Deployable mirror reflector

 

The invention relates to devices used to study cosmic rays, antennas, etc. displayed on the orbit space in the limited volume of the fairing of the launch vehicle, then deployed to larger sizes. The technical result is the formation of the reflective surface of the large size and maintaining alignment of the mirror elements on Earth. This technical result is achieved in that in a deployable mirror reflector containing the reflective surface of the cell in the form of mirror elements mounted on the framework, deployment mechanisms, hinges and latches, cells are hexahedral shape of the same size and adjacent to the cell in the center, and other cell faces, forming spaced on a circle of the peripheral zone with a common center. On certain adjacent faces of the cells are hinges, deployment mechanisms and latches. The cell located in the center, equipped with fastening elements deployable mirror reflector. The cell located in the center, and the cell peripheral zones installed in the same plane. The tabs are invited to perform magnetic two installed on premika is a very useful move in the plane of the deployable mirror reflector. 3 C.p. f-crystals, 8 ill.

The invention relates to the making, in particular to devices used to study cosmic rays, antennas, etc. displayed on the orbit space in the limited volume of the fairing of the launch vehicle, then deployed to larger sizes. Such deployable mirror reflectors (RSO) can be used to study the solar and galactic radiation and as an important element of radio measurement and information systems of the microwave range.

Known mirror reflector for microwave antennas, in which the reflective surface using a clipping from a parabolic body of revolution [1].

Known also mirrored reflectors [2, 3], in which there are mechanisms for the rotation components of the mirror elements, for example, for the concentration of solar energy. Such reflectors is impossible using existing launch vehicles to bring into space orbit, because there are no devices for their deployment.

Known deployable mirror reflectors for antennas [4], equipped with a deployment mechanism, hinges and latches, taken as a prototype. Considered in this book, the solution can be used is nannah. RSO umbrella of the type used on space relays “Lightning”. RSO umbrella have a fairly rigid structure and the most resistant to wind loads. Therefore, they are often used for antennas of mobile and portable radio stations. When folded, they have sizes that are acceptable for space technology. In RSA umbrella-type of cell in the form of mirror elements are fixed on the frames formed of any rigid or foldable ribs and having the shape of a trapezoid or triangle. Frames are mounted on hinges and provided with clamps. The surface of the mirror is made from metal mesh or metallic fabric. When deploying RSA possible shock loads, the value of which can lead to deformations of the mirror or partial failure of alignment of the mirror elements.

Such RSO not meet the requirements for precision installation of mirror surfaces for studies of cosmic radiation of various energies. Big RSO can be constructed from the mirror elements of relatively small size package which is conveniently linked to the volume of the payload available boosters, such as “Union”. However, such RSO require led on the kind of orbit preserving characteristics, configured on the Earth.

The technical result of the invention is the formation of a reflective surface, such as flat, large size, while ensuring deployment of RSA and maintaining alignment of the mirror elements on the Earth.

This technical result is achieved in that in a deployable mirror reflector containing the reflective surface of the cell in the form of mirror elements mounted on the framework, deployment mechanisms, hinges and latches, in contrast to the known cells are hexahedral shape, the same size and adjacent to the cell in the center, and other cell faces, forming spaced on a circle of the peripheral zone with a common center, and the hinges and deployment mechanisms are located on one of the faces of the cell, located in the center, in addition to the adjoining faces of the first and closing the peripheral zone cells, on the faces of the cells of the first peripheral zone having a common vertex with adjacent faces of the cell, located in the center, and on one of the faces of the cell subsequent peripheral zone adjacent to the trailing cell in the first peripheral area, and also to one of the edges of the cells with the subsequent peripheral areas, with on the x, adjacent to the faces of the cell, located in the center, and to the faces of the cells of each subsequent peripheral zone, as well as on the faces of the cell, closing each subsequent peripheral zone, the cell located in the center, equipped with fastening elements deployable mirror reflector. The cell located in the center, and the cell peripheral zones installed in the same plane. The tabs are invited to perform magnetic of the two mounted on the adjacent faces of the cell parts, one of which has a spherical surface, and the other mounted for movement in the plane of the deployable mirror reflector.

Significant advantages in accuracy and stability characteristics are RSA deployed in the plane. In space wind loads are absent, and the requirements for rigidity deployed RSA can be significantly reduced. The proposed solution will solve the problem of delivery of RT required dimensions and accuracy in the volume of the payload available boosters, such as “Union”. Performing cell hexagonal shapes of the same size will allow the folded package of cells with mirror elements to deliver on arbitrator into space orbit and encouraged them to put in the package, representing the right hexagonal prism. The total area of RT is determined by the number and size of cells. The number of cells can be seven, nineteen, thirty-seven, and so on Deployment of RSA should be smooth, without bumps, with the formation of closed peripheral areas located in the same plane, which is provided by the introduction of mechanisms for the deployment of electric drive, which eliminates shock when you deploy and automate the deployment process of RSO. The use of magnetic clamps with a spherical working surface and setting one of the elements of the latch can be moved in the plane of the deployable mirror reflector improves the quality and reliability of fixation of the cells with each other and in the General plane of RSO. The deployment of the mirror reflector in the plane increases the reliability of maintaining accurate alignment of the mirror elements on the Earth.

The invention is illustrated in Fig.1 - 8, on which is shown:

in Fig.1 is a top view of a deployed mirror reflector, consisting of seven cells;

in Fig.2 - external element I in an enlarged scale;

in Fig.3 - section e-E of Fig.2;

in Fig.4 - section In Fig.2;

in Fig.5 is a section along B-B of Fig.2;

on the tori deployable mirror reflector. consisting of nineteen cells;

in Fig.8 is a view of a deployable mirror reflector, consisting of seven cells in the folded transport position.

Detailed mirror reflector (Fig.1) contains a reflecting surface of the cell 1, located in the center, and cell 21...26located on the periphery and adjacent their faces in the first peripheral area to each other, the faces of the cell 1, located in the center, and to the faces of the subsequent cells of the peripheral zone, and so on, All cells are made in the form of mirror elements mounted on the framework. In the present invention, the mounting and alignment of the mirror elements is not considered. In the recess of one of the edges 3 of the cell 1 has a deployment mechanism 41in the recess of the edge of cell 21set the deployment mechanism 42in the recess of the edge of cell 23set the deployment mechanisms 43and 44in the cut faces of the cell 25set the deployment mechanisms 45and 46. The notches in the sides 3 are performed to provide a more compact design folded in the package cell RSO for transportation, as well as reducing the size of the clearance between the adjacent faces of the disclosed mirror reflects the>, 25and 26set accordingly hinges 51and 52, 53and 54, 55and 56,57and 58, 59and 510, 511and 512. Each pair of hinges forms the axis of the corresponding deployment mechanism. On the adjacent faces of the cells 1 and 221 and 231 and 241 and 25, 25and 26correspondingly set the tabs 61, 62, 63, 64, 65and 66.

In Fig.2 depicts a portion of the main types of RSA (remote item I), which shows the clipping plane sections b-B, B-C, D-G, D-D

In Fig.3 shows the installation of the deployment mechanisms 44and 45. The deployment mechanism 45includes the actuator 7, secured by means of screws 8. On the output axis of the actuator 7 is fixed to the gear 9, siteplease with the sector gear 10 fixed on the verge of a 3 cell 24. On the other side of the cell 24similarly, the fixed gear sector 12, tazapsidis with the gear 13 of the actuator 14 cell 23. Near the actuator 7 are end electrical switches and mechanical stops, which in the drawings are not shown.

In Fig.4 shows the configuration of the upper cha the first of which is mounted on the bracket 15, the second bracket 16. In the hole of the bracket 15 on the bearing 17 mounted the axle 18 on which is fixed the return loop 19 of the first hinge. Loop 19 is also fixed to the edge of the mirror element 23. The design of the second hinge similar in design to the first except that the bearing 17 in the second hinge mounted without axial play, and in the first it “float” to compensate for possible thermal deformation of the cells. The hinges are installed precisely aligned. General axis - a straight line connecting the center axes 18 and 20 parallel to both faces of the cell 22and the faces of the cell 23. Similarly arranged and the rest of the hinges of RSO.

The tabs deployed position RSO made magnetic. In Fig.6 shows the design and installation of one of the possible magnetic retainers, made of two parts. One part of the clamp consists of armature 21 with a spherical working surface 22 and are fixed by bolts and bracket 23 on the verge of cell 23. Second (response) portion of the retainer is placed on the cell 1 and consists of a housing 24 in which is installed a permanent magnet 25, the magnetic cores 26 and 27 and secured by a ring nut 28. The housing 24 is installed in the hole edges of the cell is provided with gasket 29 and the fastening ring nut 30, the position of which is fixed locking nut 31.

Set the same way and the rest of the tabs, RSO.

Spread RSO be carried out as follows. From the on-Board computer or controller of the spacecraft included the first actuator located between cells 1 and 21. Cell 1 with its base fixed to the body of the spacecraft. Therefore, relative to cell 1 starts to rotate around the axis of the first and second hinges package of cell 21...26on the angle, equal to 180 angular degrees. When the drive reaches the limit, cell 21set in the plane of the cell 1, the limit contacts will turn off the first actuator and the controller will include a second actuator located between cells 21and 22. Then will begin the reversal of the package cell 22...26around the axis of the second pair of hinges that are installed between the adjacent faces of the cell 21and 22also on the angle, equal to 180 angular degrees. When the cell 22will be located in the plane of the cell 1, the drive turns off and the first latch will lock the cell 22with cell 1. After this operation turns on the third drive and will begin a 180 angular degrees about the requirements between elements 22...23. After performing this operation, the second latch will lock the cell 23with cell 1 and turns on the fourth drive, will begin a 180 angular degrees relative to the plane of the cell 1 is assembled in the package, cell 24...26around the axis of the third pair of hinges mounted between a pair of elements 23...24. When the cell 24will be located in the plane of the cell 1, the drive turns off and the third latch will lock the cell 24with cell 1. After this operation turns on the fifth drive and will begin a 180 angular degrees relative to the plane of the mirror element 1 is folded in the package, cell 25-26around the axis of the second pair of hinges mounted between cells 24...25. When the cell 25will be located in the plane of the element 1, the drive turns off and the fourth latch will lock the cell 25with cell 1. After this operation turns on the sixth drive and will begin a 180 angular degrees relative to the plane of the cell 1 cell 26around the axis of the sixth pair of hinges mounted between the elements 25and 26. When the cell 26will be located in the plane of the element 1, the drive Viceroy operations formed a closed peripheral area of the cell 21...25connected clamps with Central mirror element 1. Deployable mirror reflector, consisting of seven cells, expanded in the plane about which to mirror Earth elements easily adjusted. Detailed mirror reflector is ready for operation.

Similarly the deployment of the mirror reflector, consisting of nineteen cells (see Fig.7).

Currently implemented technology mirrors-based plastics, preserving its characteristics in terms of open space. Frame mirror elements made of carbon fiber, have high rigidity, stability of the shape and size, reduced weight.

Modern science, technology pose new challenges in space associated with the expansion of RSO cosmic rays for near-earth and interplanetary probes. Thus, in particular, the creation of RSO radiation in the ultraviolet area of over 10 square meters of space-based allows you to solve a number of pressing problems of fundamental physics: collect statistics concentration and registration of cosmic rays of extremely high energy (>1020eV), to identify possible sources of such energy, the reasons for their formation is very useful for creating RSA to study cosmic rays directly in space. To derive RSO almost any required areas together with the system-a satellite into space orbit, you can use existing launch vehicles such as “Union”.

It should also be noted that the Assembly of such RSO is of uniform cells, and the alignment of the mirror elements in terrestrial conditions. Adjustment after deployment of the mirror reflector in space is not required.

Literature

1. Great Soviet encyclopedia, so 2, 1970, p 175, Fig. 15.

2.RF patent №2153132, IPC7F 24 J 2/10, 1998.

3. RF patent №2183002, IPC7G 01 V 8/14, 2002.

4. M. C. Granek, C. I. Loman. “Deployable reflector antenna umbrella”. M.: Radio and communication, 1987, S. 7-12 prototype.

5. RF patent №2147758, IPC7F 24 J 2/10, 1998.

6. Belopolsky, B. Antenna. M: Barongis, 1962, S. 355, Fig.9.26.

Claims

1. Deployable mirror reflector containing the reflective surface of the cell in the form of mirror elements mounted on the framework, deployment mechanisms, hinges and latches, wherein the cells are hexahedral shape of the same size and are adjacent to each other on sides, forming spaced on a circle of the peripheral zone with a common center, if this is svertyvaniya located on one of the faces of the cell, located in the center, on the faces of the cells of the first peripheral zone having a common vertex with adjacent faces of the cell, located in the center, in addition to the adjoining faces of the first and closing the first peripheral zone cells on the adjacent faces of the first cell further peripheral zone, and closing the cell of the first peripheral area and on the adjacent faces of the cells in each subsequent peripheral zone, in addition to the adjoining faces of the first and closing each peripheral zone cells, latches located on the sides adjacent to the sides of the cell, located in the center, except the face, which contains the hinge and the deployment mechanism, and also to the faces of the subsequent cells of the peripheral zone, except for the faces, which are the hinges and deployment mechanisms, the cell located in the center, equipped with fastening elements deployable mirror reflector.

2. Deployable mirror reflector under item 1, characterized in that the cell is located in the center, and the cell peripheral zones installed in the same plane.

3. Deployable mirror reflector under item 1, characterized in that the clamps are made of two magnetic established on the adjacent faces of the cells casw plane deployable mirror reflector.

 

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FIELD: optical engineering.

SUBSTANCE: at least two dielectric layers are produced with preset thickness. Layers are disposed one onto the other to form pack of layers. Thickness of layer packs is subject to reduction and thicknesses of separate layers are similarly reduced by means of deforming layer packs to keep relation of thicknesses or relation of thicknesses of layers. Layer pack is disposed between two carrying layers before subjecting the layers to deformation. At least one carrying layer is formed from several separate layers, which are supposed to be disposed subsequently at the end of process of partial deformation at any previous layer of carrying layer. Separate layers of carrying layer can be overlayed onto previous separate layers of carrying layer.

EFFECT: simplified process of manufacture; improved reflection factor.

22 cl

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