A variety of deployable reflectors for the use in large size space antennas have been proposed heretobefore, either as patent inventions or designs or real constructions installed either on the earth or in the space. The reflector types, such as"ATS-6","KPT-10", or various space antennas proposed by the companies"HARRYS"and"ASTRO"as well as the design"Reflector" created in Georgia and jointly tested by Georgia and Russia in the outer space on July 23-38, 1999 on the orbital space station"MIR"are just a few examples of the mentioned reflectors which should be noted herein for the purposes of reference.

Creation of optimum design of deployable reflectors for the use in large size space antennas, however, still remains a problem. In the practical point of view, umbrella like systems, with ribs, as well as rim like systems gain advantage and the reason of this fact is dully motivated.

Rib provided umbrella shape reflector design has considerable advantage due to the deployment reliability, simple design and accuracy of contours of the ribs. These advantages are particularly apparent in the deployable rib-umbrella reflectors having entire ribs designed so that they do not fold locally. The ribs are radially interconnected, are deployed by a common mechanical means and have a common fixation. These advantages are significantly reduced when each of the rib is unable to fall within the allowable dimensions of the folded reflector package by reason of its own length. In such cases"breakings"are needed to be made in special hinges and this is why the design becomes much

more complicated. In addition, mechanical means become needed for deployment and folding in"breaking"points of each individual rib which in turn makes the design more complex and reduces, at the same time, its deployment reliability, yet stiffness and accuracy.

Many designs that are analogous to the rib-umbrella shape reflector antennas have been proposed, such as disclosed in the patent 2945234 (H01Q 15/20,1958) which is comprised of rigid ribs deployable with cantilevers and fixed in a central unit. The ribs have outline similar to that of the reflector attached thereto. Such ribs are arranged radially and collected at the central unit. The length of the structure in the folded state is the main limitation for the overall dimensions of the deployable reflectors made of the whole rigid ribs.

This limitation is conditioned by the requirement of the length of the rib which must not exceed the length of the folded antenna package.

Another patent which should be mentioned herein is 5446 474 A (HOlQ 15/20,1995). This patent describes the ribs having the size which exceeds the dimensions of the package. These ribs are made of the flexible-non-rigid (deformable) single members allowing to be wound in a determined form, whereby the ribs are able to accommodate in the dimensions of the stowed reflector package. The frame with windable flexible ribs has very little stiffness in its fully deployed state when the ribs are radially expanded. To provide higher stiffness, many attempts have been made including provision of different shapes of cross sections of the individual ribs, yet the use of a variety of materials. In addition, the more stiffness can be achieved also by making design modifications.

The patent 3286259 (HO1Q 15/20,1964) discloses a design wherein the spiral forms of the ribs are proposed instead of the radial arrangement thereof.

Not being fully expanded in this state, each rib keeps the elasticity energy accumulated therein. The fixation of the ribs is performed by the reflector which is in deployed state by the same ribs. The frame obtains much more

stiffness being in such a tensioned state.

Despite numerous attempts, enlarging the reflector, which have entire ribs, in size causes increase in weight, decrease in accuracy and drop of the stiffness.

In view of the above-described problems numerous designs of the rib- umbrella shape reflector frameworks have been proposed wherein folded ribs with a variety of connections between them are provided. The analogs of such designs are as follows:-4, 5,6, 7, and 8.

"Advanced Deployable Reflectors for Communications Satellites", American Institute of Aeronautics and Astronautics, 1993.

In the above mentioned analogs, despite the variety of constructions a common principle of mounting, folding and deploying the rib-umbrella shape deployable reflectors are preserved with the use of foldable ribs.

Generally, the rib-umbrella shape reflectors with different shapes of their individual ribs give very good opportunity to construct offset type reflectors.

This is due to the necessity of different size and shape members to achieve profile of the approximated surface of various sections of reflectors having dissymmetrical double curvature. This is why, when the rib-umbrella reflectors is made of the ribs which are not fixed in any point other then the central unit it becomes simple, in principle, to make these ribs which will have different sizes and shapes.

Despite the availability of analogs mentioned herein and the variety of design solutions for the rib-umbrella shape reflectors many problems still remain, as already have been stated above, in connection with their use in large size deployable space reflector antennas.

Consequently, very often deployable rim systems having tensioned frame for attaching the reflector thereto become preferable in large size deployable reflectors.

This approach has been applying long time and a variety of design

solutions, inventions, scientific works, and experimental constructions have been creating, including operable designs launched into the space orbit.

Principal diagram of deployable rim systems is comprised of a deployable rim and flexible framework attached to the rim from inside. The framework is deployed from its stowed state by deploying the rim and is tensioned in its final state by the same rim. The tensioned framework creates the contours of approximated surface having the form of the antenna reflector, whereto a flexible reflector is attached. Many solutions have been proposed as to the individual designs of deployable rim, its deploying energomechanics, synchronization of deployment, fixation of the form in deployed state and the main thing is that various designs of tensioned flexible frameworks and attachment means for attaching the deployable reflector to the spacecraft have also been provided. With this respect, many analogs may be referred to herein including those consisting of a rim and a tensioned framework attached thereto, though not being deployable reflectors. However, these systems which were created many years ago became the basis of modern deployable rim systems.

Still another patent document which should be referred to herein is Author's Certificate 402970 (Framework of a Mirror Antenna Reflector) The framework comprises two"tyres"connected to one another by means of rigid struts. Each tyre is a polygon and is comprised of rigid rods. The rigid rods and the rigid struts of the"tyre"are connected to one another by means of hinged joints. Within the hinged joints, elastic rods are fixed, being tensioned in the center. Metal cables can be used as the elastic rods. Elastic connections are made as a ring and are forming a"web". To obtain the necessary parabolic shape of the antenna, the elastic connections are tensioned to one another by means of the elastic rods arranged in parallel with the rigid strut. Also, elastic rods are applied to avoid the twisting of the"tyres'. Such a framework is connected to the rotative devices by attaching it to a rim.

The inventions of the later period are connected with attempts to reduce

the deployable rim weight; to increase its stiffness and accuracy, upon which the accuracy of the reflector shape still remains depended in deployable rim systems; to enlarge sizes, accuracy, and stiffness of the frame tensioned by a rim and to which the reflector is attached.

However, principal novelties in deployable rim systems are not achieved.

A recently published patent EP 0959524A1 (US 6028 570, H01Q 15/20,1998) can be an illustration of this fact.

The main difference from the above-described Author's Certificate 402970 is that the deployable rim with enhanced stiffness is reduced in weight which is capable of enlarging partially the dimensions of the tensioned frame both inside the rim and outside the one to the extent possible by the design peculiarities. In addition, design of the rim, though to the limited extents conditioned by the design of the rim, allows to make improvements to obtain more convenient frame of the offset reflector surfaces.

In accordance with the above-mentioned patent application the design of the rim is extremely complicated and overloaded with mechanical units, hinges, rods, connections, etc. All of these factors have particular effect on the precision of the deployable ring project position and, of course, on the reliability of deployment. If we discuss the rim having the diameter of 15 meters with full length at the perimeter exceeding 45 meters it could easily be imagined, in the instance of hundreds of units and rods, as well as thousands of members fastened with one another by hinges, how this kinetic system will make it difficult to obtain the high accuracy contours which, in turn, creates the antenna reflector geometry, where the skewness at the surface is limited in most part, and is measured in millimeters and its tenth parts.

On the other hand, the above-mentioned analog retains the properties characteristic to the rim systems and the tensioned frameworks thereof.

In up-to-date inventions the deployable rim systems, including the above-mentioned analogs, have the same disadvantages in the system and

principal point of view, and they are divided into three groups, namely: - disadvantages of the tensioned flexible frame; - disadvantages of the deployable rim; - common disadvantages of the deployable rim systems.

The disadvantages of the tensioned frame are as follows: - lateral dimensions of the tensioned frame, which is defined by spacing apart the ends of the opposite flexible members, is too large.

Increase in its length in nonlinear way as compared with the increase in the reflector size is related with many negative consequences, namely, the height of the transportation package and the weight of the frame are increased, stiffness is decreased and obtaining high accuracy surface of the reflector becomes difficult.

- making of the tensioned frame, frame for attaching the reflector, and the frames opposite to the reflector, of elastic rods causes decrease in tensioned frame stiffness, and moreover, because of their local deformations, some problems are arisen in connection with attachment of the reflector and the local accuracy of the reflector shape. Degree of deformation and related deterioration of surface accuracy as well as difficulty of making the design are increased in the instance where elastic rods are again the connections for the opposite frame. In other instances, where these connections are effected by the stiff rods problems relating to reliability in process of deployment arise as any elastic rod may wind round the ends of the stiff rod.

- Adjustment of the tensioned frame surface geometry when the frame is made of flexible rods, i. e. the rods working in only a tensioned condition, is practically impossible, is not reliable and/or it is extremely difficult and causes some technological problems to be arisen.

- frame made of flexible rods with its tendency to deformation which extent beyond all allowable limits in exertion of unbalanced and driven forces makes the reflector impossible to attach to a spacecraft thereby arising additional problems in connection with orientation and control of the reflector.

- typical spatial structure design of the tensioned frame made of flexible rods arises additional problems in dissymmetrical offset shape reflectors as concerns the achievement of necessary geometrical accuracy. This is reasoned by reduced capabilities of performing typification and unification in manufacturing process in terms of the use of individual parts or members and in terms of their manufacturing and assembling technology as well.

In addition, big height of the periphery of the tensioned frame causes difficulties in attaching the reflector to a spacecraft.

The disadvantages of the deployable rim are as follows: - increase in perimeter of the rim which is related with the increase of the entire sizes of the reflector, i. e. with constructing of the large size deployable reflector significantly decreases the accuracy of geometrical shape of the rim in its deployed state which immediately effects on the accuracy of the reflector geometry. This is deemed to be an extremely big problem as the rim perimeter reaches tens of meters and with such sizes retaining the geometrical accuracy in millimeters or its tenth parts, especially after having been in deployed state, remains the biggest problem in machine building industry, particularly when hundreds of mechanical units and mechanisms are used.

- increase in diameter of the rim causes nonlinear decrease of the stability and increase of the weight of the deployable rim.

Common disadvantages of the rim system are that its outline in the plan does

not correspond to the oval shapes of offset shape reflectors. As a result, the design becomes complicated and, at the same time, optimization of the weight and dimensions is not reached.

The common disadvantages of the above-described analogs are crucial and they have impact on building conventional large size deployable reflector antennas including those with deployable rim systems.

It is known also a deployable reflector antenna with is described in patent US 5680145 (HOlQ 15/20,1997).

The reflector antenna comprises a deployable rim and a tensioned frame.

The deployable rim is constructed as outside rim structure surrounding the tensioned frame and being the support therefor. The tensioned frame is constructed in front net and back net made of flexible members and being tensioned by means of flexible ties, The tensioned frame is fastened to the deployable rim by means of its periphery.

To the tensioned frame, a reflector is fastened on the side of its internal net, the reflector being constructed, in this specific embodiment, in a thin net.

In this specific embodiment, the deployable rim is constructed in struts, rods, and diagonals hinged to one another. The deployable rim is provided with local deployment synchronization and fixation mechanisms.

The deployable rim is provided with a power-mechanical deployment system which is made, in this specific embodiment, of a load-bearing cable winding onto a drive means or a pneumatic system.

The known reflector antenna as a whole comprises a deployable rim, a tensioned frame fastened thereunto, whereto a reflector is attached, the deployable rim being provided with a local deployment synchronization mechanism, a local deployment fixation mechanism, and a power-mechanical deployment system.

The drawback of such a reflector antenna is the limitation in increasing the reflector sizes. This limitation is conditioned by the deformation of the

tensioned frame, low frequency of oscillation, big height between the ends of the peripheral portion, direct impact of the deviations from the designed geometry on the inaccuracy of the reflector shape when the deployable rim is in the deployed state. In addition, shape of a particular portion in plan does not correspond to that of a offset reflector antenna.

All of these factors condition decrease in accuracy and stiffness, increase in weight, complex nature of the construction, yet decrease in number of variants for the attachment of the reflector antenna to a spacecraft when the enlargement of the reflector takes place.

The technical result of the present invention is increase in stiffness and accuracy of the systems with a deployable rim, elimination of the impact of the deviations from the designed shape on the accuracy of the reflector shape in deployed state of the deployable rim, and, particularly, obtantion of new additional essential technical effect by synthesis of deployable rim systems and rib-umbrella shape dome frame systems, i. e. by synthesis of tensioned frame and rib-umbrella shape dome frame on the base of a deployable rim, which effect would allow the new deployable reflector antenna to have little weight, big accuracy, big stiffness, simplicity in its manufacturing technology and increased variety of attachment variants of attachment to a spacecraft in the event it is enlarged in size, while maintaining common deployment stability, synchronization, and orientation. Besides, the reflector antenna diagram will be in concordance with the requirements imposed for offset reflector antennas.

The deployable space reflector antenna"E. V. M." comprises a tensioned frame and a deployable dome frame attached to the tensioned frame by means of connection joints at the outside of its periphery. The tensioned frame and the deployable dome frame create approximated surface of the entire reflector of the reflector antenna, whereto the reflector is attached. The approximated surface forms symmetrical and dissymetrical structures of offset reflectors having circular, oval, or polygonal outlines in plan. The tensioned frame is

attached to the deployable rim by means of fastening joints and movable joint, or by movable joints solely. The deployable dome frame is connected to the deployable rim by means of fixed joints, movable joints, and/or the tensioned frame. In the process of being deployed, sizes of opposite contours of the deployable rim are equal or differ from one another by variable or constant value. The deployable rim is provided with a local deployment synchronization mechanism, local deployment fixation mechanism, and power-mechanical deployment system. In addition, the tensioned frame is provided with a common deployment stabilization system and common deployment orientation system.

The interconnected tensioned frame, deployable rim, and deployable dome frame are constructed in various design solutions and parts in the specific embodiment. Besides, The reflector antenna"E. V. M." represents a transportable package in its folded state which can be unfolded and fixed in its final form by deploying the deployable rim.

The reflector antenna is provided with a variety of design solutions for attaching to a spacecraft.

The deployable space reflector antenna"E. V. M." is illustrated by means of 100 figures, where: Fig 1 is principal view of the space reflector antenna"E. V. M." in its deployed state; Fig 2 is a flat rib with peripheral dividers arranged in parallel to one another; Fig 3 is a flat rib with its reflector fastening contour differing from that of the opposite contour; Fig 4 is a flat rib with peripheral dividers inclined relative to each other; and with reflector fastening contour length differing from that of the opposite contour; Fig 5 is a flat rib with reflector fastening contour and its opposite contour touching each other;

Fig 6 is a radial diagram of the reflector fastening contours with spatial arrangement of the tensioned frame flat ribs; Fig 7 is a radial-ring diagram of the reflector fastening contours with spatial arrangement of the tensioned frame flat ribs; Fig 8 is a parallel diagram of the reflector fastening contours with spatial arrangement of the tensioned frame flat ribs; Fig 9 is a triangle diagram of the reflector fastening contours with spatial arrangement of the tensioned frame flat ribs; Fig 10 is a quadrangle diagram of the reflector fastening contours with spatial arrangement of the tensioned frame flat ribs; Fig 11 is a hexagonal diagram of reflector fastening contours with spatial arrangement of the tensioned frame flat ribs; Fig 12 is a intermediate stiffness dividers fixed on the flat rib having peripheral dividers inclined relative to each other; Fig 13 is intermediate stiffness dividers fixed on the flat ribs having peripheral dividers parallel to each other; Fig 14 is intermediate stiffness dividers fixed on the intersecting line of the flat ribs; Fig 15 is gathering of the radially arranged flat rids into the central unit; Fig 16 is gathering of the radial-ring like arranged flat ribs into the central unit; Fig 17 is a rib having peripheral dividers inclined relative to each other, the rib provided with cuts; Fig 18 is a rib having peripheral dividers parallel to each other, the rib provided with cuts; Fig 19 is a perforated flat rib; Fig 20 is a perforated flat rib with its reflector contour and opposite contour touching each other; Fig 21 is a complete system of synchronized deployment and a complete system of deployment stabilization;

Fig 22 is a tensioned frame composed of a reflector frame, support frame, and rod connections; Fig 23 is a reflector frame, support frame, and rod connections with peripheral dividers inclined relative to each other; Fig 24 is rod connections constructed in struts; Fig 25 is rod connections constructed in braces; Fig 26 is a radial diagram of the reflector frame, support frame and connections in plan; Fig 27 is a radial-ring like diagram of the reflector frame, support frame and connections in a plan; Fig 28 is a radial-ring like diagram of the reflector frame, support frame and connections in a plan, in combination with the reflector frame; Fig 29 is a radial-net like diagram of the reflector frame, support frame and connections in a plan; Fig 30 is a radial-net like diagram of the reflector frame, support frame, and connections in a plan, in combination with the reflector frame; Fig 31 is a parallel arrangement of the reflector frame, support frame, and connections in a plan; Fig 32 is a diagram of tetragons created by the reflector frame, support frame, and connections in a plan, in combination with the reflector frame; Fig 33 is a diagram of tetragons created by the reflector frame, support frame, and connections in a plan ; Fig 34 is a diagram of triangles created by the reflector frame, support frame, and connections in a plan ; Fig 35 is a diagram of hexagons created by the reflector frame, support frame, and connections in a plan ; Fig 36 is a combined diagram of triangles and hexagons created by the reflector frame, support frame, and connections in a plan; Fig 37 is a reflector frame and support frame made of sheets and stiff struts;

Fig 38 is a reflector frame and support frame made of membranes and stiff struts; Fig 39 is a reflector frame, support frame, and braces made of flexible rods; Fig 40 is a reflector frame made of flexible rods, quadrangle shape support frame made of sheets, and struts made of stiff rods; Fig 41 is a reflector frame made of flexible rods, support frame made of curved sheets, and struts made of stiff rods; Fig 42 is a reflector frame made of sheets, support frame made of flexible rods, and struts made of stiff rods; Fig 43 is struts made of membranes; Fig 44 is a reflector frame and support frame made of stiff rods and equipped with intermediate"breakage"units; Fig 45 is a tensioned frame with an inclined peripheral divider and a central unifying unit; Fig 46 is a tensioned frame with an parallel peripheral divider and a central unifying unit; Fig 47 is the central unifying unit of the reflector frame and support frame made of sheets; Fig 48 is the central unifying unit of the reflector frame made of flexible rods and of the support frame made of sheets; Fig 49 is the central unifying unit of the reflector frame made of sheets and of the support frame made of flexible rods; Fig 50 is an additional frame mounted in the tensioned frame; Fig 51 is a radial-ring arrangement diagram of the additional frame; Fig 52 is a radial-net arrangement diagram of the additional frame; Fig 53 is a diagram of the additional frame arranged in off-center fashion relative to the tensioned frame; Fig 54 is an additional frame made of flexible rods, stiff rods, membranes and a combination thereof;

Fig 55 is a damper of temperature deformations for the tensioned frame and additional frame; Fig 56 is an arrangement of the deployable rim design on the planes of a regular prism lateral faces; Fig 57 is an arrangement of the deployable rim design on the planes of a regular pyramid frustum lateral faces; Fig 58 is cylindrical units for connecting the ends of the deployable rim rods; Fig 59 is a cardan unit composed of cylindrical units; Fig 60 is a cardan unit with a flexible-cylindrical unit; Fig 61 is a diagram consisted of double"scissors"of the deployable rim along with parallel peripheral dividers; Fig 62 is a diagram consisted of double"scissors"of the deployable rim along with inclined peripheral dividers; Fig 63 is a diagram consisted of unitary"scissors"of the deployable rim and additional rods along with parallel peripheral dividers; Fig 64 is a diagram consisted of unitary"scissors"of the deployable rim and additional rods along with inclined peripheral dividers ; Fig 65 is fixing rods for restricting the reverse motion of the deployable rim in the process of being deployed; Fig 66 is reverse motion restricting fixing rods on a telescopic rod; Fig 67 is damper of the displacement of the attachment of the deployable rim moving units to the peripheral divider; Fig 68 is a power-mechanical system of the deployable rim which is constructed in a load-bearing rope; Fig 69 is a geometrical relationship of the"scissors"which are the components of the design of the deployable rim, placed on the plane of the regular prism lateral faces; Fig 70 is a geometrical relationship of the"scissors"which are the components of the design of the deployable rim, placed on the plane of the pyramid

frustum lateral faces; Fig 71 is stiff fastening of the deployable dome cantilever, along with the linkage unit, to the peripheral divider of the tensioned frame; Fig 72 is a windable cantilever made of flexible material; Fig 73 is a cantilever made of flexible material, with the capability of bending in the linkage unit with respect to the peripheral divider; Fig 74 is a cantilever made of flexible material with the capability of bending its end; Fig 75 is a cantilever along with linkage unit, hinged to the peripheral divider turning around which is performed by means of a hinged-rod system; Fig 76 is a diagram of the stowed package where the cantilever along with the linkage unit is hinged to the peripheral divider; Fig 77 is a fixing of the tensioning and the form of the flexible member which forms the approximated contour of the dome frame reflector shape by means of a stiff deployer and hinged-rod system; Fig 78 is a diagram of the construction in a stowed state when a stiff deployer of the dome frame is used; Fig 79 is cantilevers of the dome frame with flexible stability ties arranged as triangles; Fig 80 is a tensioning and shaping of the flexible member forming the approximated contour of the dome frame reflector shape by means of a flexible rod; Fig 81 is a diagram of the stiff member forming the approximated contour of the dome frame reflector shape with an additional locking hinge; Fig 82 is a diagram of the construction in the stowed state with the use of a stiff member having an additional locking hinge; Fig 83 is a top view of the deployable dome frame, tensioned frame, deployable rim, and a united deployment orientation system assembled in the central unit;

Fig 84 is a sectional view, on the long axis, of the deployable dome frame, tensioned frame, deployable rim, and a united deployment orientation system assembled in the central unit; Fig 85 is a sectional view, on the short axis, of the deployable dome frame, tensioned frame, deployable rim, and a united deployment orientation system assembled in the central unit; Fig 86 is an arrangement of structural additions in cylindrical units at the ends of the deployable rim axis; Fig 87 is opening stages of the stiff guides in the united deployment orientation system with deployment capability of the deployable rim; Fig 88 is a diagram of the reflector stowed according to section on the long axis of the design of the deployable dome frame, tensioned frame, deployable rim, and the united deployment orientation system assembled in the central unit; Fig 89 is a diagram of the reflector stowed according to the section on the short axis of the design of the deployable dome frame, tensioned frame, deployable rim, and the united deployment orientation system assembled in the central unit; Fig 90 is a connection of the deployable space reflector structure to a spacecraft by means of a base unit; Fig 91 is a connection of the deployable space reflector structure to a spacecraft by means of the frame of the deployable dome; Fig 92 is a stiffened sheet member for mounting the reflector on the cantilever of the deployable dome made in the form of a rod-girder spatial structure; Fig 93 is a testing attachment of the standard template of the contour of the reflector which is to be cut at the project outline of the stiffened sheet member and flat rib or stock of the reflector frame; Fig 94 is a removal of the project outline of the stiffened sheet member and flat

rib or reflector frame stock by means of the reflector contour standard template; Fig 95 is a simulation of the stress-deployed state of the reflector structure in operation; Fig 96 is a technological diagram for determining the forces transferred from the reflector to the reflector structure and the direction thereof with the possibility of the reflector contour to be controled by means of the standard template; Fig 97 is diagrams of fastening of the reflector in tensioned state along the contours of the surfaces approximated by the deployable dome. frame and tensioned frame; Fig 98 is a diagram illustrating the ends having oval contours inside and outside the rim disposed in plane of the pyramid frustum lateral faces; Fig 99 is ovals resting by means of their edges against each other inside the rim, and the temperature deformation dampers arranged on the rods; Fig 100 is ovals arranged outside the rim, which are resting against each other by means of teeth arranged at their edges, and the temperature deformation dampers arranged on the rods.

The deployable space reflector antenna"E. V. M." 1 comprises a reflector 2 mounted on a tensioned frame 3 forming the approximated surface of the reflector shape. The tensioned frame is attached to the deployable rim 5 by the peripheral attaching means 4.

The deployable rim is provided with local deployment synchronization mechanism 6, local deployment fixing mechanism 7, and power-mechanical deployment system 8. The tensioned frame has connection to a deployable dome frame 10 by means of connecting joints 9 located outside its periphery.

The dome frame, together with the tensioned frame, forms a common approximated surface for fixing the reflector that is applicable in both

symmetrical and dissymmetrical offset reflectors having circular, oval and/or polygonal outlines in the plan. The deployable dome frame is connected to the deployable rim by means of fixed joints 11, movable joints 12, and/or the tensioned frame. The sizes of the opposite edge contours of the deployable rim are equal or they may be differed from one another by a constant value or variable in the process of being deployed. Along with the fixing points, the tensioned frame is fixed to the deployable rim by means of movable units 13 or it is fixed by the movable units only. The tensioned frame is equipped with a common deployment synchronization system 14 and common deployment stabilization system or common deployment orientation system (Fig 1).

The deployable space reflector antenna"E. V. M." comprises an extensible or flexible net or membrane constructed as a whole structure or in parts of individual shapes.

The tensioned frame is composed of flat ribs 17 (Fig. 2) made of windable and/or foldable sheets or membranes. At the peripheral edges of the ribs, peripheral dividers 18 are mounted. The peripheral dividers are made of stiff rods having equal and/or different lengths. They are arranged in parallel or inclined relative to each other in the tensioned frame (Fig 3,4).

The flat ribs, as components of the tensioned frame, individually form the reflector fixing contour 19 and the opposite contour 20. The reflector fixing contour and the opposite contour have similar or different outlines in each flat rib with equal or different lengths. These contours touch (Fig 5) or do not touch each other.

The flat ribs of the tensioned frame with their spatial relation form radial (Fig 6), radial-ring (Fig 7), parallel (Fig 8), triangle (Fig 9), quadrangle (Fig 10) and/or hexagonal (Fig 11) shapes of the reflector fixing contours.

On the flat ribs (Fig 11 and 12) or the intersection line thereof (Fig 14), intermediate stiffness dividers 21 are mounted.

While being in radial (Fig 15) or radial-ring (fig 16) space relationship

the flat ribs are united in the central unit 22.

The ribs, made of sheets or membranes, are provided with cut-outs 23 (Fig 17,18) and perforations 24 (Fig 19,20).

The common deployment synchronization system of the tensioned frame composed of flat ribs radially arranged in space is constructed by fixing long shafts 25 rotatable around the axes opposite the reflector contour on the central unit, the shafts being arranged perpendicular to the direction of winding of the flat ribs onto the central unit (Fig 21).

The common deployment stabilization system is constructed in sprockets 26 and drums 27 having cells with recesses. Both the sprockets and the drums are fixed on the rotatable shafts by turns. Between the sprockets and drums, perforated cells 28 applied on the ribs are passing in order during the passage of the flat ribs twisted around the central points.

Apart from the flat ribs, the tensioned frame may be constructed in other structures. In this case, the tensioned frame is consisted of a reflector frame 29 forming the reflector shape approximated surface and a support frame 30, the reflector frame and the support frame being connected to one another by means of rod connections 31. At the ends of the reflector frame and support frame, peripheral dividers 18 made of stiff rods having equal or different lengths are mounted, the dividers being arranged in parallel or inclined relative each other in the tensioned frame (Fig 22 and 23).

The reflector frame and support frame directly touching (Fig 25) or not touching (Fig 24) each other have either similar or different shapes and equal or different sizes in the plan.

The rod connections are comprised of struts 32 and/or braces 33 in such a manner that the ends of the braces are connected to the ends of the struts and/or braces, and the edge strut and/or edge brace is connected to the peripheral divider with its one end.

The reflector frame and the support frame connected to it by rod

connections are arranged, along with the rod connections, in the plane and/or space and form radial (Fig 26), radial-ring (Fig 27,28), radial-net (Fig 29,30), parallel (Fig 31), quadrangle (Fig 32,33), triangle (Fig 34), or hexagonal (fig 35) diagrams and/or combined diagrams thereof in plan (Fig 36).

The reflector frame and support frame are made of sheets, membranes, flexible rods and/or stiff rods, and the rod connections are made of flexible and/or stiff rods and/or sheets and/or membranes (Figures 37-44).

The stiff rods of the reflector frame and support frame are attached to the ends of the struts, braces and/or peripheral divider by means of hinge joints 34 and, in addition, they are provided with intermediate"breakage'hinges 35 between the hinge joints.

When the reflector frame and support frame and rod connections thereof are arranged in radial, radial-ring, radial-net, and combined fashion both frames are coming together into the central unit 36 (Figures 45-49).

Between the flat ribs, or between the reflector frame, support frame and/or rod connections thereof an additional frame 37 is provided in the tensioned frame (Fig 50).

The additional frame is comprised of an additional reflector frame 38 and/or additional stiffening frame 39.

The additional frame is arranged in the tensioned frame in such a manner that it forms ring, radial, radial-ring, radial-net and/or ring-net diagrams (Fig 51,52).

The members of the radially arranged flat ribs in the tensioned frame, or of the additional frame connecting the reflector frame are arranged as concentric circles or as a polygon outlined by ovals, or as eccentrically arranged circles, or as polygons outlined by ovals in plan (Fig 53), while the vertexes of each eccentrically arranged polygon are spaced apart at equal distances from the plane passing through the edge contour of the reflector.

The additional frame is constructed in flexible rods, stiff rods, sheets

and/or membranes and/or combinations thereof (Fig 54).

The reflector frame, support frame, additional frame, and the flat ribs of the tensioned frame are provided with dampers 40 of temperature deformation (Fig 55).

The deployable rim is composed of stiff rods 43 arranged on the plane 41 of the lateral edges of regular prisms or pyramid frustums. The rods are connected to one another by means of cylindrical units 42 and they are arranged in the form of"scissors"system.

The ends of the robs 43 are a attached to the edge rod dividers of the tensioned frame by means of fixing units 44 and/or movable units 45, the rod dividers being arranged on the lateral faces of the above-mentioned prisms or pyramid frustums (Fig 56,57).

The ends of the deployable rim rods arranged on the planes of the lateral faces of the regular prisms or pyramid frustums are connected to the ends of deployable rim rods arranged on the planes of the lateral ribs by means of cylindrical units 46 (Fig 58) or cardan units comprised of the cylindrical units (Fig 59).

The cardan units are constructed in three cylindrical units, two of which are the sliding cylindrical edge hinges, and the third one is an intermediate flexible-cylindrical hinge 47 (fig 60).

The rods connected with one another by means of cylindrical units and arranged on the plane of an individual face form a single"scissors" arrangement (Fig 56,57) or double"scissors"arrangement (Fig 61,62).

Apart from the above-described arrangements, to each rod, which is the component of single"scissors"arrangement, additional rods 49 arranged in the planes of lateral faces are attached by means of cylindrical units 48. The additional rods are connected to one another with their ends by means of cylindrical hinges 50 and are forming quadrangle arrangements in such a manner that two vertexes of the quadrangles are individually connected to the

vertexes of the quadrangles arranged on the adjacent ribs by means of cylindrical or cardan units (fig 63,64), and the remaining two vertexes are connected to the cylindrical unit of the"scissors"by a common rod 51 on which locator members 52 for restricting the reverse motion of the vertexes with respect to the cylindrical unit, are disposed, and, at the same time, the rod is made as a whole member or as a telescopic member 53 (Fig 65,66).

The stiff rods arranged as"scissors"and the additional rods arranged as quadrangles are connected with their ends to the peripheral divider by means of fixing units and/or they are attached by means of movable units in such a fashion that peripheral dividers contain dampers 54 and retaining members 55 for restricting the motion thereof after having performed certain displacement (Fig 67).

The power-mechanical system of the deployable rim is constructed in a load-bearing cable 56 which is fixed at the end of a rod contained in"scissors" by means of a compensator 57. The load-bearing cable extends along the longitudinal direction of one of the rods which is the component of"scissors" disposed on each rib, and passing over bearings 58 disposed at the ends of the rod it tensions and approaches the end of the rod to the opposite end of the rod on the adjacent rib. Afterward, the operation continues in a similar manner on a rib and, finally, it winds by means of an electric drive means 59 which in turn adjusts winding of the load-bearing cable and fixes it with geometrical parameters of the rim deployment and with tension force of the load-bearing cable (Fig 68). In the deployable rim, distances between the ends of the rods interconnected as a set of"scissors"arranged on the planes of the regular prism lateral faces and the cylindrical units of the"scissors"are equal (Fig 69) or distances between the ends of the rods interconnected as a set of"scissors" arranged on the planes of the pyramid frustum lateral faces and cylindrical units of the"scissors"are different (Fig 70).

The deployable dome frame is constructed in various ways.

At the end of the peripheral divider of the tensioned frame, on the reflector side, an arm 60 of the deployable dome frame is attached rigidly by means of connection units. The arm has the contour of the approximated surface of the reflector shape for attaching the reflector thereto (Fig 71).

If necessary, the arm is made of flexible material allowing to wind (Fig 72), to bend in the connection unit with respect to the divider (Fig 73) and/or to bend the arm at its end (Fig 74).

In other cases, the arm is hinged to the peripheral dividers of the tensioned frame by connection units, and its rotation is performed by means of the fixed and/or movable connections arranged at the deployable rim. The fixed and movable connections are constructed in hinge-lever rod system 61 which is also connected to the peripheral divider (Fig 75).

The stowed package of the reflector structure constructed in such a manner is illustrated on the Fig 76.

The members which form the approximated contour of the dome frame reflector are the flexible members having due profile, whose tensioning form creation and form fixing is performed by means of a stiff deployed member 63 hinged 62 to the end of the peripheral divider opposite to the reflector side.

Deployment of the stiff deployed member is performed by means of the deployable rim along with fixed and/or movable connections connected thereto and forming hinge-lever system (Fig 77). The stowed package of such a stricture is illustrated on Fig 78.

If required, the arms of the radially arranged dome frame are provided with flexible ties 64 arranged as triangles in plan (Fig 79).

Tensioning of the flexible member which forms the approximated contour of the dome frame reflector shape and its form creation is defined by a flexible rod 65 hinged to the end of the peripheral divider opposite to the reflector side, whose unfolding from its stowed condition is performed by means of the deployable rim along with the hinge-lever system of fixed or

movable connections connected thereto. In addition, the flexible rod which is fastened at the peripheral end of a girder forms combined pretension cantilever girder 67 along with flexible diagonals 66 of the dome frame due to the existing elastic force (Fig 80).

In other cases, the stiff member which forms the approximated contour of the dome frame reflector is hinged to the end of the peripheral divider by means of the connection unit and its orientation is fixed by means of the stiff rod 68 hinged thereto and, also, to the another end of the peripheral divider.

The stiff rod ensures also that the stiff member is unfolded and the projection form is fixed due to the hinge-lever system connected to the deployable rim and an additional hinge 69 having a lock (Fig 81). The stowed package of the described construction is shown on the Fig 82.

The peripheral divider of the tensioned frame, together with the cantilever member of the deployable dome frame (Fig 83), which is rigidly connected to the end of the peripheral divider by means of a connection unit on the reflector side are built in combination as a rod-girder spatial structure 70, whose chords 71, struts 72 and diagonals 73 are made of stiff rods and flexible tensioned rods (Fig 84,85).

The peripheral dividers of the tensioned frame with its fixed units and movable units and/or movable units are fixed in and/or fastened to the deployable rim by means of the chords having rod-girder spatial structure.

In a specific case, to obtain the desirable form of the stowed package of the deployable rim, the ends of the deployable rim rods arranged on the plane of the prism or pyramid frustum lateral faces are connected to the deployable rim rods arranged on the plane of the adjacent lateral edges by means of the added members 74 existing on the cylindrical hinges (Fig 86).

The ribs of the tensioned frame are united in the central unit fixed in the base unit 75 or fastened by means of a rotatable mechanism 76 provided with locators 77 for restricting the rotation (Fig 84, 85).

In the base unit, a joint deployment orientation system 16 in the form of an unfoldable stiff guide is hinged by means of a hinge 78.

The joint deployment orientation system is connected to the ends of the peripheral dividers and/or stiffness dividers and/or struts, at the opposite side to the reflector, by means of sliding units 80 (fig 87). The given solution ensures that the stiff guide of the joint deployment orientation system is unfolded by means of the deployable rim in the process of being deployed.

The stiff guide is strengthened by means of the reinforcing rods 80 connected thereto and fixed in the base unit (Fig 83).

While retaining the design simplicity of the reflector structure, the deployable rim has the form of the pyramid frustum lateral faces in the stowed state so as to fall within the sizes of the stowed package, and the vertex of the pyramid constructed thereby is located on the reflector side (Fig 88, 89).

In this specific embodiment, the additional frame is disposed also between the frame of the deployable dome frame (Fig 83).

Connection of the deployable space reflector antenna"E. V. M." to the spacecraft is performed by means of the basic unit (Fig 90) or deployable dome frame (Fig 91) through the connection structure 81.

The cantilever member of the deployable dome, which is made as a rod- girder structure, has a stiffened sheet contour 83 (Fig 92) for forming the reflector contour by an edge.

The stiffened sheet contour, i. e. reflector frame made of flat ribs or sheets, is made with an appendage on the reflector fastening side, as differed from its project outline 84, which is cut by means of controlling fastening of reflector contour standard templates 85 (Fig 93) prior to fastening the reflector thereon in such a condition when the reflector structure is in operation stress- deformed state (Fig 95).

On ground conditions, the operation stress-deformed state of the reflector antenna as achieved by simulation of weightless state 86 and by deploying the

deployable rim in a special meteorological environment, where the reflector antenna is subject to application of forces 87 with values and directions simulating the forces and directions of these forces transmitted after it has been fastened on the approximated surface contours of the reflector (Fig 95).

Determination of value and direction of power factors simulation forces transmitted by the tensioned reflector to the reflector antenna is achieved by applying the forces of such values and directions at the fastening points of the reflector to the reflector antenna which provide the project outline of the reflector in tensioned state and which is checked by the standard templates of the reflector contour.

The reflector being in tensioned state is bond on 88, sewed on 89, and/or keyed 90 at separate points to the contours of approximated surface having the form of the reflector, which is given by the deployable dome frame and tensioned frame (Fig 97).

At the ends of the double or single rods of the deployable rim, which are arranged in the plane of the pyramid frustum lateral faces, ends 91 (Fig 98) having oval outline are attached from the both sides of the plane. in parallel planes, the ends being rested, by the edge against the edge of analogous ovals made at the analogous ends of the deployable rim rods arranged on the adjacent face, in such a manner that permanent contact between them is maintained during the whole process of deployment of the rim.

The ends ovals which are arranged inside the lateral faces of the pyramid frustum (Fig 99) are elongated by means of longitudinal guides of the deployable rim rods, and the contours of ovals arranged on the opposite plane are elongated by the transverse guides of the deployable rim rods (Fig 100). In addition, the ovals edges have smooth surfaces 92 or teeth 93 thereby creating the local synchronization system of the rim deployment.

The deployable rim rods and the additional rods are provided with temperature deformation dampers 94 (Fig 99,100).

The deployable space reflector antenna"E. V. M." has the form of prism or pyramid frustum in its folded state which, in itself, represents a transportation package. The small base of the truncated pyramid may be located both on the reflector side and its opposite side.

In the folded state, the deployable space reflector antenna"E. V. M." is connected to the spacecraft by means of a connection structure attached to the central unit or deployable dome frame. The above-mentioned two embodiments of connection of the reflector antenna to the spacecraft make no difficulties in terms of power and stiffening factors due to the predictability, mechanism, and control of the deployment process, as well as big stiffness in deployed state and structural peculiarities, which will be expressed in the description of the construction, followed herein after.

Deployment of the space reflector antenna"E. V. M" from its folded state, tensioning of the tensioned frame, deployment of the dome frame and final maintenance of the form are effected by deployment of the deployable rim, and by achieving and maintaining the designed state.

Despite the geometrical shapes of the transportation package of the reflector antenna in its folded state and particularly, of the deployable rim in the folded state, its design always allows to obtain desirable geometry of the deployable rim in its final designed state.

The description of the deployable rim design confirms the fact that its design may be arranged, in any particular case, on the lateral faces surfaces of the regular prism or pyramid frustum.

The presented material describes, by the appended claims, the particular embodiments of the deployable rim with the use of"scissors"like designs.

Following the basic principles of the deployable space reflector antenna "E. V. M" design and the above-described particular embodiments thereof the following can be ensured: - deployment reliability and simplicity ;

- big rigidity; - light weight; - optimal shape and stiffness of the transportation package; - simplification of manufacture technology; and what is the most important, - big accuracy of the antenna reflector geometry; - maintaining the surface shape upon repeatedly deployment of the structure; and additionally, - big sizes of the reflector; - concordance of the design to the offset shape of the reflector; - variety of attachment versions to the spacecraft.

The above-described advantages are effected due to both the common principal design of the reflector antenna and the particular embodiments given in the description. Still, additional explanations should be provided, due to its important character, in terms of the provision of the reflector accuracy by the presented reflector antenna.

As shown in the description, the tensioned frame of the reflector antenna can be made, in particular case, not only with sheets or membranes, but with flexible rods as well. It should be noted herein also that in case the flexible rods are utilized the stiffness of the design in the tensioned frame and deployable dome frame is significantly little, the manufacturing technology is relatively intricate, and both whole and local accuracies of the approximated contours created for attachment of the reflector are reduced. Deterioration of the local accuracy is caused by local convexity of the flexible rods which, in turn, is caused by the forces transferred to them from the tensioned frame. These are added by the difficulties in attachment of the reflector to the flexible rods. The flexible rods made as wires, threads, ropes or ribbons, have the property of "catching"which is very dangerous in a deployable structure, particularly in

case where connections between the frames are made by stiff rods.

Thus it should be mentioned that the advantages of the deployable space reflector antenna"E. V. M." are wholly expressed in case where the tensioned frame is made of flat ribs or such a reflector frame and support frame are made of sheets or membranes.

The flat ribs, reflector frame, and support frame have very big stiffness in the tensioned state in their plane of arrangement. This conditions the technology for obtaining the high accuracy for the approximated surface, manufacturing simplicity and, particularly, big accuracy of contours created for attaching the reflector by tensioned frame, the repeatness of the accuracy upon multiple deployments and tensioning.

Moreover, the ribs of the tensioned frame or the frame created by it have such stiffness in its own plane that they"force"the deployable rim to take the designed position by forcible deformation thereof notwithstanding any inaccuracies of the geometry of the deployable rim taking place in its manufacturing process.

Prevention of the influence of the deployable rim geometry inaccuracies on the accuracy of the reflector can have great result. It will allow to avoid all main disadvantages of the circular deployable reflectors. This advantage is reinforced by that the connection of the tensioned flame peripheral divider to the rim can be effected solely by movable units which will allow the inaccurately made deployable rim to take its natural position without overtensioning and deforming the tensioned frame, and to ensure that only single condition for the tensioned frame accuracy is met-its tensioning.

The deployable rim in the deployable space reflector antenna"E. V. M." has double function. Its additional function is to deploy not only the tensioned frame, but also the deployable dome frame, and to maintain its shape without the need in any additional structural parts and complexity.

Precision of the deployable dome's location in the event of the above

described design solutions depends on the accuracy of the tensioned frame and does not depend on the precision of the deployable rim geometrical parameters.

The above described factors allow to obtain and maintain high accuracy and stiffness from the basic unit up to any points of the reflector shape approximated contour, because the accuracy of any point of the approximated contour is in relation to one another under the geometrically constant design and is controlled from the basic unit connected to the spacecraft by means of the connecting design means.

High accuracy of the reflector attachment contours is conditioned not only by the due picture illustrating the tensioned-deformed state, which is obtained with the design solution, but the technological aspects of the design solution, and consequently, by capabilities of rectifying any geometrical inaccuracies created at the final stage of the design manufacturing.

This is enabled by the design of the reflector being in tensioned- deformed state, where the a attaching means of the reflector contour, which is made of sheets or membranes, can be cut from the preliminarily remained appendage so as to obtain the contours having designed outline.

If it is taken into account the fact that the tensioned frame is provided with an additional frame for increasing accuracy and stiffens, which have high degree of local stiffness in the tensioned state, it will be understood the favorable condition which is created for attaching the reflector and obtaining its precise shape.

It is important also that in several embodiments of the deployable space reflector antenna"E. V. M." provides for adhesion of the reflector to the approximated contour which simplifies the technology and increases local accuracy of the reflector attachment.