earth 3.

передачи СВЧ энергии с Луны к наземным и околоземным космическим потребителям энергии.The separation of the common transmitting lunar energy antenna (PAR) 15 into two separate parts 28 and 15 (i.e., the separation from the common lunar antenna 15 of a separate much smaller part 28) ensures their independent independent work on rectennes, for example 19, located on the visible from the Moon 4 side 20 of Earth 3, and on space near-Earth orbital re-reflectors, for example 23.24, for transferring microwave energy to receiving ground power stations (rectennes), for example 25.26, located on the invisible from the Moon 4 side 27 of Earth 3, which ensures fasting achievement The goal of compatibility of the characteristic sizes of receiving ground power stations (rectennas) located both on the visible and invisible from the Moon 4 sides 20 and 27 of Earth 3 allows us to reduce (reduce) the characteristic size of space near-Earth orbital re-reflectors, for example, 23.24, to technically acceptable for the implementation of the values of l _kop 1 km while maintaining high efficiency

transmission of microwave energy from the moon to terrestrial and near-Earth space energy consumers.

 The separation of the common transmitting lunar energy antenna (PAR) into two separate independent parts ensures their independent functioning and the convenience of independent phasing, as well as a significant reduction in the scan angles of two separate parts of the common transmitting lunar energetic antenna (PAR). In addition, the compatibility of the characteristic sizes of receiving ground power stations (rectenn) with the sizes in previously developed projects of solar space power stations (SCES), which are supposed to be put into geostationary orbit, is ensured. Due to the limited size of the introduced separate transmitting lunar energy antenna (PAR) 28 compared to the rest of the total transmitting lunar energy antenna for aligning the levels of radiated microwave energy by the introduced individual parts of the common PAR in each lunar power station, for example 1,2, an additional collector array surface type for additional accumulation and concentration of solar radiation energy and connected with it introduced an additional array of solar panels for work s with an additionally introduced separate part of the common transmitting lunar energy antenna, designed to transmit microwave energy to ground-based rectennes on the Earth's side visible from the Moon. In this case, the lattices of solar panels, along with other lattices, can be installed directly on the lunar surface: either mounted vertically (normally) to the surface of the Moon (Fig. 1), or installed in the echelon of the lattices.

Sources of information
1. Vanke V.A. Leskov L.V. Lukyanov A.V. Space power systems, - M. Mechanical Engineering, 1990, 144 p.

 2. Griliches V. A. Solar space power stations, L. Nauka, 1986, 181 pp.

 3. US patent N 3781647, 12/23/73.

 4. Copyright certificate of the USSR N 946372, publ. in B.I. N 3, 1983.

 5. US patent N 5019768, NKI 322-2R from 05/28/91. (prototype).

 6. Gostyukhin V.L. Trusov K.G. Klimachev Yu.S. Danich Yu.S. Active phased antenna arrays, M. Radio and Communications, 1993, 270 p.

 7. Baranov V. K. New radiation concentrators and prospects for their use in optics and solar technology, Proceedings of the Moscow State Optical Institute, 1979, issue 179, p. 57 70.

 8. Korolev E.F. Simulators for spacecraft control, abstract index, Status and development trends of radio engineering, ASNTI "Grid", subarray RS, M. 1985, NIIEIR.

Claims (2)

 1. The method of lunar space energy supply, which consists in the fact that at each lunar energy station located on the surface of the moon side visible from the Earth, including the western and eastern ends of the moon side visible from the Earth, respectively, during lunar days using each grating surface-type collectors accumulate and concentrate solar radiation energy, convert it in each grid of solar cells into direct or alternating current energy of low frequencies, convert this energy to high-frequency microwave energy in each ensemble of microwave energy transmitters, emit it in the form of a set of generated composite microwave energy rays using each one transmitting lunar energy antenna, made in the form of modules of a multi-beam active phased array antenna (MFAR), emitting for each one energy Microwave beam in the direction of each of the receiving ground power stations, made in the form of rectennes, located on the side of the Earth visible from the Moon, and for each one microwave beam in the direction of each of the space near-Earth orbital re-reflectors of microwave energy, with the help of which they reflect microwave energy to the rectenn located on the side of the Earth that is not visible from the moon, convert the microwave energy received by the rectenn into low-frequency direct or alternating current energy and transmit it to consumers of energy, while in order to obtain the phasing of energy microwave rays from each of the MFAR modules on rectennas located on the visible side of the Earth from the Moon, and space near-Earth orbital The microwave energy reflectors in the direction to each of the MFAR modules emit rectken pilot signals, along which all the MFAR modules are phased, to obtain the phasing of microwave energy rays from each of the modules of space near-Earth orbital microwave reflectors on rectennas located on an invisible from the Moon side of the Earth, in the direction of each of the modules of the space near-Earth orbital re-reflectors of microwave energy, emit pilot signals from rectennas located on the side of the Earth invisible from the Moon, which differs I mean that at each lunar energy station located within the visible side of the Moon, microwave energy is transmitted to rectenns located on the visible side of the Earth from the moon, from a separately introduced transmitting lunar antenna, made in the form of MFAR modules, which is the first a separate part of the common transmitting lunar energy antenna, the transfer of microwave energy to the space near-Earth orbital re-reflectors of microwave energy is produced from the second separate part of the common transmitting lunar energy antenna for the transfer of microwave energy to the rectenna located on the side of the Earth not visible from the Moon, while on each transmitting lunar power station located within the visible side of the Moon, during the days of lunar days, using each additionally introduced array of surface-type collectors, they accumulate and concentrate solar radiation energy, including reflected solar radiation energy from near-moon solar orbital re-reflectors, transform it in each additionally introduced solar array x batteries into energy of direct or alternating current of low frequencies, convert this energy in the ensemble of transmitters into microwave energy and bring it to a separately introduced transmitting lunar energy antenna, for emitting microwave energy in the form of a set of generated composite microwave energy rays for each one Microwave beam in the direction of each one of the rectennas located on the side of the Earth visible from the moon, and to obtain the phasing of microwave rays from each of the modules of the first separate part of the common transmitting to it of the lunar energy antenna on rectennas located on the Earth’s side visible from the Moon, in the direction to each of the modules of the first separate part of the transmitting lunar energy antenna, a pilot signal is emitted from the rectennas located on the Earth’s side visible from the Moon to obtain the microwave phasing from each of the modules of the second separate part of the transmitting lunar energy antenna on space near-Earth orbital re-reflectors, towards each of the modules of the second separate part of the transmitting lunar energy cal antennas emit pilot signals from Earth orbital space pereotrazhateley microwave energy.  2. A system of lunar space power supply, containing at each lunar power station located on the surface of the side of the Moon visible from the Earth, including the western and eastern ends of the side of the Moon visible from the Earth, respectively, a surface-type array of collectors for the accumulation and concentration of solar radiation energy, a grid of solar panels connected to a grid of collectors of a surface type for converting solar radiation energy into direct or alternating current energy of low of frequencies connected to the solar array, an ensemble of microwave energy transmitters for converting low-frequency direct or alternating current energy into microwave microwave energy connected to an ensemble of microwave energy transmitters, one transmitting lunar energy antenna made in the form of modules with a multipath active phased antenna lattice (MFAR), intended for radiation by it in the form of a plurality of generated composite microwave energy rays along one microwave energy beam in the direction of each of small energy stations made in the form of rectennes located on the side of the Earth visible from the Moon, and for each one microwave energy beam in the direction of each of the space near-Earth orbital re-reflectors of microwave energy, designed to re-reflect microwave energy to rectennes located on the invisible from the Moon to the Earth’s side, while the rectennas are connected to energy consumers, all MFAR modules of all lunar energy stations are connected to a guidance system for guidance, tracking and phasing of modules, and rectennas are connected to appropriate sources of pilot signals intended for phasing of all MFAR modules, characterized in that at each lunar power station located within the visible side of the Moon from the Earth and each lunar power station located within the invisible side of the Moon transmitting the lunar energy antenna is made in the form of the first separate part of a common transmitting lunar antenna for transmitting microwave energy to rectennes located on the side of the Earth visible from the moon and the second from a portion of a common transmitting lunar antenna for transmitting microwave energy to space near-Earth orbital re-reflectors of microwave energy, the first separate part of a common transmitting antenna through an appropriate ensemble of microwave energy transmitters being connected to an additional array of solar panels connected to an additionally introduced array of surface-type collectors.

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