Present invention refers to the sphere of radio engineering, in particular to space large size expandable antennas.

There is known an expandable reflector [1], which comprises a reflector frame, provided with expanding device and supports of antenna feeding source. The reflector frame is made in the form of a folding reinforcement ring, and the reflector feet in the form of telescopic elements. The reflector supports by one end are hingedly connected with the reinforcement ring, and the other ends have common hinge unit.

The short-comings of such a reflector are the following : 1) the lack of reflector expanding reliability, which is caused by hinge connections with each other and reflector frame ; 2) the elasticity of the reflector and feeding source supports, which on its side is caused by existing of a backlash in the joints and by small cross section of elements in the unit area, that is limited by the requirement of minimal volume for transport pack ; 3) low preciseness of reflector surface and focal container mounting resulting from elasticity of reflector frame and feeding source supports and in the case of fixing of a reflector elastic net to the dot frame the surface deviation from theoretical parabolic caused by existing of the reverse buckling effect.

There is also known an expandable antenna [2] the nearest technical solution to the present invention, which comprises reflector frame provided with expanding device and feeding source supports. The reflector frame is made in the form of hinge-bar structure, and the reflector supports is made in the form of telescopic elements.

The negative properties of the antenna are : 1. small reliability of antenna expanding, resulting frc ; n the friction movement of frame elements to each other, particularly of the supports to the reflector frame and to each other and from plurality of mechanical hinge connections of the elements, working of the joints of sliding friction of the telescopic support elements ; 2. elasticity of antenna frame, caused by the elasticity of feeding source supports with each other and with reflector and namely with the reflector frame elements. resulting from the existence of backlashes in the fixed hinges and from limiting of the bar sections gathered in the joints regarding the minimum volume of the construction transport pack and transformation conditions ; 3. small preciseness of the reflector surface and feeding source mounting, caused by the possibility of frame hinge units and elastic reflector shelf mounted thereto deviation from design state, that greatly reduces the possibility of repeating the form. The reverse buckling occurs only in the case of dot fixing of the reflector elastic surface ; 4. large weight of antenna construction ; 5. complexity of antenna construction, resulting from the plurality of units and bar elements in the construction.

The purpose of the present invention is : 1. High reliability of antenna expanding, that is achieved by providing the antcnnn construction frame with radial ribs, diaphragms, elastic elements, pneumatic containers and inflating gas, i. c. on the stage of expanding the changing of the form of these elements is conducted on basis of elasticity under effect of compressed gas, the absence of mechanic units provides for high reliability of expanding, using main and additional expanding devices ;

2. High rigidity of antenna frame, that is achieved by using in the antenna frame radial ribs, diaphragms and elastic elements as carrying elements, by connecting with each other and with other elements without hinge, i. e. without backlashes ; Besides, these elements make rigidity ribs, which have big moment of inertia, among them-pneumatic containers, which also have big moment of inertia, the placing of pneumatic elements, which after solidification become the rigid shells, cyclic two-layer rigid shell having rigid ribs, the rigidity of which is high enough.

The feeding source supports, in the form of rigid elastic element cylindrical shell, in which the elastic elements act as rigid ribs, are characterized by high rigidity ; 3. High preciseness of antenna reflector surface, that is achieved by absence of hinges in constructions of the reflector, the reflector frame and feeding source supports, that enables to obtain high rigidity and preciseness of reflector frame and feeding source supports. Due to absence of mechanical hinges the high preciseness of repeating the form of the construction is achieved, that is quite low in the case of existence of the hinges.

The high preciseness of reflector surface is achieved by reducing the effect of reverse buckling, in particular by fixing reflector elastic shell to the radial-paraboloidal contour, radial ribs to the linear band subframe stretched between them, the contours of fixing to the reflector, elastic shell of which coincides with theoretical paraboloidal with high preciseness.

The preciseness of antenna for a long period is achieved by solidification of pneumatic containers, which excludes the deviations caused by changing of the pressure.

The antenna preciseness is achieved by placing of the antenna frame in the thermal insulation layer, by means of which is achieved subzero temperature on the frame elements, i. e. sign inverted subzero temperature is avoided, that is the sign inverted temperature are excluded and respectively the temperature and creep deformations are drawn to the minimum ; 4. The small weight of antenna construction, which is achieved by using in it of the thinwall tensed elements, absence of mechanic units, by using compressed gas as an expanding device, as a fixing device by solidification of pneumatic containers impregnated with the same polymer by means of gas ; 5. The simplicity of antenna construction, which is achieved by using hingeless sheet radial ribs and pneumatic containers for building, by using gas as an expanding device, as a fixing device using the space vacuum effect or by solidification of polymer pneumatic containers by means of inflating gas.

Besides the above mentioned the following technical results are also achieved : -in order to provide with electric power, it comprises expandable solar batteries constituted of panels, by means of which antenna can exist in off-linc condition, like an artificial satellite, operating as off-line power supply. As an expanding device for solar batteries a construction of feeding source supports is used ; -reducing of the temperature effect, which is achieved by placing antenna frame in light and heat conducting thermal insulating layer ; -reducing of temperature effect, providing with power supply, reducing the weight, simplification, that is achieved by placing antenna frame in the layer of elastic soiar batteries

which act as thermal insulator, as well as solar batteries, does not require a special expanding device, that is an additional weight for antenna ; -provision of expanding process reliability, which is achieved by adding expanding device to radial ribs, provided with toroidal or other kinds of pneumatic containers. On the stage of expansion in the case of loosing the hermeticity by pneumatic containers the expansion of radial ribs is provided with additional expanding device in the form of pneumatic tores ; -the reducing of the weight, the volume of the transport pack, which is achieved by making the pneumatic containers with through zones in the peripheral or whole area.'1 he material expenditure is reduced, as well as the volume and weight ; -the preservation of the fixation of the form, increase of function reliability is achieved by solidification of polymer pneumatic containers under the effect of space vacuum or. gas, whereas at the solidification process, which goes on better at above-zero temperatures. In order to obtain above-zero temperature by conducting the electric power, the pneumatic containers are provided with metal net. After solidification the metal net and solidified polymer act together as a reinforced composition material ; -the weight reduction, which is achieved by impregnation and solidification of separate areas of pneumatic containers. The material expenditure is reduced in result of which a solid bar structure shell is obtained ; -the preciseness increase is achieved, by that in central part of antenna a rigid reflecting mirror having high preciseness is fixed ; -the increase of reflecting elastic shell preciseness by reducing reverse buckling effect, that is achieved by providing band subfarme between the radial ribs, the elements of which are in tensed state and receive the tension voltage of elastic reflecting shell ; -the increase of focus, feeding source preciseness is achieved by providing the rigidity of feeding source supports connecting unit, obtained by immobile connection of support elastic elements on the section line, or their fast fixing onto the rigid disc. By means of the said unit high rigidity of the unit is achieved as well as of the feeding source supports, particularly this unit is the analog of reflector connecting unit, provides fur rigid and not hinge placing of the support, which reduces its calculated length and respectively elasticity, i. e. stability index improves, which enables to focus high preciseness ; -the reliability increase at transportation of the antenna to the orbit is achieved by resting the transport pack on the support made in the form of pneumatic tores. The pneumoconstructions can damp the dynamic loads well, which results in reducing impacts on the antenna transport pack and respective displacements ; -the increase of antenna diameter taking into account the limitation of transport pack volume and weight, which is achieved by using pneumatic tores as the main and additional expanding devices connected with each other only by peripheral multilayer, inclined in respect to each other pneumatic cylinders, having elastic diaphragms. The radia) ribs are made with thin film, which can be winded as well as folded.

The offered technical solution provides for reducing the price of the communication system and increasing the reliability.

The reducing of the price is achieved by, that in result of construction simplification and reducing of the weight the expenses for its manufacture, transportation and exploitation

are reduced. The high reliability of expanding the construction in the orbit and increase of the mounting preciseness of reflector surface and focal container enables to reduce the length of working wave, i. e. to increase frequency, that on its side reduces the weight and cost of signal receiving-transmitting apparatus and increases the service quality and number of users.

The said construction of parabolic antenna enables to achieve the mentioned effect.

The construction comprises a reflector frame provided with the device of expanding and fixing of a feeding source and elastic reflector shell. The construction is characterized with new features, in particular, the expandable parabolic antenna represents elastic radial ribs 5 fixed to a drum 4 and diaphragms 6 disposed among them, and the supports of feeding source are made of elastic elements 7 connected in the longitudinal direction with the possibility of turning in respect to each other, whereas each support 2 from one side is connected by its elastic elements 7 ends with the radial ribs 5 of reflector frame 1 and diaphragms 6, and from the second side-to on e another motionless, and the expanding device of antenna represents pneumatic containers 8 and 9 fixed between the reflector frame 1 radial ribs 5 and elastic elements of feeding source supports 2.

The antenna is provided with expandable solar batteries 11 constituted of panels 10, and expanding device represents the construction of antenna feeding source support 2.

The thermal insulation elastic layer 12 is fixed to antenna frame.

The elastic solar batteries layer 13 is fastened to antenna frame.

The antenna is provided with additional expanding device 14, with toroidal or other kind of pneumatic containers.

The pneumatic containers have different outline, whereas in the vicinity of the reflector pneumatic containers are made in the form of cantilever 15, or on the whole area of reflector-in the form of through-zone pneumatic containers 16.

The outer surface of the pneumatic containers are impregnated with anaerobic polymer 17 solidified in the space vacuum conditions, besides the inner surfaces of pneumatic containers are impregnated with one component of two-component polymer, and the other component 18 of the polymer is a material 18 which must be sprayed as an aerosol onto the first component or gas for filling up the pneumatic containers, the pneumatic containers are provided with electric power conducting metal net 19.

The separate zones constituting a solid bar structure shell 20 of pneumatic containers are impregnated with polymer.

The rigid reflecting mirror 21 is attached to the central drum, the diameter of which is less than the inner diameter of space ship transport module.

The radio waves reflecting elastic shell between the ribs of the reflector frame is provided with band subframe 22 placed in the orthogonal plane in respect to the shell, and along with the ribs with the tacky band 23 covered with the Him dry at mounting stage, having the length of rib parabolic contour, for fixing the ribs on the frame, whereas the dimensions of wedge-like pieces 24, constituting elastic rellector shell are selectcd so, that elastic reflecting shell stretched over the ribs and subframe in operation state is stretched uniformly in radial and circular directions.

The feeding source elements intersecting at the antenna axis of symmetry are connected fast on the section line, where the feeding source is fixed, and the remaining

elastic elements and pneumatic containers are either in the free state, or altogether are connected motionless with the rigid disc 25.

At the stage of injecting in the orbit the transport pack is placed on pneumatic supports 26.

The ribs of reflector frame are made of elastic films 27, the expanding pneumatic tores of which are made in several layers, connected with each other with the possibility of turning, vertical and inclined pneumatic cylinders having elastic elements, between which pneumatic containers are fixed, whereas the elastic elements of pneumatic containers fixed on the pneumatic tores and of the feeding source supports are connected with each other motionless, pneumatic containers are sealed to each other.

In transport position the radial ribs and pneumatic containers placed between them are winded to the drum, and the feeding source supports 2 are folded or winded and placed on the winded reflector. The expanding of antenna is carried out by filling up of pneumatic containers 8, 9.

In the case functioning as an artificial satellite the antenna, in order to reduce electric power expenditure for supplying radiotechnical, stabilizing and control apparatus and to increase the reliability of electric power supply, is characterized with a new feature, particularly it is provided with expandable solar batteries constituted of panels, which are fastened to the antenna frame.

The solar batteries in order to facilitate the corresponding area and orientation, can be disposed on the antenna non-operation surface, periphery on the feeding source supports, on the axis of antenna symmetry and in the planes passing the supports axes, on the focal container. The solar batteries may undergo one-fold, two-fold or three-fold transformation, whereas a expanding and retaining device can be used construction of antenna feeding source support 2 or the pneumatic cylinders, that increases the expanding reliability of solar batteries.

The solar batteries 11 folded in the transport pack are placed on the outer surface of folded antenna and at transportation stage serves as a tie.

The thermal insulating layer 12 is fastened on the antenna frame in order to provide the reliability for antenna, i. e. to provide for the preciseness and constant raeliotcchnical parameters during long term period.

As it is known, orbital among them the communication system term is defined by 5 and more years. The hard conditions of space, especially temperature changes on the sun and shadow sides (150 ° C), effect greatly the mechanical indices of the construction.

It is well known, that at such conditions, for long period in the conditions of temperature changes there develop creeping deformations, that change their geometry, in our case the antenna preciseness, i. e. radiotechnical parameters. To reduce the temperature factor the light and lieat resistant laycr as an clastic material, which has good thermal insulating properties and is fastened on the construction so, that to include maxima ! number of construction elements inside, if it is radio conductor, the reflector surface can also be placed in it. So the thermal insulator 12 provides the constant subzero temperature on the construction, that will greatly reduce creeping deformations. It is possible to use elastic material along with thermal insulator or apart from it, which is also covered with the layer (solar elastic batteries 13, photocells) absorbing the solar beams and transforming them into

electric power, which parallel to thermal insulator function will act as solar battery. In the case of need, to facilitate the electric power supply of the system the elastic as well as folding solar batteries can be used, that will increase the reliability of antenna electric power supply.

The expandable parabolic antenna is characterized by a new feature, in particular in order to increase reliability at expanding stage, it is provided with additional expanding device 14.

The only obstacle at the process of expanding is the loss of leak-proofness, that can occur due to some unexpected reasons or at hitting the antenna by meteor. At small damages damages, the expanding stage from releasing of the rocket carrier body until complete solidification of pneumatic containers is provided with certain reserve of inflating gas, which facilitates the preservation of constant working pressure in damaged pneumatic containers.

At large damages the expansion may not occur. For this possible case antenna is provided with independent pneumatic tores, which cross the radial ribs so, that after expansion they facilitate the resistance and rigidness of the rib. In the second case antenna along with main pneumatic containers on the periphery is provided with pneumatic tores fixed on the reflector radial rib.

The expandable parabolic antenna is characterized with a new feature, in particular, to reduce the price its weight is being reduced. The expenses at injection it in the orbit and functioning are reduced, on the stage of stabilization in expanded position and control. The weight reduction is achieved by reducing the total area (mass) of pneumatic containers. In the peripheral part, where along with the increase of the antenna diameter the distance between ribs increases and respectively the area of pneumatic containers, this latter has high lifting point, that creates linear cantilever element with pneumatic containers having small area. The pneumatic containers may have through zones, in which there can be made antenna reflector surface or elements having other appointment. The expandable parabolic antenna is characterized with a new feature, in particular to fix the expanded antenna the pneumatic containers are impregnated with polymer 17 solidified in the space. Such materials are rarely met in the conditions of space, though this year American astronauts expanded pneumatic construction, which was solidified. The said technology and the material parameters are not known to us. From the literature [3], there are known materials, which are solidified in the space by cold, heat, vacuum, ultra-violet and infrared irradiation, vapor, etc. From the mentioned the most efficient is the vacuum, as it does not depend on the construction orientation and respectively on additional expenses.

We offer to use anaerobic adhesives and hermetic in the said technology. The class of these adhesives and hermetic is known, the appointment of which is to adhere or seal the elements. The adhering-solidification is conducted by snuggling of two surfaces against one another, i. e. by removing the air from the space between them. The air is drawn automatically from the surface in the vacuum ; i. e. in the case of injection is in the space. By using this factor the application of anaerobic adhesives and hermetic with new appointment is achieved, particularly the fabrics impregnated with them in the conditions of earth (atmosphere) preserve elasticity, but at injection in the space (vacuum) they solidify and create

construction material. In the second case it is possible to use two-component polymeric adhesives, e. g. epoxy adhesives. In particular, epoxy two-component adhesives after mixing the components begin to solidify and adhere. The application of epoxy adhesive with new appointment provides for applying one of the components on the inner surface of pneumatic containers, and spraying the other component as an aerosol by means of filling gas.

The other component may be a component in the state of gas. In this case the inflating and solidification will be conducted only by means of this gas.

It must be marked, that all these processes are carried out efficiently only at plus temperatures and at subzero temperatures these processes become complicated.

The construction is characterized with a new feature, in particular to increase the solidification reliability in the zone of subzero temperature the pneumatic containers are provided with metal net in which by conducting the electric power the plus temperature is created.

In the case, when the carrier layer is a fabric, and the polymer applied on it acts as air-resistant layer, the metal net can be included in the fabric structure as well as in polymeric layer.

In order to reduce the mass of the applied polymer pneumatic shell, and in the whole of the antenna with the polymer is impregnated not the pneumatic shell totally, but its separate ones. For example, it is possible that the solidified construction takes bar shell structure.

The expandable parabolic antenna is characterized with a new feature, in particular with increased preciseness of reflector surface, that on its side gives the high quality of the signal, the reliability increases and the price of the system is reduced. The said effect is achieved by that on the antenna central drum 4 the rigid reflecting parabolic mirror 21 is fixed fast. The paraboloidal mirror, which changes the central part of antenna elastic reflecting surface. The mirror, i. c., the antenna central part has high preciseness, that is most important in the antennas of this type. Besides, the mirror diameter is limited by the dimensions of transport pack. The mirror is a support for the feeding source folded supports 2, at the stage of transportation.

The elastic radial ribs at transformation stage doesn't touch the mirror surface that is out of operation, as the central drum has a certain taper, directed to the focus. The taper is selected so, that the radial ribs the height of which decreases to the periphery and in the winded position with the lower contour bears against cone, pack support plane i. e. the upper operating contours of the ribs displace in regard to the plane of mirror fixing to the drum, so it extends from the mirror. Thus according to the expanding trajectory the rib doesn't touch the mirror. In the case of accidental touch there is no obstacle as the said surface is even and catching is excluded. Whereas, by means of the mirror the commutation can be conducted, that will enable to avoid conductors, which at subzero temperature may become fragile.

On the remaining area of antenna reflector elastic shell among the radial ribs the reverse buckling effect occurs, the deviation of the elastic reflector shell 3 from the theoretical parabolic in the direction of the focus. In the present antenna construction the main reason causing the inaccuracy of the reflector is the said effect.

In order to reduce to minimum the deviations caused by reverse buckling effect the elastic reflecting shell 3 between radial ribs 5 is provided with band subframe 22 disposed in the orthogonal plane to the surface, and along the ribs with tacky dry film having the length of paraboloidal contour, for fixing to the ribs.

Whereas the dimensions of wedge-like pieces 24 of elastic reflecting shell are selected so, that the reflecting shell over the ribs and subframe in operation state is stretched uniformly in radial and circular directions.

From the three components of rotation surfaces, only the two are determining parabolic deformations, which are placed in the plane passing the axis of paraboloid symmetry, the third-in the circular direction is smaller and thus avoided.

The radial ribs of the antenna are disposed in the plane along the axis of symmetry, they develop the said two main components. The third circular component is insignificant and mainly depends on the identity of pneumatic shells.

The deviations in this direction are limited by means of reflector subframe.

To reduce the maximal deviations of the elastic reflecting shell caused by reverse buckling effect among the reflector radial ribs 5 the band subframe 22 in the orthogonal plane to the reflecting surface is provided, the configuration and geometry of which can be different. The subframe is prepared on a separate stand, where must be provided the outline of its elements, the tension and the connection of high preciseness of the contour, which must be fastened on the net.

The reflecting elastic shell is made ofd wedge-like triangular pieces 24, the connection contour of which is fastened on paraboloidal ribs. In order to provide for the uniformal tension of the reflector the separate wedge-like pieces are stretched uniformly on the plane in pairs in the direction of two axes.

Whereas, on the plane the flat spread of wedge-like surface is applied beforehand, which represents the triangle, the outliner of which suits the projection contour of the wedge. To the two pieces stretched uniformly on the plane, to the curvature side of the triangle the unstretchable tacky band 23 covered with polyethylene film is sewed so, that the polyethylene is on the free side.

Thus the whole reflector subframe 22 is made, which is fastened manually to the ribs. Particularly the reflector is expanded onto the plane with the subframe being on the upper surface, in respect to which the antenna is hung with its operating surface, the polyethylene film is removed from each cord 23 and is sealed to the ribs 5 in stretched position, on which the perforation is applied beforehand, for fixing the band by means of thread or wire.

The expandable paraboloidal antenna is characterized with a new feature, particularly the improvement of preciseness, radiotechnical characteristics, that is achieved by means of the new technical result-by high preciseness of the feeding source mounting.

As it is known, the preciseness of the feeding source must be about the same as of the reflector surface, that is the result of high rigidity of the connection of the feeding source support with the reflector support and with focal container.

The number of the feeding supports 2 and the diaphragms in each support, the construction and sections due to the configuration of the construction can be different, the antenna construction gives such a possibility. The connection of the reflector with the feeding source is conducted by means of elastic transformable unit, in which there is no friction and transformation mainly is conducted on basis of the elasticity of the elements. The feeding source supports are connected also with hingless mechanical unit, particularly in the first variant of the elastic elements, intersecting on the axis of symmetry of antenna supports, at the section line, where the feeding source is mounted, are fixed motionless in respect to each other. The other elastic elements and pneumatic containers 9 are in free position. In the second variant the elastic elements 7 and pneumatic containers 9 are fixed fast to the rigid disc 25, which is mounted perpendicular to the antenna axis of symmetry. Such unit provides for focal container high preciseness, i. e. has the increased resistance to torsion.

The said construction unit provides for rigidness, the preciseness of focus arrangement and free transformation of the support.

The supports of the mentioned kind and the connection unit enables to apply in the form of focal container substantially large mass in comparison with reflector weight.

The expandable parabolic antenna is characterized with a new feature, in particular, in order to increase reliability at transportation stage and to protect the transport pack from damage at injection in the orbit, the antenna transport pack is placed on the pneumatic cushions 26, the configuration of pneumatic cushions and its construction is selected so, that the vibroloads occurring at injection of the rocket in the orbit are reduced to minimum. The pneumatic cushions consist of several sections. At damaging of one or several sections the pneumatic cushion preserves the properties of a damper. The pneumatic cushion is mounted on the rocket body. The pneumatic cushion itself on the pack bearing surface is provided with a rigid disc, which excludes the displacement of the parts of antenna transport pack in respect to each other in vertical direction, the direction of rocket trajectory, and in the transverse direction the tie, e. g. rocket body has a same function.

The expandable parabolic antenna is characterized with a new feature, particularly in order to reduce the price and increase the reliability for 50 meters and more diameter the lightened construction is offered, in particular the radial ribs are made of elastic material and represents a frame member consisting of two symmetrical parabolic contours. Such elements are gathered in one center, and the peripheral contour is stretched by means of tores 14 system.

It must be marked, that expanding pneumatic containers are not placed among the radial ribs, but are disposed on the contour in the form of toroidal pneumatic containers. Such scheme enables the radial ribs to fold in minimum volume. Otherwise, the pneumatic containers have the weight more, than the toroidal pneumatic containers.

The ends of radial ribs are provided with pneumatic cylinders strengthened with elastic diaphragms, the number of which can be one or more. The tension of the diaphragms is

conducted by means of the said pneumatic cylinders by applying of pneumatic tores. The pneumatic cylinders for uniform stretch of the diaphragms and the connection of pneumatic tores. The pneumatic cylinders are mounted in respect to the pneumatic tores perpendicularly as well as inclined.

The elastic elements of antenna feeding source supports and of pneumatic cylinders are connected fast to each other, the pneumatic containers 8 and 9 are sealed to each other.

There is provided for solidification of pneumatic containers in the space.

The diaphragms have symmetric parabolic contours. The reflector elastic shell is fixed on the both sided of the reflector, that facilitates the diaphragm stability and the general rigidness of the antenna.

On the base of the offered expanding parabolic antenna construction there can be built parabolic, as well as spherical, hyperbolic, flat and other kinds of surfaces, the appointment of which is different. Whereas the rigidity drum can be planned as in its center, so in its any point including the periphery, that doesn't resist to the winding of diaphragms thereof. For example, the asymmetric circular, rectangular or other kind of sectors cut out from the parabolic, which is fixed to the space ship by means of the drum disposed on contour, at the other end the feeding source is mounted. In this case every rib and respectively every pneumatic shell has different outline. The expanding parabolic antenna is built with (0, 2-0, 8 mm) width elastic shell diaphragms and with air resistant fabric layer, or with pneumatic container materials covered with polymer solidified in the space. All of these materials must contain the module of high flexibility, high coefficient of expanding temperature and capability to reserve these properties for a long period in the interval of 150° C temperature. Besides, they must not loose elasticity under the-150 ° C temperature and other factors of vacuum in the space.

The special technology has been worked out to build the antenna.

The ribs on the central drum are fixed fast by means of rivels or adhesive. The contours of the rib are cut out in the uniform pack. On each contour are applied the contours for connecting of pneumatic shells thermal insulators, also for elastic solar batteries, as well as the perforation for fixing the reflector shell.

The pneumatic shells 8 are prepared by respective spreading, which corresponds to the form of soap membrane tensed on the given curvature contour, which is determined by the : corresponding calculation.

The expandable parabolic antenna is presented by the following graphic material : Fig. 1-antenna in the folded transport position.

Fig. 2-antenna in half expanded position.

Fig. 3-antenna in the expanded operating position.

Fig. 4-the cylindrical drum, fixed by means of radial ribs, in the expanded position.

Fig. 5-the same in the winded position.

Fig. 6-cone drum, fixed with radial ribs in the expended position, and the same in the winded position.

Fig. 7-the reflector fragment with radial ribs and additional diaphragms oriented unilaterally.

Fig. 8-the reflector fragment with radial ribs and pair of additional diaphragms.

Fig. 9-the reflector fragment with radial ribs and additional radial diaphragms.

Fig. 10-the reflector fragment with radial ribs and additional diaphragm unit, to which elastic elements of the feeding source supports are connected.

Fig. 11-the connection unit of the supports by means of rigid disc.

Fig. 12-the other variant of the cormection unit of the supports.

Fig. 13-connection unit of the feeding source support of the reflector frame.

Fig. 14-the feeding source support in expanded operating position.

Fig. 15-the first stage of support transformation, flat position.

Fig. 16-the second stage of support transformation, folding stage.

Fig. 17-the support transformation third stage, the turning of the ribs to each other by 90 °.

Fig. 18-the section of the antenna transport pack, with feeding source support folded spiralwise Fig. 19-the variant of the fragment of the embodiment of pneumatic container, when the pneumatic containers in the peripheral part along with radial ribs create the cantilever.

Fig. 20-the same figure in the section.

Fig. 21-the variant of pneumatic container embodiment with through zones.

Fig. 22-the same in section.

Fig. 23-the solidified variant of pneumatic containers, when the solidified zones create rigid bar shell with metal net.

Fig. 24-the same in the section.

Fig. 25-antenna in the expanded state with expanding solar batteries with expanding rigid panels fixed to the feeding source supports.

Fig. 26-antenna in the expanded state with expandable solar batteries, having rigid panels, mounted on the reflector perpendicular to the antenna axis of symmetry.

Fig. 27-antenna in the expanded state with expandable rigid panel solar batteries mounted on the reflector radial ribs parallel to the antenna axis of symmetry.

Fig. 28-antenna transport pack in section, with folded solar batteries with rigid panels fixed to the feeding source supports.

Fig. 29-antenna transport pack on the antenna axis of symmetry, with folded solar batteries, having rigid panels mounted perpendicular.

Fig. 30-antenna transport pack with rigid panel folded solar batteries fixed parallel on the radial ribs on the antenna axis of symmetry.

Fig. 31-the fragment of expandable solar batteries, hawing rigid panels, with longitudinal expanding device in the folded position, with expanding device of the feeding source support construction.

Fig. 32-the same at the initial stage of expanding.

Fig. 33-the at the intermediate stage of expanding.

Fig. 34-the additional expanding device to the rigid solar batteries, with folded pneumatic cylinders disposed along the longitudinal joints.

Fig. 35-the same at the initial stage of expanding.

Fig. 36-the same at the final stage of expanding.

Fig. 37.-the variant of solar batteries with rigid panels in the expanded operating position Fig. 38-antenna top view in expanded operating position, provided with elastic thermal insulation and solar battery layer, also with toroidal additional expanding device on the ends of radial ribs.

Fig. 39-the same in the section.

Fig. 40-the reflector in section with toroidal additional carrying expanding devices.

Fig. 41-the band subframe with circular elements.

Fig. 42-the band subframe with circular and radial elements.

Fig. 43-the band subframe with unilaterally inclined elements.

Fig. 44-the band subframe with bilateral inclined elements.

Fig. 45-configuration of the subframe element, the scheme of fixation to the radial ribs and reflector net.

Fig. 46-the scheme of mounting of the antenna reflector surface from wedge-like elements.

Fig. 47-the scheme of spreading the reflector wedge-like elements and their technological treatment.

Fig. 48 and 49-the scheme of fastening of band cord on two neighboring wedge-like elements at the stage of preparing of antenna reflector net.

Fig. 50-mounted reflector net with band cards on the connection contour of reflector net wedge-like elements.

Fig. 51 and 52-the section of reflector fragment with pneumatic containers, subframe element, thermal insulator, elastic solar battery.

Fig. 53-the antenna in folded position at injection stage in the orbit, the pack lays on the toroidal pneumatic containers.

Fig. 54-expanding parabolic antenna for the diameter more than 50m in the operating position.

Fig. 55-the rectangular variant of the expanding asymmetric parabolic antenna with the disposition in the peripheral part of the drum.

Fig. 56-the same in the round form.

The exploration term of the antenna makes 10-15 years and it can work in the receiving as well as in the transmitting regime.

By means of the offered structure can be built flat, spherical, parabolic and other surfaces, whereas the drum of rigidity can be placed in the center of the construction, as well as on its periphery.

The fig. 53 represents the sector construction cut out of the parabolic antenna, in which a drum 1 as a semi-cylinder is placed on the periphery, whereas the radial ribs are not similar, each rib has a different length and outline. Each pneumatic container is of different outline.

In the case of making of the central drum 4 in the form of the cylinder the winding of the radial ribs fig. 4 increases the pack height fig. 5.

The increment of the pack height from the drum surface is equal to the lifting point of the paraboloid. In order to reduce the pack height the drum is made in the form of truncated cone fig. 6. If the cone is selected respectively the height winded radial ribs is suited with the drum height fig. 6. It is possible to about the lower contour of radial rib on the surface of the drum base fig. 28, fig. 53.

To increase the reflector rigidity and reduce the concentration of the ribs in the central part the additional diaphragm 6 fig. 7 are used, the geometrical parameters of which are selected so, that do not resist to the winding process.

For the same purpose the pair of additional diaphragms are used in each sector, fig. 8 and fig. 9, in which in the case of existence of three clastic elements 7 in the feeding source supports a unit is provided for fixing of the supports to the reflector feeding source supports.

The section 6 line of the reflector radial ribs 5 and the diaphragms coincide with the supports 2 axis of symmetry. The elastic elements 7 of the diaphragm 6 and the feeding source support 7 have the possibility of turning in respect to each other as well as to the reflector radial rib 5, this is the important condition for the transformation of the unit fig. 10. As to the radial rib 5 and diaphragm 6, they are fixed motionless the elastic elements 7 of the feeding source support, and the bases are sealed to each other on the reflector and support pneumatic containers 9 by means of through opening, fig. 3.

The connection unit of the feeding source supports 9 must meet the conditions of stability and rigidness. As it is known, three bars crossed in one point gives the staticaly changing system. The fast fixation of the elastic elements 7 to the rigid disc 25 placed in focus enables to change the section point of the supports 2 axis, whereas the existence of three elastic elements 7 in each support 2 gives the possibility of practically rigid fixation to the disc 25. In the case of three support the stability is provided fig. 11. Besides, it is possible, that the elastic diaphragms of each support, which cross the antenna axis of symmetry, to touch each other fig. 11, or to cross each other fig. 12. In accordance of the concrete requirements in respect of the feeding source type the focal container can be arranged in different ways, among them fig. 11 and fig. 12. Whereas it is desirable that the feeding source supports were made of radio conducting materials. On the fig. 14 the construction of three elastic diaphragm feeding source support construction is shown. As it was mentioned above, we can have in the feeding source support one or more elastic diaphragms. The support with three diaphragms undergoes three-fold transformation. First, from the cylindrical form after turning of two elastic elements in the plane of the third transformation into the flat position fig. 15. Second, the transformation of flat element into the sinusoid fold position fig. 16 and third, the fold structure ends turning in respect to each other under 90 and torsion fig. 17,

this latter is caused by the torsion in result of by the 90 turning of the connection unit of the feeding source support with the reflector.

The transformation of the feeding source support after transferring into the flat position is possible by means of spiral scheme fig. 18. The antenna pneumatic containers represent the expanding mechanism of the construction together with the gas, and in the case of solidification they act as fixators of antenna form.

The form of pneumatic containers 8 must be selected so, that only the tension forces must act in them. Such form is acquired by uniformly tensed surface. All the elements of antenna are stretched the pneumatic containers 8, radial rids 5, diaphragms 6, elastic element 7, the tension forces of which is balanced by the compressed gas.

In the peripheral part the pneumatic containers constitute hyperbolic paraboloid.

Fig. 20 represents the cantilever elements in the section.

For long-term exploitation of the antenna in the orbit it is necessary to solidify the pneumatic elements. This requirement is stipulated by the difficulty of providing the hermeticity for long period.

The solidification of antenna pneumatic parts 8, 9 is provided for.

In the offered antenna the polymer is solidified by different method.

According to the solidification scheme, the polymer can be applied on the outer or inner surface of the pneumatic container, or the fabric can be impregnated, besides the fabric along with the function of impregnated polymer solidification will fulfill the function of gas conducting layer. The solidification can occur under the effect of vacuum.

In the case of supplying of the second solidifying component as the gas the infection as well as the solidification will occur.

In the case of use of the second solidifying component in the liquid form, the gas is still needed and the liquid must be sprayed on the polymer as an aerosol.

For the mentioned technologies the anaerobic and epoxy adhesives and hermetic are mostly available.

The anaerobic materials solidify in the vacuum by themselves. In the case of epoxy adhesive, the fabric is impregnated from the two components with one more viscous component, and the second comparably liquid component is sprayed thereof.

The weight of the solidified shell may reach 200 g/m2, which is the substantial mass in the case of large antennas.

In order to reduce the antenna weight the polymer is applied and solidified only on the certain zones. Fig. 23 shows the pneumatic container on which the solidified areas create the bar structure. Fig. 24-the same in the section. The weight of the pneumatic containers solidified in this way may be reduced by 50% and more.

In the case of antenna functioning in the off-iinc regime, it must be provided with electric power, that is important to preserve its orientation and also for functioning the radio apparatus mounted thereof. For obtaining the electric power the solar batteries are used as a rule.

Fig. 25 represents the scheme, when the solar batteries ! I for expansion arc fixed on the feeding source support in the plane passing the axes of symmetry of the antenna and support. The fixation of the panels 10 in regard of the scheme enables to reduce the oscillation period, the rigidness and preciseness of the feeding source support increases, the orientation improves besides they do not make additional obstacles for radio\\a\cs as they are disposed in the plane of the supports.

Fig. 26 represents the scheme, when the expandable solar batteries are connected to the surface of the antenna, that doesn't operate, in particular to the axis of symmetry. The advantage of the scheme is that the center of gravity of the solar batteries is close tu trac antenna gravity center and is fixed to the rigid drum.

Fig. 27 represents the scheme, when the solar batteries arc fixed parallcl on tlc reflector radial rigidity ribs, particularly, the solar batteries continue the radia ! ribs. The advantage of the scheme is that the panels are disposed in different planes which arc crossed on the antenna axis of symmetry, this greatly increases the chance of falling of ligh flow thereon.

Fig. 28 represents the expandable parabolic antenna folded pack in section, where tin- solar batteries fixed to the feeding source support along with the support are folded out of the reflector winded pack.

Fig. 29 represents the antenna transport pack @ in axonomctry, when the solar batteries are fixed on the central drum and the folding is conducted out of the winded reflector, in the vertical direction.

Fig. 30 represents the top view of antenna transport pack, when the soiar batteries represent the continuation of radial ribs and are winded to the reflector pack.

In every case discussed above the feeding source support construction is used as the expanding device for the solar batteries with one or more clastic elements.

Fig. 31 shows the fragment of expandable solar batteries with two folded panel and the construction of expanding feeding source support.

Fig. 32 and fig. 33 show the stages of expansion of the solar batteries.

In order to increase the reliability of expansion each pair of panels have independent expanding device in the form of pneumatic containers.

Fig. 34 represents the folded scheme, fig. 35 and 36-the stages of expansion.

Fig. 37 represents the axonometry of the expanded solar battery fixed on the centra) drum 4. As we see from the figure after expansion the feeding source support construction 2 acts as the carrier beam, whereas its elastic element 7 creates the rib of rigidity for the solar battery 11, which can be of different configuration. The number of the ribs can be increased if necessary.

As it is known the function term of the antenna in the orbit is defined by H) years and more. The temperature changes 150° C and other hard conditions cause creeping deformations, etc.

In order to avoid the said deformations the antenna construction is placed in the special light and heat resistant thermal insulation 12 shell, which is fixed on the radial ribs 5 so, that it includes therein the radial ribs 5, pneumatic container 8, 9, also the reflector net 3, fig. 38. This shell enables the antenna frame to be in the constant shadow, under subzero temperature, that will greatly reduce temperature as well as creeping deformations.

The terminal insulation layer instead of the common material can be made ouf plastic thermal insulation layer 13 covered with photocells. In this case this layer will act as a solar- battery and thermal insulator. The antenna is provided with expandable solar batterics 1 1 having the rigid panels.

Fig. 38 represents the top view of the antenna in expanded position, with thermal insulating layer and expanded solar batteries.

Fig. 39-the same in section. As it is seen from the figure antenna thermal insulation layer 12 and pneumatic containers 8 do not touch each other. Besides, the thermal insulation 12 layer is fixed so, that deformations caused by temperature changes do not transfer to the radial ribs 5, that can cause the rib deformation.

The additional expanding device 14, toroidal pneumatic containers can be disposed not only on the antenna periphery, but on the whole area of radial ribs fig. 40, which wilt change the wedge-like pneumatic containers 8. If one of the tores is damaged that will nut effect the antenna expanding process, the weight of the antenna increases insignificantly.

In the parabolic antennas having radial diaphragms in order to reduce the conventional reverse buckling effect of the elastic reflector, the subframe 22 is made under are reflector net, fig.3. The subframe elements consist of band elements made of the sheet material, which they are placed in the orthogonal plane to the parabolic reflector. The subframe structure can be different. Fig 41 shows the band subframe 22 with circular elements, Fig. 42-with circular and radial elements. Fig. 43 represents the elements inclined unilaterally. Fig. 44-elements inclined bilaterally. The band elements undergo the tension. that is why it is preferable that it has symmetrical contour. As the upper contour of the hand element is curved 5 and corresponds the line of theoretical paraboloid and crossection of the band elements, the second contour is symmetrical with the longitudinal axis of the band element, fig. 45.

The antenna reflector surface 3, is made with wedge-like elements 24, lig. 46. which are made with special tech ; zology. Whereas, the sublirame 22, is fixed to each wecdge-like element 24 beforehand.

Fig. 47 shows the scheme of making the wedge-like elements, by means of which the net is stretched uniformly, that is the main condition to receive high radio parameters of the antenna.

Fig. 48, 49, 50 show the mounting scheme of the wedge-like efcments 24 on their connection contour, with mounting cord 23 on the radial rib.

Fig. 51 represents the reflector sector in section, with solidified pneumatic container 20 between the radial ribs 5, with band element of the subsframe and thermal insulating layers 12. Fig. 52 represents the same.

The supports of the feeding source fig. 11, 12, 13, 14, 15, 16, 17 arc placed in the shell. The support of the feeding source consist of one or more elastic clement 7. which are

connected with the possibility of turning in respect to each other and in the operation position represent the cylinder, strengthened with rigid ribs.

In the case of 50 m or more diameter it is advantageour is radioal ribs expand and fix with peripheral pneumatic tores 14, which are placed in several layers. The ribs and pneumatic tores 14 are connected with pneumatic cylinders 2 having clastic elements, which provide for uniform tension. The pneumatic cylinder can be arranged inclined. I he feeding source supports represent the continuation of pneumatic containers and the number of the elastic elements therein is equal.

The winding of the parabolic antenna is conducted on the earth on the stand with radial directors, with the focus hung downwards position, by means of coin a) drum rotation in respective vertical direction. The radial ribs hung on the directors due to the attachment effect to the directors wind on the rotating central drum 4, whereas the reflecting surface and the area of pneumatic containers disposed below due to the earth gravitation are out of the radial ribs, and the back ones of the pneumatic containers 8 are disposed among them. In order to place the pneumatic containers completely between the ribs the air can be pumped out simultaneously with the winding. After this the expandable solarI'batterics 11 and thc supports 2 of the feeding source are folded, the pack will turn over with the focus upwards and the antenna is ready for transportation.

At the moment of injection in the orbit the antenna is separated from the rocket body.

At this time the gas conduit placed on the central drum is in the open position, in order to remove the antenna from the gas left in the pack. Otherwise the rest of the gas may cause the antenna inflaction at the injection stage, and after the separation from the body may cause the blow, that is not desirable, as the pneumatic containers can be damaged, or the antenna may receive the turning moment, the stabilization of which is connected with certain difficulties.

After removing the pack from the body the gas conduit is closed and hte controlled supply of gas to the pneumatic containers start simultaneously, the expanding of the reflector, the feeding source supports and solar batteries is going on. After receiving the operating pressure in the antenna the gas supply is stopped, and by means of special

detectors the gas is supplied when the pressure is low, and the valves are open if the pressure is high. The central drum 4 is provided with gas reserve, which supplies the constant pressure in the pneumatic containers until their complete solidification. After which the gas conduit is opened and the antenna is emptied of the gas by means of the special clevice. is aimed on the object and is ready to function.

Reference : 1. US Patent N 3576566, IPC H 01 Q 15/20 ; 2. US Patent N 3618111, IPC H 01 Q15/20 ; 3. Compositional Materials in the Constructions of Dying Vehicles. Edited by A. L. Abibova, M., Machinostroenie, 1977 (Rus),.