Abstract:
The invention relates to space engineering, and can be used for space radio, television and telephone communications, as well as illuminating ground objects at night from space. The inventive unfolding film-type radiation reflector comprises a framework consisting of pneumatic tubes and cells, a film reflecting surface connected to the framework along the perimeter thereof and a gimbal assembly mountable on a space vehicle. The internal and external frames of the gimbal assembly are made from internal and external wheel-shaped pneumatic tubes. The internal wheel-shaped pneumatic tube is embodied in such a way that it is mountable on the space vehicle, while the external wheel-shaped pneumatic tube is embodied in the form of a framework element and is connected to the film reflecting surface. Said invention makes it possible to reduce the mass and overall dimensions of mechanisms for packing and unfolding the film-type radiation reflector.

Description:
CROSS-REFERENCE TO RELATED APPLICATION 
       [0001]    This application claims the benefit of the priority filing date in PCT/RU2007/000080 referenced in WIPO Publication WO/2007/139434. The earliest priority date claimed is May 2, 2006. 
     
    
     FEDERALLY SPONSORED RESEARCH 
       [0002]    Not Applicable 
       SEQUENCE LISTING OR PROGRAM 
       [0003]    Not Applicable 
       STATEMENT REGARDING COPYRIGHTED MATERIAL 
       [0004]    Portions of the disclosure of this patent document contain material that is subject to copyright protection. The copyright owner has no objection to the facsimile reproduction by anyone of the patent document or the patent disclosure as it appears in the Patent and Trademark Office file or records, but otherwise reserves all copyright rights whatsoever. 
       BACKGROUND 
       [0005]    The invention relates to space engineering, more specifically, to space communication engineering. The technical result achieved by realization of the invention lies in the reduction of weight and dimensions of devices for folding and opening the film radiation reflector. 
         [0006]    The main point of the invention is the developed construction which permits a large-size mirror sheet to be packed, transported, and unfolded, and its orientation better controlled in space in accordance with a preset program. 
         [0007]    There is a known radiation reflector that consists of an external pneumatic chamber and radial supports in the form of perforated flexible tubes supplied with pneumatic cells. These pneumatic cells interact between themselves and with the mirror sheet, which in turn is connected to the internal pneumatic chamber and the filler (source of gas). 
         [0008]    However, the known radiation reflector does not possess constructional details that allow packing and spreading out from the folded position. This defect makes it difficult to transport the reflector, unfold it in space, and control its orientation. 
         [0009]    Also known in the art is a “Solar sailing vessel” (SSV) with a film radiation reflector which, by its constructional features, may be specified as the prototype for the present invention. 
         [0010]    The prototype has a case, main and additional flexible tubes, and devices to control the orientation of the main and additional flexible tubes. Means of surface formation are realized as pneumatic systems. 
         [0011]    Control means for flexible reflecting surfaces are made in the form of gimbal suspensions with electric drives placed outside the SSV. External frames of the gimbal suspensions have corresponding means for forming flat reflecting surfaces and devices for their unfolding. 
         [0012]    However, placement of electric drives for orientation and rolling up the reflecting surfaces on the gimbal suspensions outside the spacecraft (SC) increases their weight and dimensions and makes folding and transporting the reflector more difficult. The prototype does not provide for the folding of the flexible surface (reflecting sheet) for transportation and the constructional details used for its spreading out from the folded position. 
         [0013]    The technical task consists of working out such construction of the radiation reflector that can ensure the folding, transportation and spreading out of the reflecting sheet, as well as reducing the weight and dimensions of the devices for unfolding and controlling the orientation of the radiation reflector. 
       SUMMARY 
       [0014]    The technical task of working out a construction of the radiation reflector that can ensure the folding, transportation and spreading out of the reflecting sheet, as well as reducing the weight and dimensions of the devices for unfolding and controlling the orientation of the radiation reflector, is solved by introducing into the case of the radiation reflector the following kinematically connected devices: the flexible reflecting mirror and the means for formation, in the form of pneumatic systems, and the control means for the orientation of the flexible reflecting surface, mounted on the gimbal suspensions. 
         [0015]    In this case, gimbal suspensions are made in the form of first and second concentric pneumatic chambers interacting with each other and kinematically connected by axes and shafts with the corresponding electric drivers for orientation fixed on the case of the SC. The concentric pneumatic chambers and the pneumatic system for surface formation are pneumatically connected with the source of filling (e.g. gas). 
         [0016]    The second variant of the radiation reflector additionally includes the first spinup electric motor, and kinematically connected to it, the first freely rotating drum installed on the case. The drum has the second and third electric motors for orientation and filler sources (gas) rigidly affixed to it. 
         [0017]    In the third variant of the unfolding film radiation reflector, the second and third electric motors for orientation are installed in such a way that the orientation directions of their shafts coincide with the orientation direction of their radial pneumatic supports. Here, the second electric motor is installed on the SC case rigidly, while the third one is installed by hinges, freely revolving around the rod and oriented along the shaft of the second motor and interacting with the shaft. 
         [0018]    In the forth variant of the unfolding film radiation reflector, the second and third electric motors for orientation and the first and second gas fillers are installed in symmetrical pairs along the long axis of the SC case at its bow (or stern). The case of the second electric motor is rigidly connected to the bar with the second gas filler, while the case of the third electric motor (along with the rigidly connected first gas filler) is fastened by hinges, with the help of brackets, to the bar that is installed on the shaft of the unrolling motor affixed to the SC case. 
         [0019]    In this variant, the flexible reflecting surface has the form of a circle and is packed by being rolled up from four sides in two perpendicular directions coinciding with the direction of the radial pneumatic supports. 
         [0020]    In the second variant, the flexible reflecting surface in the form of a circle is folded sector by sector like accordion bellows in such a way that the filling of the pneumatic cells on the radial supports is realized from the center to the periphery, whereupon the pneumatic cells of the external pneumatic chamber are filled. 
         [0021]    In both variants of the radiation reflector, radial pneumatic supports and the external pneumatic chamber have pneumatic valves installed in a certain manner. 
         [0022]    In this situation, the pneumatic valve has a tube with two radial and two longitudinal apertures. In the tube, there is a spring-loaded small ball that interacts with the compressed gas inside the flexible tube and the “tongs-like” ends of the two second springs installed at both diametrically opposite ends. 
     
    
     
       FIGURES 
         [0023]      FIG. 1  is the construction of the present invention: 
           [0024]    ( 1 ) case of the spacecraft (SC), 
           [0025]    ( 2 ) drum, 
           [0026]    ( 3 ) the first motor of unrolling, 
           [0027]    ( 4 , 5 ) the second and the third electric motors for orientation, 
           [0028]    ( 6 , 7 ) the first and second culring shafts, 
           [0029]    ( 8 ) filler source, 
           [0030]    ( 9 ) hose, 
           [0031]    ( 10 , 11 ) the first and second concentric pneumatic chambers, 
           [0032]    ( 12 , 13 ) the first and second hinge joints, 
           [0033]    ( 14 ) external (the third) pneumatic chamber, 
           [0034]    ( 15 ) radial pneumatic supports 
           [0035]    ( 16 ) mirror sheet, 
           [0036]    ( 17 ) taut bands, 
           [0037]    ( 18 , 19 ) the first and second curling axes, 
           [0038]    ( 20 ) pneumatic valve, 
           [0039]      FIG. 2  shoes the hinge joint  13  of the curling axis  6  with the first pneumatic chamber wherein: 
           [0040]    ( 21 ) is the tubular tip, 
           [0041]    ( 22 ) is the sleeve, 
           [0042]    ( 23 ) is the ring, 
           [0043]    ( 24 ) is the connecting pipe 
           [0044]      FIG. 3  shows the joint of the drum spinup, where positions  1 - 9  repeat the positions of  FIG. 1 : 
           [0045]    ( 25 ) wheel. 
           [0046]      FIG. 4  shows the design of the second curling shaft  7 , wherein: 
           [0047]    ( 26 , 27 ) are the first and second gimbal suspensions, 
           [0048]    ( 28 ) is the spider, 
           [0049]    ( 29 ) is the guide, 
           [0050]    ( 30 ) is the slide-block, 
           [0051]    ( 31 ) are the guiding tabs (wires), 
           [0052]    ( 32 ) are the slots, 
           [0053]    ( 33 ) is the spring, 
           [0054]    ( 34 ) are the links of the curling shaft, 
           [0055]    ( 35 ) are the hinge joints, 
           [0056]    ( 36 ) is the cylindrical tip of the shaft  7 . 
           [0057]      FIG. 5  shows the A-A sectional view of the curling shaft  7  as in  FIG. 4 , where positions  26 - 36  repeat the positions of  FIG. 4 . 
           [0058]      FIG. 6  shows the film reflector  16  as in  FIG. 1  rolled up from two sides along the OX axis as viewed from the SC end. 
           [0059]      FIG. 7  shows the B view as in  FIG. 6 , where the mirror sheet  16  of the reflector is rolled up from two sides. 
           [0060]      FIG. 8  shows the C view of the reflecting film as in  FIG. 7 , rolled up from four sides. 
           [0061]      FIG. 9  shows the K view as in  FIG. 8 , where the reflecting film is rolled up from four sides and covered with the casing  37 . 
           [0062]      FIG. 10  shows the second variant of packing the reflecting film for transportation, where positions  1 - 21  repeat the positions of  FIG. 1 : 
           [0063]    ( 38 ) lines of the reflector deflection towards the observer (forward)—firm lines,
       ( 39 ) lines of the reflector deflection in the counter direction (backwards)—dash-dots,       
 
           [0065]    ( 40 ) additional (the fifth-sixteenth) radial pneumatic supports, 
           [0066]    ( 41 ) crosses and circles indicate preferred points to install pneumatic valves for optimal and quick release of the mirror sheet, 
           [0067]    ( 42 ) pneumatic chambers have the toroidal form, 
           [0068]    ( 43 ) flexible tube, 
           [0069]    ( 44 ) bushing, 
           [0070]    ( 45 ) radial apertures, 
           [0071]    ( 46 ) longitudinal apertures, 
           [0072]    ( 47 ) nipple, 
           [0073]    ( 48 ) cylindrical spring, 
           [0074]    ( 49 ) flat springs with the pliers-like tips, 
           [0075]    ( 50 ) slots, 
           [0076]    ( 51 ) the first plug, 
           [0077]    ( 52 ) ball. 
           [0078]      FIG. 12  shows the design of the second variant of the pneumatic valve  20 , where positions  42 - 52  repeat the positions of  FIG. 11 , wherein: 
           [0079]    ( 53 ) is the second bushing, 
           [0080]    ( 54 ) is the second plug, 
           [0081]    ( 55 ) are the elastic bands. 
           [0082]      FIG. 13  shows the N-N sectional view as in  FIG. 12 , where positions  42 - 55  repeat the positions of  FIG. 11  and  FIG. 12 . 
           [0083]      FIG. 14  shows the third variant of the pneumatic valve, where positions  42 - 54  repeat the positions of  FIG. 12 . 
           [0084]    ( 56 ) elastic diaphragm, 
           [0085]    ( 57 ) cup. 
           [0086]      FIG. 15  shows the third variant of placing the orientation motors  4  and  5  and filler sources (compressed gas)  4 , where positions  4 - 19  repeat the positions of  FIG. 1 . 
           [0087]    ( 58 ) bar, 
           [0088]    ( 59 ) hinge joints, 
           [0089]    ( 60 ) brackets, 
           [0090]    ( 61 ) r-type lever, 
           [0091]    ( 62 ) the second filler source (gas), 
           [0092]    ( 63 ) pneumatic valve, 
           [0093]    ( 64 ) column of the spinup electric motor, 
           [0094]    ( 65 ) adjusting flange, 
           [0095]    ( 66 ) fingers (pins). 
       
    
    
     DESCRIPTION 
       [0096]    The principle of unfolding the film reflector shown in  FIGS. 1-10  comprises the following: Film radiation reflectors intended for space radio, television and telephone communication, as well as for illuminating ground objects from space at night, must be of several hundred meters in diameter and installed in unmanned aircrafts. On the ground, the reflecting sheet  16  should be folded and packed in such a way as to secure its automatic release and control in space according to a preset program. The entire construction of the film reflector is mounted on the drum  2  that is installed on the cylindrical spacecraft (SC) with the ability for free rotation. The drum starts rotation with the help of the spinup electric motor  3 . The motor is rigidly attached to the SC case and interacts with the drum through the wheel  21 . 
         [0097]    The second  4  and third  5  electric motors for orientation, together with the filler sources (e.g. compressed gas)  8 ,  62 , are fixed rigidly on the rotating drum  2 . The storage sources (gas)  9  and electric motors  4 ,  5  are arranged along the perimeter of the drum in every 90° and are matched and balanced in weight in relation to the axis of the drum rotation. 
         [0098]      FIG. 3  shows the design of the spinup joint. The drum  2  is mounted on the SC case  1  with the ability for free rotation. The second  4  and third  5  spinup electric motors, together with the filler sources (gas)  8 ,  62 , are arranged and affixed along the perimeter of the drum. Two filler sources are used as counterbalances. They should be selected in accordance with the weight of the electric motors  4  and  5 . The wheel  25  placed on the electric motor shaft  3  interacts with the drum and brings it into rotation. Under the action of centrifugal forces created by rotation of the drum and by parallel straightening effect of the pneumatic supports  15  and the external pneumatic chamber  14 , the mirror sheet  16  takes a flat round form. 
         [0099]    The drum may be also in the form of a rotating stator [ FIG. 3 ]. In this case the first electric motor is of no necessity. 
         [0100]    The mirror sheet may be sped up by rotation of the SC case with the help of jet motors. 
         [0101]    Release of the mirror sheet may be done without speeding it up. In this case the rotating stator, the drum and the spinup motor  3  are not needed. 
         [0102]    To control the orientation of the mirror sheet in relation to the SC case, gimbal suspensions are used by interacting the first (internal)  10  and second (external)  11  pneumatic chambers. In this case, the shaft of the second electric motor  4  interacts with the first pneumatic chamber  10  by means of the first curling shaft  6 , whereas the shaft of the third electric motor  5  interacts with the second pneumatic chamber by means of the gimbal shaft and the second curling shaft  7 . Diametrically opposite points of the mentioned pneumatic chambers (gimbal suspensions) are joined at the hinges to the tips of the corresponding curling axes  18 ,  19 . 
         [0103]    The curling shafts  6 ,  7  and the axes of rotation  18 ,  19  are designed in the form of a strip consisting of links connected at the hinges similar to the links of a wristwatch bracelet (see  FIG. 4  and  FIG. 5 ). Such shafts and axes are freely roll up in one plane into a cylindrical pack ready for transportation. The unfolded reflector, the mentioned shafts, and the axes take a flat form and transmit rotation from the electric motors  4 , 5  to the corresponding concentric pneumatic chambers  10 ,  11 . In the mode of rotation, they work as rigid shafts and axes that allow the changing orientation of the pneumatic chambers  10 ,  11  within the angles ±β and ±α correspondingly. 
         [0104]    Design of the second curling shaft  7  displayed in  FIG. 4  and  FIG. 5  is more elaborate than that of the first shaft  6 . This is due to the necessity for transmitting rotation at different angles and for different distances. Such situations arise when the first pneumatic chamber  10  rotates within the ±β angle with the help of the electric motor  4 . 
         [0105]    The gimbal shaft, consisting of the first  26  and second  27  gimbal suspensions and the spider  28 , is included in the design of the second curling shaft  7  in order to transmit rotation at an angle to the second pneumatic chamber  11 . The first gimbal suspension is made from the shaft of the motor  5  itself. A similar attachment design is seen in the gimbal of the curling axis  19 . Constructional elements  29 - 33  are included in the design of the second curling shaft  7  and the axis  19  to perform the function of controlled elongation. Design of this joint is analogous to the design of the office stapler. The guide  29  is a rectangular plate bended at four sides. Its lower end is joined to the second gimbal suspension  27 . The laterals of the guide  29  have narrow longitudinal slots  32  in which the guiding tabs  31  of the slide-block  30  move. The upper end of the guide  29  has a groove in which the slide-block  30  freely moves. The upper end of the spring  33  is attached to the upper end of the slide-block bent at right angles. The lower end of the spring is fastened to the lower end of the guide  29 . In this way, the length of both the second curling shaft and the curling axis is regulated. Links  34  are connected to each other by hinges similar to the links of a wristwatch bracelet. 
         [0106]    The lower line of the links  34  is fastened to the upper end of the slide-block  30 . The uppermost line of the links—connected at the hinges, making a flexible chain—is rigidly attached to the cylindrical tip  36  of the shaft  7 . The tips  36  of the shaft  7  and the axis  19  are free to go through the corresponding sleeves  22 , disposed in the sections of the first pneumatic chamber on both diametrically opposite sides. Then, the tip  36  of the shaft is rigidly attached to the second concentric pneumatic chamber  11  and changes its orientation within the ±a angle. 
         [0107]    After that, the spinup motor becomes disconnected. Then, the chains of the power supply, for the electric motors for orientation  4  and  5  and for unfolding the reflector  16 , are connected with the help of the relay or contact switch. 
         [0108]    Unlike the shafts  6  and  7 , the axes&#39; ends  18  and  19  have tubular tips  21  and connecting pipes through which the filler (gas) is fed into the first and second pneumatic chamber (see  FIG. 2 ). 
         [0109]    Design of the first curling shaft  6  is devoid of the gimbal (details  26 - 28 ) and the joint of lengthening (details  29 - 33 ). In all other respects their elements are identical. The tip of the first curling shaft  6  is rigidly fixed to the first concentric pneumatic chamber  10  and rotates it by the ±β angle. 
         [0110]    The second curling axis  19 , like the first shaft  7 , includes the gimbal (details  26 - 28 ) and the joint of the axis lengthening (details  29 - 33 ). In other respects, axes  18  and  19  are identical in design. 
         [0111]    Unlike the first axis, the tip  21  of the second axis  19  goes through the sleeve  22  in the first concentric pneumatic chamber  10  and hermetically connects the cavity of the second pneumatic chamber  11  with the second filler source (gas)  62 . 
         [0112]    The tubular tip of the first axis  18  connects the cavity of the first concentric pneumatic chamber  10  with the first filler source (gas)  8 . The filler (gas) is fed through the electric pneumatic valve  63  and the hose  9 . If the spinup electric motor is used, the electric pneumatic valve can be of a radio-controlled type. 
         [0113]    To feed the filler (gas) to the second concentric pneumatic chamber  11 , the end of the second axis has a rigidly and coaxially joined tube  21  that is connected with the filler source (gas)  8  by the connecting pipe  24  and the hose  9 . The tip of the tube  21  is rigidly attached to the second concentric pneumatic chamber  11  whose inner cavity pneumatically communicates with the filler source (gas) through the pneumatic valve  63 . If the reflector is unfolded under remote programmed control, the pneumatic valve may be replaced by the radio-controlled electropneumatic valve. The sleeve  22  is rigidly fixed in the second hinge joint  13  along the radial section of the first pneumatic chamber and provides rotation of the second chamber in relation to the first one within the ±α angle. 
         [0114]    The first hinge joint  12  differs from the second one in the following manner: the tip of the first curling axis  18  rotates in the sleeve installed like the second one along the OY axis in the first pneumatic chamber  10 . Thus, the electric motor  4  helps to change the orientation of the first pneumatic chamber within the ±β angle. In this case, the electric motor  5  controls orientation of the second pneumatic chamber  11  within the ±α angle. 
         [0115]    The second pneumatic chamber is rigidly connected to the radial pneumatic supports  15  arranged along the rotation axes OX and OY. Also, the inner cavity of the mentioned pneumatic chamber communicates with the inner cavities of the radial pneumatic supports  15  through pneumatic valves  20 . The pneumatic valves secure the given direction and the order of filling the pneumatic cells of the radial pneumatic supports  15  and the external (the third) pneumatic chamber  14  by the filler (gas). 
         [0116]    This variant of packing the reflecting sheet  16  displayed in  FIG. 4-FIG .  7  requires the following order of filling: first the radial supports  15  oriented along the OY axis should be filled by gas, then the radial supports  15  oriented along the OX axis from the center to the periphery. Additional radial pneumatic supports  15  are also filled from the center to the periphery. The external pneumatic chamber is the last to be filled simultaneously in four directions from the OY axis, or in two directions from every pneumatic support. 
         [0117]    After the external pneumatic chamber takes the form of a circle, the taut bands  17  connected with the second and the external (the third) pneumatic chambers stretch the mirror sheet from all sides in radial directions until the mirror sheet takes the flat round form. 
         [0118]    Arrangement of the pneumatic valves, their carrying capacity, and the distance between two neighboring valves, determine the rate of filling individual parts of radial pneumatic supports and the external pneumatic chamber. 
         [0119]    To provide the necessary quickness in unfolding the mirror sheet  16 , it is possible to use centrifugal forces appearing at the drum  2  spinup. This is done with the help of the first electric spinup motor  3  which has the wheel  25  mounted on its shaft. It is possible to achieve the necessary rate of unfolding the mirror sheet by regulating the speed of rotation of the drum, to which the packed mirror sheet is connected, and with the use of the preset program for filling the pneumatic cells. 
         [0120]    However, the mirror sheet can also be unfolded with the help of only the pneumatic system without resorting to the spinup. In this case, design of the reflector is considerably simpler. 
         [0121]      FIG. 6  shows the mirror sheet  16  after being rolled up from two sides along the OX axis. 
         [0122]      FIG. 7  shows the B view by  FIG. 6 . The crosses  41  ( FIG. 10 ) denote the arrangement of pneumatic valves on the radial supports  15 . Pneumatic valves ensure the necessary rate of the mirror sheet release. The lesser the number of pneumatic valves, the more their carrying capacity, and the less the time needed for the mirror sheet  16  to release. 
         [0123]      FIG. 8  shows the C view of the mirror sheet by  FIG. 7  after it is rolled up from two sides along the OY axis. 
         [0124]      FIG. 9  shows the K view of the mirror sheet by  FIG. 8  after it is rolled up from four sides along two axes. 
         [0125]    The mirror sheet rolled up from four sides is adjusted to the SC case from two sides and occupies the least volume. 
         [0126]    To protect the mirror from outside damage, it is covered by the casing  37 , which consists of two collapsible parts. 
         [0127]    Once delivered to space, the rolled up mirror sheet is unfolded in the opposite order. The collapsible parts of the casing  37  are cast away. First, the sheet is released along the OY axis by filling the pneumatic supports oriented along the OY axis with its simultaneous spinup. Then, the pneumatic supports oriented along the OX axis are straightened. This succession is achieved with the help of valves meant for higher pressure P 2 . 
         [0128]    When centrifugal forces are used for unfolding the mirror sheet the drum is simultaneously rotated with the help of the electric motor  3 . With that end in mind it is possible to rotate the SC case with the help of jet engines. 
         [0129]    The third variant of arrangement of the motors  4 ,  5  and the filler sources (of gas)  8  (see  FIG. 15 ) is used when the radiation reflector is placed at the bow or stern of the SC; in particular, when the reflector is used as a solar sail, or for illuminating ground objects with solar radiation at night, or as a reflector in space radio, television and telephone communication. 
         [0130]    The column (or the shaft of the spinup motor)  64  is oriented along the longitudinal axis of the SC case. 
         [0131]    The reflector is attached to the column by the flange  65 . The adjusting flange has the form of a cylinder whose end is rigidly attached to the bar  58 . Two symmetrical ends of the bar have the electric motor for orientation and for the filler source  8  coaxially and rigidly fixed. Both filler sources  8 ,  62  must be equivalent to the electric motors  4 ,  5  in form and weight. 
         [0132]    If there is no need for the spinup of the reflector, one filler source is used instead of two. It may be installed in any place on SC board. In this case, the shaft of the third electric motor  5  is oriented along the OX axis, i.e. at right angles with the shaft of the second electric motor  4  coinciding with the OY axis. The third electric motor of orientation  5  and the second filler source  62  are attached to the bar  58  by two brackets  60  and the hinge joint  59 , with the ability for free movement revolving around it. 
         [0133]    The shaft of the second electric motor  4  is rigidly fixed to the upper end of the ┌-shaped lever  61 . The lower end of this lever is also connected to the case of the third electric motor for orientation  5 . This connection secures the changes in orientation for the second curling shaft  7  in accordance with variations in orientation of the first concentric pneumatic chamber  10 . In this case, the curling shaft is of equal length which eliminates the necessity for the gimbal shaft (positions  26 - 28 ) and constructional elements ( 29 - 33 ) to lengthen the curling shaft. 
         [0134]    With the small diameters of the first  10  and second  11  concentric pneumatic chambers that can be achieved in the third variant of the reflector design, there is no need for the curling shafts  6 ,  7  and the axes  18 ,  19 . They may be replaced by rigid shafts and axes made in the form of cylindrical rods. The heads of the curling axes  18 ,  19  are set on the fingers (pins)  66  with the ability for free rotation (see  FIG. 15 ). 
         [0135]    To prevent separation of the axes from the fingers  66 , the axes have grooves in which the tips of screws rotate. The tips of screws are wrung up in the bushings which are fixed in the root parts of the curling axes  18 ,  19 . 
         [0136]    Fingers (pins)  66  fixate the position of the curling axes and are rigidly attached to the cases of the corresponding filler sources (of gas)  8 ,  62  along the direction of the OX and OY axes. Thus, fingers  66  are attached coaxically to the corresponding curling shafts  6 ,  7 . 
         [0137]    The disposition and weight of the electric motors  4  and  5 , as well of the two filler sources  8 ,  62  with the attached shafts  6 ,  7  and axes  18 ,  19 , must be chosen in such a way to secure the balance of centrifugal forces as they revolve around the shaft  64  of the spinup electric motor (not shown in  FIG. 15 ). 
         [0138]    In space conditions of weightlessness, it is possible to release the reflecting sheet without the spinup, using only the straightening force of the pneumatic cells. In this case, there is no need in using the spinup devices. They are needed if the diameters of the reflector are large, which excite gyro forces that hinders orientation control. 
         [0139]      FIG. 11  displays the design of the first variant of the pneumatic valve  20 . The valve includes the cylindrical bushing  44  which has the ball  52  and the spring  48  placed inside it. One end of the spring abuts against the ball, while the other end abuts against the plug  51 . The aperture at the other end of the tube is of smaller diameter. The spring-loaded ball hermetically stops the aperture in the tube. The ball lets gas pass into the adjoining pneumatic cell if pressure in the previous cell exceeds the P 1  level. Once this level is exceeded, the spring  48  contracts and the ball lets gas into the next pneumatic cell through the aperture  46  in the bushing  44  and the tube  45 . 
         [0140]      FIG. 12  displays the design of the second variant of the valve  20 . The valve also consists of the cylindrical (second) bushing  53 , the ball  52 , two elastic bands  56  fixed in mutually perpendicular directions, and the second plug  51 . The aperture  45  in the flexible tube coincides with the aperture  46  of the valve. 
         [0141]    Unlike the first variant ( FIG. 11 ), the ball stops the aperture in the bushing  53  owing to the tensile force of the elastic bands  55 . Once the pressure exceeds the preset P 1  level, the elastic bands extend, the ball is loosened, and gas is fed into the next pneumatic cell through the aperture  45 . 
         [0142]    To achieve this effect, the design of the valve (see  FIG. 11  and  FIG. 12 ) should be supplied by two tongs-like flat springs  47 . At one end, these springs are fixed rigidly to the bushing  42  ( 49 ), while the other tongs-like ends abut against the ball  43  from two diametrically opposite sides. Pressing forces of the springs are directed to the center of the ball along the same, single line and mutually compensate each other. Once the pressure level P 1  in the previous pneumatic cell is exceeded, the ball shifts to the left, the tongs-like ends of the springs  47  push the ball out in the same direction and fixate the opened position of the valve. 
         [0143]    Operating principle of the third variant of the pneumatic valve (see  FIG. 14 ) consists of the following. Like the second variant of the pneumatic valve, the ball  52  stops the aperture of the second plug  54 . The elastic diaphragm  56  presses the ball to the spherical indent at the end of the second plug. By varying the thickness and force of elasticity of the diaphragm material, it is possible to find the pressure level at which the pneumatic valve  20  functions. Once the allowable pressure level is exceeded, the diaphragm expands, the aperture in the diaphragm widens, and the ball is pushed out through the aperture of the diaphragm. The ball enters into the bushing  57  cavity, the filler (gas) is fed into the bushing cavity, slightly raising the nipple  47  and going into the cavity of the pneumatic cell  42  through radial apertures  45 . For better reliability, the aperture  46  in the cylindrical tube  42 ( 49 ) may be built over the nipple  53  which lets gas in through only one direction. Pneumatic cells may also be filled with the hardening foam dielectric [ FIG. 1 ]. 
         [0144]    The pneumatic cells may have toroidal or spherical form. Toroidal pneumatic cells can be arranged to form a chain. Toroidal pneumatic cells are smaller in weight and volume than spherical ones. 
         [0145]    The hardening foam dielectric used as the filler enhances reliability of the radiation reflector. 
         [0146]    The valves can be disposed in the joints of the radial pneumatic supports  15  with the second pneumatic chamber. 
         [0147]    The pneumatic valves filling the external (third) pneumatic chamber  14  (denoted by circles in  FIG. 10 ) can be calculated for pressure P 2  higher than P 1  at which the radial pneumatic supports are filled. 
         [0148]    Valves of this kind, calculated for different pressure values P 1  and P 2 , could be used for gradual release of the folded mirror sheet  16 , first along the axis OY, then along the axis OX (see  FIG. 7 ). 
         [0149]    Thus, all pneumatic cells are gradually filled one after another forming the radial supports  15  and the external pneumatic chamber  14 . In this way the whole system is filled. 
         [0150]    In case separate pneumatic cells are damaged, the system retains its form because the valves do not admit gas into the damaged pneumatic cell. In this way, reliability and durability of the whole system is enhanced. 
         [0151]    Like the prototype, the main and supplementary flexible reflecting surfaces can be released as it was described above. 
         [0152]    A film radiation reflector can be used as a solar sail in an unmanned aircraft and for illuminating ground objects by solar radiation at night. 
         [0153]    Sources of information used in drawing up the present application are the following: Aliev, A. S., Tagirov D. T. Film radiation reflector. Patent RU # 2207675, 7H01Q15/14, G 02 B5/12. Apr. 1, 2002; Aliev, A. S., Kaziakhmedov F. G. Solar sailing vessel. Patent RU . . . by the application # 2003128353/11 of Sep. 19, 2003; Syromyatnikov, V. S., Bryants, N. V., Koverina, I. P. Spacecraft with the solar sail. RU, Patent # 2053940, Dec. 10, 1996.