Spacecraft and section of phased antenna array |
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IPC classes for russian patent Spacecraft and section of phased antenna array (RU 2333139):
                    
 Command control device for antenna array phase shifters / 2316854
Proposed device that can be used in electronically scanned arrays incorporating beam control and pattern-shaping systems, phasing system using command method for controlling ferrite phase shifters and polarization switches is designed for building multicomponent antenna assemblies characterized in high beam scanning speed at minimal number of control conductors in antenna assembly and in high operating reliability as well as for reducing array cost due to installation of ferrite phase shifters in array without their pre-selection and sorting-out with respect to phase-time and phase-temperature characteristics for further antenna-by-antenna individual tuning and channel calibration in assembled antenna array to minimize magnetization reversal in ferrite phase shifters and polarization switches by implementing algorithm of reset-pulse individual length adaptive generation including results of measuring magnetizing current pulse length of phase shifter (polarization switch) according to maximal cycle of hysteresis loop. Device has digital data processor unit incorporating random-access FLASH memory, built-in checkup system, circuit for limiting current maximum through power circuit of each current reset switch and installation, temperature senior, universal series channel interface, and through at least each array antenna being phased out, as well as for micro-miniaturization of the entire device to monolithic integrated circuit of SLSIC type built around system-on-chip base.
 Antenna system / 2273923
Proposed antenna system that can be used in many communication systems for transmitting and/or receiving at least two signals, first one of mentioned signals being generated in first-operator frequency band by first operator and second one of mentioned signal, in second-operator frequency band by second operator, has antenna assembly characterized in adjustable angle of inclination of optical axis that incorporates plurality of antennas for radiating and/or receiving signals; antennas are installed on antenna holder and assembled in the form of at least two subarrays, each incorporating one or more mentioned antennas, control facility for electrical phase regulation of signals radiated and/or received by antenna assembly so as to control angle of inclination of antenna assembly electric axis, combining facility that provides for antenna assembly to radiate and/or receive, in effect simultaneously, first one of mentioned signals at first angle of inclination of electric axis and second one of mentioned signals at second angle of inclination of electric axis.
 Balloon ultrashort-wave antenna / 2321110
Proposed ultrashort-wave balloon antenna has metal container accommodating radio station and conductors running above container surface parallel to its longitudinal axis. Counterpoise in the form of metal disk and conductors radially diverging from its edge is installed in cavity perpendicular to container longitudinal axis. One end of each conductor disposed above container is connected to container base and other, to counterpoise metal disk. Container surface is connected in addition to each of these conductors through shorting jumper. Coaxial feeder is disposed in cavity of one of jumpers and in part of conductor running to metal disk, feeder external sheath being connected to disk center and central conductor, to container top. U-shaped conductors are connected in addition to container body.
 Balloon container antenna / 2321109
Proposed balloon container antenna has metal container in the form of two identical coaxially installed metal blocks with conductor leads connected to their peripheral ends. Rectangular metal plates are installed on opposite edges of blocks on each of butt-ends abutting against each other. Planes of all plates are relatively parallel and perpendicular to butt-end plane. Output coaxial feeder running from radio station is connected through shielding screen to vertex of one of triangular plates and through central conductor, to vertex of other plate. Optimal proportions of dimensions of components affording desired effect are evaluated.
 Balloon antenna / 2318274
Proposed balloon antenna has metal container and metal rod secured coaxially to the latter at metal-rod base. External end of rod mounts two loop radiators orthogonal relative to one another, their outputs being integrated and connected by means of metal ring to central conductor of coaxial output of radio station disposed in metal container; connected to this central conductor is antenna counterpoise in the form of radially diverging conductors and additional conductor sections connected to their external ends. Optimal proportion of antenna structural component dimensions are determined.
 Mechanical design of elongated radar antenna array for flying vehicle / 2308129
Proposed elongated radar antenna array for flying vehicle, for instance helicopter, is essentially set of printed-circuit antenna modules installed in array enclosure to form flat effective surface of antenna array by effective sides of module dipoles; antenna array is provided with enclosure-mounted suspension unit for its setting up from horizontal shipment position to vertical operating one and for rotating it in operating position by means of drives disposed in flying vehicle; antenna array has pressurized enclosure combined with antenna module dome whose function is performed by front electromagnetically transparent wall of antenna array enclosure. Antenna modules are installed on internal load-bearing partition of antenna array enclosure and disposed between this partition and mentioned front wall functioning as dome under conditions of forced air supply to antenna modules to abstract internal heat affording utmost use of external air flow during vehicle flight; its cooling facilities are disposed within enclosure, on its rear part, between its rear wall and mentioned load-bearing partition; cooling air is admitted through inlet holes of hollow longitudinal framework member built integral with load-bearing partition and positioned in parallel with antenna-module along antenna array curtain; distribution line; it is provided with inlet cooling air distribution holes on their disposition end to supply cooling air to antenna modules and to area of module clearances accommodating antenna module heat sinks forming cooling ducts for air passage through circulation ports of internal load-bearing partition to rear part of array enclosure; the latter is composite structure built of several (say, three) longitudinal parts joined together; capacity of cooling facilities is sufficient to ensure total flow not over 1.32 (l/s) x W-1 per unit heat power released by antenna modules.
 Ball antenna / 2308128
Proposed antenna that can be used for receiving television programs, for mobile and USW radio communications in zones of uncertain horizontal- and vertical-polarization wave reception is applied to surface of ball filled with light gas and is made in the form of circular loops whose geometric dimensions comply with main and additional frequency bands. Connected to loops through half-wave intervals are short-circuited stubs integrating adjacent loops. The latter can be applied along parallel or meridian lines of ball depending on wave polarization.
 Folding antenna / 2304328
The antenna has three identical n-links pantographs 1,2,3 installed vertically so that they form a straight cylinder with a cross-section in the form of an equilateral triangle, adjoining to each other the ends of the elements 41,42 forming the links of the pantographs are connected to each other pivotally, some ends of the pantographs are fastened with the foundation in the shape of a beaker provided with a cover in which pantographs are located in packed state, elements 41, 42 of the links of the pantographs are connected pivotally in the centers, in the places of hinged connection of the elements there are rings 6, the antenna is provided with a holder limiting the maximal size of the antenna in an unfolding state and with a holder preventing the antenna from piling up after its unfolding.
 Helicopter radar antenna-feeder assembly / 2291525
Proposed radar antenna-feeder assembly designed for trouble-free operation under variable- and vibratory-load conditions due to enhanced strength incorporated in its mechanical design and improved aerodynamic properties of elongated antenna array and feeder circuit has its receiving-radiating components forming flat elongated antenna array and high-frequency feeder circuit physically integrated with functional units; antenna array case accommodates its suspension unit for turning it by means of helicopter-mounted drive from horizontal transport position under helicopter fuselage to vertical working position and vice versa. Antenna array modules function as its stiffness ribs. Provision is made for easy disconnection of antenna array from helicopter under emergency conditions.
 Spacecraft antenna-feeder assembly (alternatives) / 2276434
Proposed spacecraft antenna-feeder assembly has antennas disposed in diametric opposition to external diameter of spacecraft hull and integrated by feeder system incorporating radio-frequency feeders and power splitters connected to on-board radio system; each antenna has axially symmetric funnel-shaped directivity pattern whose opening angle is regulated by spacecraft flight path. Directions of axial minimum value of directivity pattern of antennas are combined with central direction of sector of communication angles with equipped ground measuring station during oriented flight of spacecraft; installed in immediate proximity of antennas and inserted in feeder system are radio-signal amplifiers. Antenna-feeder assembly for high-power and large-size spacecraft incorporates provision to adapt its power characteristics to spacecraft altitude changes in space, including equally probable spacecraft position in space.
 Scanning antenna of helicopter on-board radar (alternatives) / 2263377
Radiator, excitation line, and loop coupler are produced and mounted in position; antenna is made in the form of linear array in L wave band disposed in helicopter lifting rotor blade which is used as directivity pattern scanning mechanism due to its rotation.
 Transceiving antenna / 2249280
Proposed superbroad-band antenna characterized in passband extended to six octaves with fixed low-pass transmission windows is disposed in plane perpendicular to screen and has radiators made in the form of three monopoles that form funnel-shaped directivity pattern in elevation plane and omnidirectional pattern in azimuth plane. Electric length of radiators and distances between axes of central radiator and side ones are stipulated. In addition radiators and matching device or matching device only are disposed in space filled with insulating material having dielectric constant not over 2.0. This space may be shaped as elliptical cylinder or elliptical truncated cone. Other dimensions of antenna are specified. Cone may be interpolated by polyhedron with minimum four apexes whose pointed edges are rounder off at radius of minimum 0.01λm.
 Method of thermocontrol of spacecraft and device for implementation of this method / 2329922
Invention refers to thermal control, chiefly to thermal control of automatic spacecrafts. The suggested method includes excessive heat removal from apparatus installed on a heat conductive cellular panel of an instrumentation container. The latter is formed by a combination of two U-shaped cellular panel blocks. L-shaped regulated heating pipes (HP) are installed into a middle instrument cellular panel. Evaporators of these HPs are longitudinally and in pairs connected to each other, while condensers are placed into side cellular panels which operate as radiators-emitters. For additional heat removal built-in HPs are incorporated, the evaporators of which are connected to evaporators of L-shaped HPs, while condensers are built into additional disclosed radiators-emitters. Evaporators and condensers of incorporated HPs are interconnected to each other by means of flexible silphon portions. Additional radiators-emitters are disclosed by means of electric drives into various angular positions depending on the removed heat space; the said angular positions are determined by a control unit with temperature sensors. The suggested system of a thermo regulation can contain two instrument containers of the said U-shaped blocks. These containers are connected to each other along the planes of the corresponding middle cellular panels so that the side cellular panels (radiators-emitters) of containers are located in orthogonal planes to each other.
 Method of arrangement of stationary earth man-made satellite / 2329920
Proposed method consists in using a vessel aboard the satellite with a required constant area of the liquid phase location on the said vessel wall surface. The Earth satellite lengthwise axis, in operating conditions, is constantly directed along the current radius-vector of the orbit mass centre. The aforesaid vessel is placed at a maximum possible distance from the satellite mass centre along the direction parallel to the said lengthwise axis. The vessel should be placed so that the normal at the point of the vessel wall surface opposite the working medium outlet was directed towards the satellite mass centre. The said point should be located at a minimum possible distance from the satellite lengthwise axis.
 Fairing of rocket launcher / 2328410
Invention concerns devices for improvement of aerodynamic properties of aircrafts, mostly rocket launchers (RL). The fairing comprises nose cone (1), cylindrical compartment (2), rear extension (3) of the last stage (4) of RL. The fairing features permeable porous rim (5) and insert (6) that damp pressure fluctuation (in the flow separation zones). Biconical nose cone (1) is preferred, and semi-vertex angle of the first cone (7) is 25°- 35°, while semi-vertex angle of the second cone (8) is 13°- 25°. Length of the first cone is 0.2 - 0.25 of the total nose cone (1) length. The rim (5) and insert (6) are both as long as 0.11 of the cylindrical compartment (2) length. Total length of this compartment exceeds its diametre at least by 1.11 times. The extension (3) can have partition ribs made of permeable or pressure pulsation-damping material.
 Plot board for ground surveillance object selection from orbital space vehicle / 2324898
Plot board for ground surveillance object selection from orbital space vehicle refers to space technology. The plot board for ground surveillance object selection from orbital space vehicle includes flexible tape with the ground map printed on it, and semitransparent plate above the tape. Two halves of the space vehicle's orbit pass are drawn on the plate in such a way that the ascending node in the beginning of the first half of the orbit pass and the descending node in the beginning of the second half of the orbit pass are superimposed. The plot board also comprises a device for the tape map transport along the plate with orbit pass image; the transport device comprising two shafts that are spaced-apart and interconnected in parallel. The map printed on the tape has the equator beginning and ending points superimposed, and the tape is made in the form of a ring and pulled on the shafts so as to move along the map equator line. The distance between the shaft axes and size of the plate with the orbit pass image along the equator direction are equal to (L-d)/2, where L - is the map equator length; d - is absolute distance between passes measures in linear units along the map equator; shaft radius equals to d/(2π). The stated above gives the effect of decreased plot board size.
 Method of suppression of interference caused by vibrations of elastic structure of transformable space antenna in the course of operation and device for realization of this method / 2323136
Proposed method consists in monitoring acceleration and respective deviations of geometric parameters from theoretical magnitudes at check points. Monitoring is carried out continuously in real time. Check points are made for all shape-forming members of antenna structure. Device proposed for realization of this method has geometry and acceleration monitoring system which is made in form of combined spatial position and acceleration sensors. Sensors are made in form of miniature three-axis units of gyroscopes-accelerometers which are electrically connected with onboard information-and-measurement control system via analog-to-digital converters. Onboard information-and-measurement control system is electrically connected via respective power amplifiers with actuating members of extended structural members of spacecraft.
 Spacecraft instrumentation module / 2319646
Proposed instrumentation module has body made from honeycomb panels. Thermostatted plate of payload is mounted on body with the aid of brackets. Equipment of instrumentation module is installed on honeycomb panels, mainly inside module. Honeycomb panels are provided with labyrinth-type vent holes and technological holes for introduction and removal of structural members: rods, pipe lines, cable bundles, etc. Clearances between honeycomb panels of body of instrumentation module, between instrumentation module and thermostatted plate, between edges of technological holes and said structural members are shielded by means of optically opaque member which is made from material having electrically conducting layer ensuring electrical tightness of instrumentation module. Shielding member is also provided with labyrinth-type vent holes.
 Device for deployment of ultra-red target in space / 2314976
Proposed device has cassette with inflatable envelopes and doors, nitrogen generators with pyro retarders, starting device with spring mechanism for ejection of cassette from starting device and electric connector. Door axles are provided with torsion springs. Nitrogen generators provided with check valves are located on one side from thin-film envelopes. Height of ejection mechanism in compressed state is comparable with diameter of each nitrogen generator. Electric cable of electric connector has free loop whose length is equal to path of motion of cassette till moment of steady ignition of pyro retarders. Circuit supplying the electric pulse to igniter of each pyro retarder is provided with terminal closing this circuit at the beginning of motion of cassette.
 Rocket nose cone and method of its separation / 2314233
Proposed rocket nose cone has body made in form of envelope which is closed at one end and is provided with frame on other end which is not closed; rocket nose cone is provided with tubular force exciters. Body has weakened section in plane of separation. Body forms inner closed chambers in plane of separation where tubular force exciters of directive action are located. Chambers are formed by body envelope and by its longitudinal fins. Walls of these fins are directed to plane of separation and are parallel relative to it; they are strengthened by transversal structural members fastened to body envelope. Detachable covers are secured on longitudinal fins of chambers by means of fasteners; they have weakened sections in plane of separation of nose cone which are similar to those made in body; their areas are equivalent.
 Composite stable-sized platform / 2312771
The invention is pertaining to the load-carrying structures made out of the laminated polymeric composite materials and may be used in the high-precision space and ground equipment, for example, as the support for the optical instruments, the antenna systems and the measuring systems. The presented platform is made in the form of the plane annular or circular centrally-symmetric board and contains the encasings made out of the layers of the fibrous material impregnated with the polymeric binding, the cell-type filler placed between the casings and the attachment points disposed with the equal angle pitch. Each layer of the casings consists of the sectors docked among themselves with the equal central angle. Quantity of the sectors in each layer is equal or multiple to the number of the attachment points. In each sector of one layer the filaments are oriented at the equal angle concerning the central axis of the sector. T sectors of each subsequent layer are shifted concerning the sectors of the previous layer at the angle equal to the half of the central angle of the sector. In each sector of the same layer the filaments may be oriented at the angle of 90° to the central axis of the sector. There may be present the layers, where the filaments are oriented at the angle of 0° to this axis. The technical result of the invention is to ensure the control over the thermal deformation of the platform with the purpose to reach the given accuracy of positioning of the attachment points on it at fulfillment of the strength and rigidity requirements to its design.
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FIELD: transport. SUBSTANCE: spacecraft includes the phased antenna array (PHAA) representing flat rectangular sections, each of them the structures furnished with a front covering fitted on the carcass. The spacecraft onboard equipment is fixed on the rear sides of the flat hardware platforms arranged at the PHAA sections rear. In placing the spacecraft into orbit, the PHAA sections are folded with their faces parallel to each other, with solar batteries panels being inserted there between. Transceiver units are arranged on the front covering rear with their radiator on the covering face. Thermal pipes are arranged inside the front covering and connected with the device of heat withdrawal into space. The suggested PHAA section contains a carcass, the a front skin, a transceiver units and radiators. The section carcass is made up of rectangular closed section channels furnished with an extra internal strip. The front covering made up of three-layer panels is attached to the said strip. A screen-vacuum heat-insulation layer is arranged between the aforesaid panels. The outer panel is made from carbon-based plastic material, the inner panel is made from aluminum alloy. The inner panel honeycomb structure accommodates heat pipes withdrawing heat from the transceiver units. EFFECT: high geometrical stability of the phased antenna array, smaller weight. 9 cl, 10 dwg
The proposed technical solution related to space technology, and in particular to device spacecraft, equipped with a phased array antenna and intended for a wide range of tasks on remote sensing of the Earth. The proposed solutions can be used to study other planets in the Solar system with the orbits of their satellites. When designing a spacecraft equipped with a phased array antenna of large dimensions, in addition to the traditional tasks for optimizing the appearance of the device and its on-Board systems, it is necessary to solve the problems of integration in the design of the spacecraft antenna phased array considerable dimensions, the stability of its geometrical parameters under various conditions of flight of the spacecraft, combined with the convenience of placing a spacecraft antenna phased array under the fairing of the launch vehicle during insertion of the apparatus into orbit. There are a number of solutions spacecraft, equipped with a phased array antenna (see Sverak, Wiegenstein. Space system of remote sensing of the Earth, Moscow, 1997). A distinctive feature of the technical solutions of these satellites (ENVISAT-1, ERS-1, RADARSAT-1, JERS-1, and others, see str, 139, 145, 149 specified source) is a division of the spacecraft to the orbital module with on-Board service equipment, antenna phased array airborne early warning lattice large size and flat solar panel. When this phased array antenna and solar panels are fixed on the orbital module. During insertion of the spacecraft into orbit phased array antenna and solar panels in a variety of ways to fold around the orbital module. Antenna phased arrays of these technical solutions are in the form of flat sections, the sections of the antenna phased arrays can be supported from the back side of the antenna power frame, made in the form of shaped structures, see, for example, the device space of RADARSAT-1 (specified source, str). The antenna is the large dimensions of the module of remote sensing "Nature" (see str specified source) made in the form of clippings paraboloid of revolution and composed of front and rear covers and the frame in the form of a rod system. These features space solutions spacecraft cause the significant mass of the spacecraft, insufficient and geometric structural stability antenna phased arrays. A certain step in the development of technical solutions spacecraft antenna phased array is a technical solution (see patent Led is the UK No. 2330343, IPC 64G 1/10, publ. 21.04.1999), which tries to integrate a phased array antenna and on-Board service equipment, traditionally placed in the orbital module, in one structural module of the spacecraft. This technical solution is the closest analogue to the claimed solution of the spacecraft. In accordance with this technical solution spacecraft contains antenna phased array airborne early warning grille, side utility equipment, solar cells system power spacecraft, fuel system from fuel tank. Antenna phased array made of two sections, each of which is made in the shape of an elongated rectangle. To increase the usable space of the phased array antenna has two straight angle of each section of the antenna in this solution is additionally cut in two segments placed relative to each other and to the sides of the sections at an obtuse angle. Section phased array antenna pivotally connected to each other, while the hinged connection of the sections of the phased array antenna is made with the possibility of folding sections face each other during insertion of the spacecraft into orbit and deploy partitions in space butt with each other. Each section of the phased antenna is esedi equipped with front panel frame and modules antenna phased array radiators and transceiver blocks. In this technical solution, the frames of the sections of the phased array antenna includes longitudinal and transverse load-bearing elements - the stiffening elements made in the form of walls, placed perpendicular to the front casing with the back of her hand. Two longitudinal walls parallel to the long side of the section and located at some distance from the long ends of the front casing, the transverse wall parallel to the short sides of the sections, placed at some distance from the short sides of the sections. Apart from the walls, this technical solution structure of power included the power rods, trailing nodes of intersection of the transverse and longitudinal walls. The front casing is fixed on the power frame. Modules antenna phased array include emitters and transceiver blocks. The emitters are located on the front side of the front casing, and transceiver blocks on the rear side of the front casing. The emitters of the electrical connections is connected with the transceiver blocks. Side of the service equipment connected to the rear sides of the sections of the antenna phased array blocks onboard service equipment attached to the walls of the frames of the sections of the antenna phased array. This is the technical solution spacecraft equipped with fuel system, includes fuel tank. In this technical solution, each section of the phased array antenna provided with a fuel tank, fuel tanks placed near the geometric center of the sections on the rear side of the front shell. The power supply system of a spacecraft includes solar cells. This technical solution solar cells placed on the rear surface of the spacecraft is on the back side of the front covers and the frames of the sections of the antenna phased array. In addition to marked items spacecraft includes mechanical means of fixation, zackowski and disclosure sections of the antenna phased array after insertion of the device into space. In addition, the spacecraft contains antennas for communications, sensors orientation. During insertion of the spacecraft into space section of the phased array antenna are folded beneath the fairing of the launch vehicle parallel to each other. Their front sides facing each other. After insertion of the spacecraft into orbit partitions are deployed relative to each other and joined with each other on their short sides, forming a single planar antenna phased array airborne early warning bars. Using this technical solution, ensuring optimal antenna configuration of fair the EN-lattice during insertion of the apparatus into orbit with the further deployment of partitions into a single antenna, not possible to develop a spacecraft light-weight due to the large mass proposed in the technical solution of the frame. This is due to the fact that technical solution is not considered thin thermal regulation of the front casing sections antenna phased array. The closest analogue of the claimed section of the phased array antenna is a section of the phased array antenna (see Oigrien. "Design of structural elements aperture antennas and HEADLIGHTS", ed. MAI, M., 1996, p.34-35). In accordance with this decision, section phased array antenna includes a frame, front trim panel, modules, antenna phased array and means of control. The frame section of the phased array antenna in this technical solution enables the contour of the longitudinal and transverse load-bearing elements. Path, the longitudinal and lateral elements of this technical solution made of channels U-shaped profile (position 1 and 2 Fig.2.2 specified source). Front trim panel, in the terminology of the source - antenna canvas, mounted on the frame and made this technical solution in the form of a sheet, the outer surface of which is metallized by sputtering method. Modules phased array antenna in this technical solution is placed on the back side of the front of the her skin. In this technical solution, the means of control in the form of sleeves (pos.4 Fig.2.2 specified source), which in this technical solution also serve to secure the modules phased array antenna at the rear side of the front shell. The main disadvantage of this technical solution is the instability of the geometrical parameters of the surface of the phased array antenna due to the unresolved issue of heat dissipation from the module antenna phased array. Technical problem solved by the claimed spacecraft, is to develop a device of the spacecraft, equipped with a phased array antenna, the power supply system which can generate considerable energy in combination with high geometric stability antenna phased array and light-weight design of the device. The technical problem solved by the claimed device section of the phased array antenna is the development of a device section antenna phased array for high geometric stability of the surface of the phased array antenna in combination with a small mass. The specified technical task proposed device spacecraft is solved as follows. It is known device to the economic system, containing the antenna phased array airborne early warning grille, made in the form of pivotally connected with each other by two flat rectangular sections. Each section phased array antenna provided with a front panel installed on provided with transverse structural members of the frame and modules phased array antenna, which include radiators located on the front sides of the front casing, and transceiver blocks on the rear sides of the front liners. In addition, the spacecraft is equipped with on-Board service equipment, solar cells, fuel system with the fuel tank. In the known spacecraft hinged connection of the sections of the phased array antenna to each other is made with the possibility of folding sections face each other during insertion of the spacecraft into orbit and deploy partitions in space butt with each other. In the device known spacecraft news is that the solar cells placed on two rectangular solar cells, each of which is pivotally attached to one of the sections of the antenna phased array. Swivel solar panels with sections phased array antenna is made with the possibility of their placement between section the s antenna phased array during insertion of the spacecraft into orbit and deploy solar panels in space. The frame of each section phased array antenna is made in the form of a frame with a rectangular circuit connected to the transverse structural members, while the transceiver blocks are placed in the openings of the frames of the frames. Section phased array antenna is further provided with systems management, including arterial heat pipes placed inside the front casing sections phased array antenna. Arterial heat pipe thermally connected to the removal device thermal energy into space. Each section phased array antenna equipped with a hardware platform that is installed from the back side of the section phased array antenna with a gap relative to the frame skeleton. Hardware platform fixed on the outline of a skeleton frame, while the side of the service equipment is placed in the gap between hardware platforms and frames of the frame and fixed to the inner sides of the hardware platforms. The outer surface hardware platforms made in the form of radiators-radiators. In addition, in the inventive device spacecraft's new is that thermal control system partitions antenna phased arrays can be provided with a collector heat pipes on the rear sides of the front obsh the wok near one of the sides of the frames, and arterial heat pipes are placed perpendicular to these sides of the frames with capability thermal contact with the collector heat pipes. In addition, in the inventive device spacecraft's new is that thermal control system partitions antenna phased arrays can be equipped with evaporative heat pipe thermally connected to the collector heat pipes and device removal of thermal energy into space. In addition, in the inventive device spacecraft news is that the evaporative heat pipes thermally can be connected to hardware platforms. In addition, in the inventive device spacecraft's new is that the device of the removal of thermal energy in space can be made in the form of additional heat-sink-radiator thermally connected to the evaporator by the heat pipe. Additional radiator-emitter in the inventive spacecraft can be placed along the end of the skeleton frame, at least one of the sections of the antenna phased array. Additional radiator-emitter can also be placed on the rear side of the frame frame, at least one of the sections of the antenna phased array. In addition to t the th, in the inventive device spacecraft's new is that section of the phased array antenna may be further provided with a rear casings connected with the frames of the frames of the sections of the antenna phased arrays, with at least part of the surface of the rear casing may be made in the form of an additional radiator emitter. The specified technical task of the claimed device section of the phased array antenna is solved as follows. In the known device section of the antenna phased array containing made in the form of a rectangular frame, the frame including a transverse load-bearing elements and the circuit made of channel bars mounted on the frame front trim panel, modules, antenna phased array and means to control what is new is that the frame is made of channel bars closed rectangular profile, equipped with an additional internal jumper located near the mid-height of the profile. In addition, in the inventive device antenna phased array new is that the front casing composed of two three-layer panels, between which is placed a layer of screen-vacuum thermal insulation. Bearing layers of the outer panel is made of carbon fiber, filler made in the form of hundreds of namecalling the material, and load-bearing layers of the inner panel and the filler, made in the form of a honeycomb made of aluminum alloy. In addition, the sheathing panels are fixed to the inner jumper the channels of the frame by fastening elements made of a material with low thermal conductivity. Modules phased array antenna made of emitters installed on the outer panel, and the transmission and reception units that are installed on the inner panel of the front plating in the openings of the frame frame. The means of control in the inventive device section of the phased array antenna is made in the form of heat pipes, missed inside the placeholder inner panel. The proposed device of the spacecraft allows you to develop spacecraft with energy system that will generate significant power energy, which is achieved by placing solar cells on the solar panels. Moreover, the placement of solar panels on the stage launching into space between sections of a phased array antenna allows you to conveniently place solar panels large area inside the fairing of the launch vehicle. High geometric stability of the phased array antenna is provided by performing a hard Kark the sa sections in the form of a frame in combination with the introduction of the sections of thermal control system, including arterial heat pipes. Arterial heat pipes, missed inside of the front casing sections phased array antenna, in combination with placement of the transceiver blocks on the rear surface of the front casing, and their emitters on their outer surfaces to provide effective removal of heat energy from the transceiver blocks and radiators, and from the front surface of the front casing, which can be hot on some phases of flight from solar radiation and from the Earth radiation. The skeleton frame, which should consist of a well heat-conducting material, enables you to ensure the effective alignment of the temperature field across the antenna of the phased array. We offer accommodation on-Board service equipment hardware platforms contributes to the development of small spacecraft mass, as it provides accommodation onboard service equipment on one side of the platform, while the other side hardware platform is used to reset thermal energy into space. The inventive device spacecraft provides opportunities for reset thermal energy from sections phased array antenna into space. Arterial talovyerov can be thermally connected to the radiator-emitter, placed on the outer side of the hardware platforms that it is advisable to perform at small dimensions of the sections of the phased array antenna and with a small amount of heat dissipation in the module antenna phased array. When large volumes of heat dissipation in the module antenna phased array spacecraft may be further provided with additional radiators (emitters). Extra radiators-radiators depends largely on the nature of the orbit, which operates the spacecraft, which determines the position of the spacecraft relative to the Sun. Depending on this additional radiators-radiators can be placed on the ends of the frames of the frames of the sections of the antenna phased arrays or on the rear side frames frames. In some cases, the sections phased array antenna can be equipped with a rear casings, with a part of their surface can be used as an additional heat sink emitter. Effective transfer of heat from the transceiver blocks most appropriately be made through a system of heat pipes. Thermally connecting the arterial heat pipes with a means of removal of thermal energy in space can be achieved by collector tepavicharov, thermally connected to the evaporator by heat pipes. The totality of the claimed features of the decision section of the phased array antenna enables you to develop a design section with low weight and high stability of geometrical parameters in conditions of space flight. The claimed solution of the front casing section phased array antenna provides for its implementation of the two-layer panels, and the outer is made from carbon fiber with a non-metallic filler, and the inside is made of aluminum alloy. This solution allows to solve the partition antenna phased array of diverse tasks of the various functional elements: high razmorozhennoe design is a result of the execution of the outer panels of carbon fiber with an aggregate of non-metallic material, and the task of perception inertial loads from the transceiver blocks to solve it through the use of three-layer inner panel of aluminum alloy. The presence of a layer of screen-vacuum thermal insulation between the panels of the front casing in combination with placement of the heat pipes inside the placeholder inner panel, honeycomb, aluminum alloy, solving the problem of heat removal from the transceiver blocks, minimizes the heat flow from the transceiver modules to N. the outer panel of the front casing, which reduces the gradient of the temperature field on the surface of the outer panel and reduces its thermal deformation. In the reduction of thermal gradients on the section structure plays an important role and frame sections. Implementation of channel of rectangular cross-section, the profile of which has an internal jumper, provides effective temperature equalization throughout the structure, which reduces the impact of the armature on the outer panel. The front panel fixing cladding to internal jumpers placed in the middle of the height of the profiles allows you to avoid deformation of the torsion and bending of the frame due to heat flow in the power frame members of the frame from the front panels of the hull. This contributes to the fixing of the panels of the front casing section on the power elements of the frame-fastening elements made of a material with low thermal conductivity. The proposed technical solution is illustrated in the following materials: figure 1 - view of the spacecraft with folded sections of the phased array antenna and solar panels under the head fairing of the launch vehicle during insertion of the spacecraft into orbit; figure 2 - General view of the spacecraft after launch into orbit (section phased array antenna and solar panels ripped), figure 3 - view of the and spacecraft in the front, 4 is a view of the spacecraft along arrow a from Fig 3, 5 is a view of the spacecraft in the direction of arrow B with 3, 6 is a General view of the frame section of the antenna phased array, 7 is a structural diagram of thermal control system of the spacecraft, Fig - structural diagram of the layers of the front casing section antenna phased array, Fig.9 - incision anterior plating in the contact zone of arterial heat pipe with transceiver units; figure 10 is a section of the front panel in place of its connection with the frame. Declare spacecraft is organized as follows. Declare the spacecraft contains the antenna phased array airborne early warning lattice composed of two sections 1, onboard service equipment 2, solar cells placed on the solar battery 3, the fuel system with the fuel tank 4. Antenna phased array consists of two flat rectangular sections 1. Section pivotally connected to each other by means of the deployment mechanism 5 antenna phased array. Each section is equipped with front casing 6 mounted on the frame 7 (see Fig.6), modules phased array antenna, comprising the emitters 8, placed on the front sides of the front casing 6, and transceiver blocks 9 on the rear side of the front casing (see Phi is .9 and 10). The frame of each section phased array antenna is made in the form of a frame with a rectangular circuit 10 connected to the transverse structural members 11 (see Fig.6). When this transceiver blocks are placed in the openings of the frame frame. The frames of the sections of the phased array antenna is one of the main elements of the power circuit of the entire spacecraft, the presence of the frame, as will be discussed below, makes it possible to solve several optimization goals design-layout scheme of the spacecraft. The hinged connection of the sections of the phased array antenna to each other is made with the possibility of folding sections face each other during insertion of the spacecraft into orbit (see figure 1) and partition deployment in space butt to each other (see figure 2). After launch of the spacecraft on the orbit partition of a phased array antenna to fit flush with each other along one of their sides to form a unified fabric antenna phased array. The inclusion of the frame allows to solve several tasks. First, the frames themselves, and their ends are convenient to use as load-bearing element for mounting the various elements of the spacecraft. The above mechanisms deployment of antenna sections Fay is vannoy lattice is also advisable to secure the ends of the frames of the frames. Secondly, fixing the front casing sections phased array antenna on the contour of the frames of the frame, and transverse reinforcing elements of the frame, the frame can be used as the heat-conducting elements to align perepadov temperature on the surface of the antenna phased array. As mentioned above, the solar cells of the claimed device spacecraft are placed on two rectangular solar cells 3. Each of the panels solar panels pivotally attached to one of the sections of the antenna phased array. Swivel solar panels with sections phased array antenna is made with the possibility of their placement between sections of the antenna phased array during insertion of the spacecraft into orbit and deploy solar panels in space. Solar panel it is reasonable to fasten to the sides of the sections of the phased array antenna, opposition parties, on which section of the antenna phased array joined with each other. Solar panels are fixed on the sections of the antenna phased array using drives 12. The actuator 12, it is advisable to do not only with capability deployment of solar panels in space, but with obespecheniyavozmozhnost their turn when orbiting artificial satellite of the Earth. As the deployment mechanism sections phased array antenna, actuators, solar panels should be placed on the frame of the frame. The inventive device spacecraft differs supply sections phased array antenna systems management. The necessity of including in the composition of its sections phased array antenna control systems due to the significant dissipation of transceiver units and high requirements on the stability of the geometric dimensions of the antenna phased array, which requires, in addition to efficient removal of excess heat into space, minimizing temperature variations on the surface of the antenna phased array. System control sections phased array antenna include arterial heat pipes 18, is placed inside the front casing sections phased array antenna (see Fig.9). Arterial heat pipes thermally connected with the heat extraction, which provides excess heat into space. To achieve optimal mass parameters of the spacecraft in combination with optimal temperature regime of their work contributes to the supply of each antenna section f is tirovannoj lattice hardware platform 13. Hardware platform 13 is installed from the rear side sections phased array antenna with a gap with respect to the frame of the frame and attached to the end of its path. Hardware platform can be attached to the ends of the frame frame with the use of inclined rods 14 and bracket 15. Hardware platform it is advisable to put in parallel with the frames of the frame sections of the antenna phased array. Side of the service equipment 2 is placed in the gap between hardware platforms and frames of the frame and fixed to the inner sides of the hardware platforms and the outer surface of the hardware platforms it is reasonable to perform in the form of radiators-radiators. System control sections control sections phased array antenna, it is advisable to provide the collector with heat pipe 19 (see 7, 10). When this collector heat pipe 19 is advisable to place on the back of the front casing near one side of the contour of the frames, and arterial heat pipe 18 is placed inside the front casing sections phased array antenna perpendicular to these sides of the frames with capability thermal contact with the collector heat pipes. In some cases, the collector heat pipes are easier to perform in the form of two is perenich parallel heat pipes, as shown in figure 10. In addition, thermal control system partitions antenna phased arrays it is reasonable to provide evaporative heat pipes 20, thermally connected to the collector heat pipes and device removal of thermal energy into space (see 7, 10). As the device of removal of thermal energy in space can be used hardware platform. In this case, the evaporative heat pipe is thermally connected with the hardware platforms, the removal of thermal energy from the front of the casing sections phased array antenna is made with the use of an external surface of the apparatus platform 13, is made, as mentioned above, in the form of a radiator of the radiator. As the device of removal of thermal energy in space can be used as additional radiators-radiators 21. In this case, additional radiators-radiators thermally connected with the evaporation heat pipes (see Fig.7). Additional radiator-radiator 21 can be placed along the end of the skeleton frame, at least one of the sections of the antenna phased array. Additional radiator-emitter can also be placed on the rear side of the frame frame, at least the, one of the sections of the antenna phased array. Additional radiator-radiator also can be placed on the rear side sections of the antenna phased arrays, while section antenna phased arrays must be further provided with a rear casings connected with the frames of the frames of the sections of the antenna phased arrays, with at least part of the surface of the rear casing may be made in the form of additional heat-sink-radiator. The rear casing, not shown in the drawings, may be placed parallel to the front casings and secured on the opposite side of the frame frame. To ensure insulation of the entire spacecraft section phased array antenna, it is advisable to close the on-screen-vacuum thermal insulation 37 with the ends of the frame frame and on the back of the frame (see figure 10). As mentioned above, the spacecraft is equipped with a fuel system including a fuel tank 4. In addition, the fuel system may include cylinders 22 of compressed gas, the correction engine 23, engine orientation 16. The fuel tank 4 can be placed on one of the sections of the antenna phased array. While it is advisable to perform a spherical shape, and place near the junction of the sections of the phased array antenna to each other in the unfolded position as shown in figure 4, and on another section of the phased array antenna near the specified interface sections can be placed cylinders 22 of compressed gas. This placement of the fuel tank 4 and the cylinders 22 of compressed gas provides accommodation close to the center of mass of the spacecraft and minimizes the change of position of the center of mass of the spacecraft as production of consumable components. Reduction of disturbing influences can serve and placement of the engine correction 23 directly on the fuel tank 4. As mentioned above, the contour of the frame frame is one of the main load-bearing elements of construction, provides significant advantages for the placement of the elements of the spacecraft. In particular, at the ends of frames frames can be placed engines orientation system 16 spacecraft. The ends of the frames frames can be used for fastening the fuel tank 4 via the fastening elements 17. In addition, at the ends of frames frames can be placed sensors 34 system orientation of the spacecraft and the antenna 33 of the connection. Declare section phased array antenna is arranged as follows. Section antenna phased array contains the frame 7. The frame is made (see Fig.6) in the form of a rectangular frame. The frame includes a transverse load-bearing elements 11 and the circuit 10. Cross silove the elements and the circuit is made of channels. The frame of the proposed solutions made of channels closed rectangular profile (see figure 10). Channel frame provided with an additional internal jumper 24, located near the mid-height of the profile. In addition, section antenna phased array contains mounted on the frame of the front casing 6, the modules phased array antenna and means of control. The front casing section of the phased array antenna is composed (see Fig) of the two-layer panels: outer 25 and inner 26. Between the outer panel and the inner layer placed 27 screen-vacuum thermal insulation. Bearing layers 29 25 of the outer panel is made of carbon fiber, its placeholder is made in the form of honeycombs 30 of non-metallic material, and bearing layers 31 of the inner panel 26 and the filler is made in the form of honeycombs 32, made of aluminum alloy. Sheathing panels are fixed (see figure 10) on the internal jumpers 24 channel frame fastening elements 28. The fastening elements should consist of a material with low thermal conductivity, which can be selected, for example, titanium. As shown in figure 10, the fastening elements of the front casing to the frame can be made in the form of bolted connection. Modules phased array antenna made of emitters , installed on the outside of the panel by means of fasteners 35, and transceiver blocks 9, installed on the inner panel of the front plating in the openings of the frame frame using fastening elements 36. Means of control of the front cladding made in the form of arterial heat pipes 18, missed inside the filler 32 of the inner panel 26 (see Fig.9). Arterial heat pipes are placed inside the placeholder inner panel with thermal contact with the bearing inner layers panel. Declare the spacecraft operates as follows. The spacecraft appears to orbit in the folded position. This section of the phased array antenna folded right sides together with the formation of a gap between them wide enough to fit between the sections of the antenna phased array of solar panels. Rear side sections phased array antenna with hardware platforms while facing outwards from the folded spacecraft. This solution space of the apparatus in the folded position provides its compact accommodation under the head fairing of the rocket. Inertial loads from on-Board equipment when this is perceived hardware platforms and transferred to the circuit frames frames sec is the second phased array antenna. In addition, the contours of frames frames are perceived and inertial loads from the front casing sections phased array antenna and placed them on the modules and elements of the spacecraft, located at the ends of frames frames, including solar panels. Contour frames frames inertial loads are transferred to the design of the rocket. The proposed device of the spacecraft allows you to place the main elements of a spacecraft on a small shoulder relative to the frame, which reduces the load on the structure. After insertion of the spacecraft into orbit first deployment mechanism deploys section phased array antenna. Section phased array antenna deployed and joined with each other along one of their sides to form a unified fabric antenna phased array. Then using drive solar panels are deployed solar panels. In the future spacecraft on orbit using the drive solar panels can control the position of the solar panels. When operating a spacecraft in orbit transceiver modules perform the generation and reception of high frequency electromagnetic radiation pic what edstam emitters modules phased array antenna, and using onboard equipment controls the operation of the spacecraft. Excess thermal energy from the transceiver modules and on-Board equipment is transmitted by means of radiation heat energy into space. Moreover, the device of the spacecraft provides ample opportunities for the organization of the processes of allocation of excess energy into space. Thermal energy from on-Board equipment is a heat-sink-radiator located at the side of the hardware platforms. This radiator-emitter can be used to reset thermal energy from the transceiver blocks. When this excess thermal energy from the transceiver blocks is perceived by the coolant arterial heat pipes and diverted to the removal of thermal energy into space. In the event of a significant amount of thermal energy that is subject to disqualification from the transceiver blocks, excess thermal energy from them can be abstracted into space through additional radiators-radiators placed at the ends of frames frames antenna phased array or on the back of the casing sections. Declare section phased array antenna operates as follows. When working antenna phased array preempted the possibility blocks generate high frequency pulses and through emitters perform transmission and reception of electromagnetic signals. When this transceiver modules and the emitters emit thermal energy. Section phased array antenna having a large area, also perceives the heat radiation from the Sun and from the Earth. Heat pipes placed inside the placeholder inner panel outer skin carry out taking thermal energy from the transceiver blocks and transfer it to the exterior in relation to section phased array antenna means radiation of heat into space. The placement of the transceiver blocks on the inner panel is made of aluminum alloy provides in addition, the redistribution of energy over the entire area of the antenna of the phased array. The frame section of the phased array antenna contributes to the redistribution of thermal energy over the entire area of the antenna phased array. Layer screen-vacuum thermal insulation of the front casing isolates the outer panel of the front casing from the inner panel. When the outer panel with regard to the fastening of the panels to the frame using fastening elements with low thermal conductivity is thermally isolated from the rest of the design section of the phased array antenna and remains geometrically stable modules phased array antenna in flight. The claimed space is static device and the section of the phased array antenna can be manufactured at the enterprises of rocket and space industry. 1. The spacecraft containing the antenna phased array airborne early warning grille, made in the form of pivotally connected with each other by two flat rectangular sections, each of which is equipped with a front panel installed on provided with transverse structural members of the frame, the modules phased array antenna, comprising the radiators located on the front sides of the front casing, and transceiver blocks on the rear sides of the front covers, in addition, the spacecraft is equipped with on-Board service equipment, solar cells, fuel system with the fuel tank, while the hinged connection of the sections of the phased array antenna to each other is made with the possibility of folding sections, right sides to each other during insertion of the spacecraft into orbit and deploy partitions in space butt to each other, characterized in that the solar cells placed on two rectangular solar cells, each of which is pivotally connected to one of the sections of the phased array antenna, and the hinged connection of solar panels with these sections provides the possibility of placing solar panels between these sections during insertion of the spacecraft into orbit and deploy solar panels in space, each frame is of the second section of the phased array antenna is made in the form of a frame with a rectangular outline, connected to the transverse structural members, transceiver blocks are placed in the openings of these frames, and the section is further provided with systems management, including arterial heat pipes placed inside the front covers of these sections and thermally connected to the removal device thermal energy into space, with each section of the phased array antenna equipped with a hardware platform that is installed from the back side of the section with a gap relative to the frame skeleton of this section and fixed to the contour of the frame, and the side of the service equipment is placed in the gap between hardware platforms and frames of the frame and fixed to the inner sides of the hardware platforms, and the outer surface hardware platforms made in the form of radiators-radiators. 2. The spacecraft according to claim 1, characterized in that the system control sections provided with collector heat pipes, placed on the back sides of these front casing near one side of the frames, and arterial heat pipes are placed perpendicular to these sides of the frames with thermal contact with the collector heat pipes. 3. The spacecraft according to claim 2, characterized in that the control systems s is s equipped with evaporative heat pipes, thermally connected to the collector heat pipes and device removal of thermal energy into space. 4. The spacecraft according to claim 3, characterized in that the evaporative heat pipe thermally connected to hardware platforms. 5. The spacecraft according to claim 3, characterized in that the removal device thermal energy into space made in the form of additional heat-sink-radiator thermally connected to the evaporator by the heat pipe. 6. The spacecraft according to claim 5, characterized in that the additional radiator-emitter placed along the end of the skeleton frame, at least one of the sections of the antenna phased array. 7. The spacecraft according to claim 5, characterized in that the additional radiator-emitter on the rear side of the frame frame, at least one of the sections of the antenna phased array. 8. The spacecraft according to claim 1, characterized in that section of the phased array antenna is further provided with a rear casings connected with the frames of the frames of the sections of the antenna phased arrays, with at least part of the surface of the rear casing is made in the form of additional radiator emitter. 9. Section phased array antenna containing made in the form of a rectangular frame, the frame including a transverse load-bearing elements and the circuit, made of channels installed on the front frame lining, modules phased array antenna and control means, characterized in that the frame is made of channel bars closed rectangular profile, equipped with an additional internal jumper located near the mid-height profile, the front casing composed of two three-layer panels, between which is placed a layer of screen-vacuum thermal insulation and load-bearing layers of the outer panel is made of carbon fiber, filler made in the form of hundreds of non-metallic material, and the bearing inner layers panel and filler, made in the form of a honeycomb made of aluminum alloy, with sheathing panels fixed to the inner jumper the channels of the frame by fastening elements made of a material with low thermal conductivity, modules phased array antenna made in the form of emitters installed on the outer panel, and transceiver units installed on the inner panel of the front plating in the openings of the frame frame, and the aforementioned control means made in the form of heat pipes, missed inside the placeholder inner panel.
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